diff --git a/.github/workflows/cpp-python-build.yml b/.github/workflows/cpp-python-build.yml index fe07e77097..c771e841cb 100644 --- a/.github/workflows/cpp-python-build.yml +++ b/.github/workflows/cpp-python-build.yml @@ -36,6 +36,16 @@ jobs: [ -e "$filename" ] || continue xmllint --noout --schema JSBSimSystem.xsd $filename done + - name: Valide aircraft files + run: | + for dir in $(ls -d aircraft/*); do + base=$(basename $dir) + [ "$base" != "blank" ] || continue + filename="${dir}/${base}.xml" + if [ -f "$filename" ]; then + xmllint --noout --schema JSBSim.xsd $filename + fi + done MSIS-validation: name: MSIS code validation diff --git a/JSBSim.xsd b/JSBSim.xsd index 1a4b545a9a..ec470d6523 100644 --- a/JSBSim.xsd +++ b/JSBSim.xsd @@ -1,74 +1,79 @@ - - The JSBSim v2.0 configuration file format (JSBSim-ML) is the medium for describing - aircraft flight characteristics to the JSBSim code. For more information about JSBSim, see the - web site at: www.jsbsim.org. -

- The config file format stores and conveys the characteristics of any unique aircraft to the JSBSim - executable. The information that is specified in the configuration file includes: -

    -
  • Administrative
    • -
  • Geometric and measurement
    • -
  • Mass and weight/balance
    • -
  • Buoyant forces
    • -
  • Ground reactions
    • -
  • External reactions
    • -
  • Propulsion
    • -
  • Systems, Autopilot, and Flight Control
    • -
  • Aerodynamics
    • -
  • Input/Output
    • -
-

- The basic structure of the configuration file at the highest level is shown beginning with the - fdm_config element definition. - - + + The JSBSim v2.0 configuration file format (JSBSim-ML) is the medium for describing + aircraft flight characteristics to the JSBSim code. For more information about + JSBSim, see the web site at: www.jsbsim.org. +

+ The config file format stores and conveys the characteristics of any unique + aircraft to the JSBSim executable. The information that is specified in the + configuration file includes: +

    +
  • Administrative
    • +
  • Geometric and measurement
    • +
  • Mass and weight/balance
    • +
  • Buoyant forces
    • +
  • Ground reactions
    • +
  • External reactions
    • +
  • Propulsion
    • +
  • Systems, Autopilot, and Flight Control
    • +
  • Aerodynamics
    • +
  • Input/Output
    • +
+

+ The basic structure of the configuration file at the highest level is shown + beginning with the fdm_config element definition. + + + + - - This is the root element for a JSBSim config file. - + + This is the root element for a JSBSim config file. + - - + + + - + - + + + - - - - - - - - - + + + + + + + + + - + - + + - - The name of the aircraft this model represents. - + + The name of the aircraft this model represents. + - - - A release type of ALPHA or BETA will print out a warning message explaining - that this preproduction release may not be of high quality. - - + + A release type of ALPHA or BETA will print out a warning message explaining + that this preproduction release may not be of high quality. + @@ -78,10 +83,11 @@ - - Often, the version may initially be simply specified as "\$Revision: 1.29 $", so that - a configuration management tool such as cvs can automatically generate revision numbers. - + + Often, the version may initially be simply specified as "\$Revision: 1.29 $", + so that a configuration management tool such as cvs can automatically + generate revision numbers. + @@ -91,148 +97,309 @@ - - - - + + + + + + - - - - - + + + + + - - - - + + + + + + - - - - + + + + + - - - - + + + + + - - - - + + + + + - - - - + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + - - - + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + - - The fileheader section is where important information about the model is recorded. The authors, their contact information - and affiliation, are all documented in this section. Notes about the model, as well as limitations and reference information are also recorded - in this section. - + + The fileheader section is where important information about the model is + recorded. The authors, their contact information and affiliation, are all + documented in this section. Notes about the model, as well as limitations + and reference information are also recorded in this section. + - - The name of the model author[s]. - + + The name of the model author[s]. + - - The contact email address for an author (optional). - + + The contact email address for an author (optional). + - - The organization that the author[s] belongs to. - + + The organization that the author[s] belongs to. + - - - This is an optional field for a license name and URL. - + + + This is an optional field for a license name and URL. + - - - The name of the license, e.g. "GPL". - - - - - The URL where the license can be found. - - + + + The name of the license, e.g. "GPL". + + + + + The URL where the license can be found. + + - - This field stores the sensitivity classification, such as "classified", "secret", "proprietary", etc. - + + This field stores the sensitivity classification, such as "classified", + "secret", "proprietary", etc. + - - The date that the model was initially created in the form yyyy-mm-dd - + + The date that the model was initially created in the form yyyy-mm-dd + - - The version number in the form #.#, or #.#.#, etc. This can also simply be a cvs keyword, such as "\$Revision: 1.29 $". - + + The version number in the form #.#, or #.#.#, etc. This can also simply + be a cvs keyword, such as "\$Revision: 1.29 $". + - - Copyright holder(s) - + + Copyright holder(s) + - - A simple text description of the aircraft model. - + + A simple text description of the aircraft model. + - - Notes are general notes about the model, perhaps such as special information helpful in flying it. - + + Notes are general notes about the model, perhaps such as special + information helpful in flying it. + - - Limitations for this model should be noted. For instance, if gear is not aerodynamically modeled. - + + Limitations for this model should be noted. For instance, if gear + is not aerodynamically modeled. + - - All references used in creating this model should be included. - + + All references used in creating this model should be included. + - - A reference consists of an author, a publication date, a reference ID (document ID, etc.), - and of course a title. The title is the only item in a reference that is required. - + + A reference consists of an author, a publication date, a reference ID (document + ID, etc.), and of course a title. The title is the only item in a reference + that is required. + @@ -242,979 +409,445 @@ + + + + + + + + + + + + + + + + + + + + + + + + + + + + - The metrics section holds information about the geometric characteristics of the aircraft that are important - for the equations of motion and aerodynamics. Wing (or reference) area, wing span (or lateral reference length), - and wing chord (or longitudinal reference length) are all recorded in this section. The center of graivty is also recorded - in this section. Units may be given as shown in this section. + The metrics section holds information about the geometric characteristics + of the aircraft that are important for the equations of motion and aerodynamics. + Wing (or reference) area, wing span (or lateral reference length), and wing + chord (or longitudinal reference length) are all recorded in this section. + The center of graivty is also recorded in this section. Units may be given + as shown in this section. - - - - - - - - - - + + + + + + + + + + + + + + + + + + + + + + + + - - - - Wing area (reference area) for the vehicle being modeled. The default unit - is square feet (FT2). - - - - - - - - - - - - - Wingspan (lateral reference length) for the vehicle being modeled. The - default unit is feet (FT). - - - - - - - - - - - - - The angle the wing makes with the fuselage centerline for the vehicle being modeled. The default unit - is degrees (DEG). - - - - - - - - - - - - - Chord (longitudinal reference length) for the vehicle being modeled. The default - unit is feet (FT). - - - - - - - - - - - - - Horizontal tail area. The default unit is square feet (FT2). - - - - - - - - - - - - - Horizontal tail arm. This is the distance from the center of gravity - to the quarter chord of the horizontal tail. The default unit is feet (FT). - - - - - - - - - - - - - Vertical tail area. The default unit is square feet (FT2). - - - - - - - - - - - - - - Vertical tail arm. The default unit is feet (FT). - - - - - - - - - - + - - Mass properties are specified in this section. The moments of inertia - are specified first. All of Ixx, Iyy, and Izz are required, in order. The products of inertia are - not required but, if present, must appear in order Ixy, Ixz, Iyz. Next, the empty weight of - the aircraft, and the CG location are specified, in that order. Finally, any number of point masses - can be specified. - + + Mass properties are specified in this section. The moments of inertia are + specified first. All of Ixx, Iyy, and Izz are required, in order. The products + of inertia are not required but, if present, must appear in order Ixy, Ixz, + Iyz. Next, the empty weight of the aircraft, and the CG location are specified, + in that order. Finally, any number of point masses can be specified. + - - - - - - - - - - + + + + + + + + + + + + + + + + + + + + + + + + + - - - - Moment of Inertia, Ixx - - - - - - - - - - - - - Moment of Inertia, Iyy - - - - - - - - - - - - - Moment of Inertia, Izz - - - - - - - - - - - - - Moment of Inertia, Ixy - - - - - - - - - - - - - Moment of Inertia, Ixz - - - - - - - - - - - - - Moment of Inertia, Iyz - - - - - - - - - - - - - Empty weight of vehicle. - - - - - - - - - + - - + + + + + + + + + + + + + + + + + + + + - + - + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + - - - - - + + + + + + + + + - - - A location is a vector, containing an x, Y, and Z, element. The default unit is inches (IN). The unit is specifed - in the unit attribute of the location - not in the individual x, y, or z child elements. - + + + + + The system definition can be present any number of times in an aircraft + definition. This section is used to define an arbitrary system, such as + navigation, guidance, or control avionics, electrical systems, etc. The + system, autopilot, and flight_control sections of a configuration file are + all built the same way, using channel elements that contain strings of + component definitions. + + + + + + + The autopilot section is not required for many uses, including for use + within Flightgear. The autopilot functions can be specified within the + autopilot section, or a file name can be given where the autopilot is + specified. + + + + + + + - - - - + + + + + + + + + + + + + + + + - - - - - - - - - - + + - - - A direction is a unit vector, containing an x, Y, and Z element which defines - a direction in a specified frame. - + + + + + + + + + + - - - + + + + + + + + + - - + - - - + + + + + + + + + + + + + + + + + + - - - - - - - - - - - - The system definition can be present any number of times in an aircraft definition. This - section is used to define an arbitrary system, such as navigation, guidance, or control - avionics, electrical systems, etc. The system, autopilot, and flight_control sections of a - configuration file are all built the same way, using channel elements that contain strings - of component definitions. - - - - - - - - - - - - - - - - The autopilot section is not required for many uses, including for use within Flightgear. - The autopilot functions can be specified within the autopilot section, or a file name can be given where the - autopilot is specified. - - - - - - - - - - - - - - - - This element specifies a minimum and/or a maximum limit that the associated component will be allowed - to have. The result will be clipped to the specified limits. - - - - - - - - - - - The domain defines the minimum and maximum input value allowed. - - - - - - - - - - - The range defines the minimum and maximum output value mapped.. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - The aerosurface scale component maps an input value (which must fall within the span specified in the domain element) - to an output value that falls within the span specified in the range element. For example, if the actual input value is 30% of - the distance from the minimum to the maximum domain value, the output would be the value corresponding - to 30% of the span of the range, from the minimum range value. - - - - - - - - - - - The Gain element may contain a fixed numeric value, or it may be a property name. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - The Gain element may contain a fixed numeric value, or it may be a property name. - - - - - - - - - - - - - - - - - - - - The Gain element may contain a fixed numeric value, or it may be a property name. - - - - - - - - - - - - - - - - - - - - - - - - - - - - + + - + - - - - - - - - + + + + + + - - - - - - - - - - An actuator component models a general purpose mechanical effector. The actuator can - exhibit a lag, can be rate- and position-limited, can feature a bias, can have a deadband, - and it can feature hysteresis. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - + - - - - - - - - - - - - - - - - - - - - - - The width value specifies the width of the deadband - i.e. - the total span about zero where the input will be mapped to zero output. - - - - - - - The noise can be entered as a percentage of the signal, or as an absolute value. - - - - - - - - - - - - - - - - - + + + - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - + + + + + + + + + - + - - - - + + - - - - - + + + + + + + + + + + + + + + + + + + - + + + + - - - - - + + + - - - - - - - - + + + + + + + + + + + + + + + - - + + + - - - + + + - - - - - - - - - - - - - - - - - - - - - - - - - - - - - + - - - + @@ -1225,564 +858,163 @@ - - - - - - - - - - - - - + - - - - - - + + + + + + + + + - + - + + - + + + - - - - + + + + - - + + - + + - - + + + + + + + + + - - - - + + + - - - - + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - + + - - - - + + + - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - The pointing element is an alternative to the use of the orient element. With the pointing - element, a unit vector is supplied that represents the direction that the thruster force vector acts - in. The pointing vector is defined in the structural frame. - - - - - - - - - - - - - - + + - - + + + + + - - - - - - - - - - - - - - - - - - \ No newline at end of file + + + + + + + + + + + + + + + diff --git a/JSBSimCommon.xsd b/JSBSimCommon.xsd index 13512ffd43..720928e360 100644 --- a/JSBSimCommon.xsd +++ b/JSBSimCommon.xsd @@ -1,6 +1,11 @@ + + + + + @@ -16,6 +21,23 @@ + + + + + + + + + + + + + + + + + A "property" is a JSBSim simulation parameter that represents any of a @@ -26,14 +48,20 @@ - + - + + + + + + + @@ -44,33 +72,90 @@ - + + + + + + + + + + + + + A location is a vector, containing an X, Y, and Z, element. The default unit + is inches (IN). The unit is specifed in the unit attribute of the location + - not in the individual x, y, or z child elements. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + - + @@ -81,6 +166,7 @@ + @@ -119,24 +205,772 @@ - + - + - + + + + + A description of the function. + + + + + + + + + + + + + + + + + + + + + + + + + + + - + + + + + + + + + + + + + + + + + + + + + + + + + + + + + The name for a channel is simply a brief, descriptive, name. The name + is not used for anything other than display. + + + + + The execute attribute value refers to a property that evaluates to a + boolean indicating whether the channel should execute or not. If this + attribute is not supplied, the channel always executes. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + The aerosurface scale component maps an input value (which must fall within + the span specified in the domain element) to an output value that falls + within the span specified in the range element. For example, if the actual + input value is 30% of the distance from the minimum to the maximum domain + value, the output would be the value corresponding to 30% of the span of + the range, from the minimum range value. + + + + + + + + - A description of the function. + The Gain element may contain a fixed numeric value, or it may be a + property name. - + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + - + - \ No newline at end of file + + + + + + + + + + + Specifies the proportional constant value or property. + + + + + The integrator control action gain. + + + + + + + + Specifies a rectangular integrator. + Specifies a trapezoidal integrator. + Specifies an Adams-Bashforth second order integrator. [default] + Specifies an Adams-Bashforth third order integrator. + + + + + + + + + + The derivative control action gain. + + + + + The trigger element provides a way to specify a property that controls + how the integrator works, and is designed for wind-up protection. If + the value of the property supplied to the trigger element is 0, there + is no effect. If the value of the trigger property is non-zero, + (positive or negative) then the integrator does not integrate and + holds the last value. If the trigger property value is negative, the + integrator value is reset to 0.0. + + + + + + pvdot is the process variable time derivative. If not specified, + the derivative control action will be determined from the change + in the input from the last time step (divided by the time step + size). If pvdot is specified, the specified value will be used + instead. The difference may be minimal in practice - UNLESS there + is an unnatural step change in the input value. For instance, if + the control input (process variable) is alpha, an alphadot value + is calculated as mentioned from the previous value. If pvdot is + explicitly specified as alphadot (alphadot is calculated and is + available as a native property in JSBSim) the results can be + smoother - particularly if there is a step change in the error + signal (the input) due to a step change in the target state. To + be clear, pvdot is meant to be the time derivative of the + input parameter. If the input to the PID controller is pitch rate + then pvdot should be pitch acceleration. If altitude is the input + then pvdot should be altitude rate. + + + + + + + + + + + + + + + Specifies a standard PID controller where the output is defined + as: Output = Kp * (Input + Integrator_value + Kd*Dval), where + Dval is the time derivative of the input signel. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + The Gain element may contain a fixed numeric value, or it may be a + property name. + + + + + + + + + + + + + + + + + + + + + The Gain element may contain a fixed numeric value, or it may be a + property name. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + An actuator component models a general purpose mechanical effector. The + actuator can exhibit a lag, can be rate- and position-limited, can + feature a bias, can have a deadband, and it can feature hysteresis. + + + + + + + + + The rate limit can be specified as a numeric value or as a property. + Further, an "incr" or "decr" sense attribute to specify which + direction the rate limit should apply to. + + + + + + + The sense attribute determines which direction the rate + limit applies to. If no sense is given, the rate limit + applies to both directions equally. If "incr" is specified + then the rate limit applies only to the rate of increase. + If "decr" is specified, then the rate limit applies only to + a decreasing rate. The decreasing rate limit - if given - is + assumed to be negative - no negative sign is required. + + + + Specify this type when the rate limit applies to an increasing rate. + Specify this type when the rate limit applies to a decreasing rate. + + + + + + + + + + + + + + + + + + + + + + + + + + + + The width value specifies the width of the deadband - i.e. the total + span about zero where the input will be mapped to zero output. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + The noise can be entered as a percentage of the signal, or as an absolute value. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + This element specifies a minimum and/or a maximum limit that the + associated component will be allowed to have. The result will be + clipped to the specified limits. + + + + + + + + + + + + + The range defines the minimum and maximum output value mapped.. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + The format in which the data output will be issued. + + + + + + + + + + + + + + + + diff --git a/JSBSimScript.xsd b/JSBSimScript.xsd index 084c61af9c..9185db9140 100644 --- a/JSBSimScript.xsd +++ b/JSBSimScript.xsd @@ -21,65 +21,20 @@ - - + + - - - - - - - - - - - - - - - - - - - - - - - The format in which the data output will be issued. - - - - - - - - - - - - - - - - + + - - - - - - - - The "run" element has as its parent the "runscript" element. The run @@ -91,7 +46,7 @@ - + A property element placed within the run element (in a sort of @@ -108,19 +63,19 @@ - + This attribute is not currently used. A script will always begin execution at time 0.0. - + Since script execution always begins at time 0.0, the "end" attribute is essentially the same thing as the duration of the script. - + The dt attribute is simply the frame time, or the times step size. @@ -136,12 +91,12 @@ - + - + - - + + The delay element represents the number of seconds to delay in executing the set actions for an event once the conditions have @@ -207,7 +162,7 @@ - + @@ -231,7 +186,7 @@ - + @@ -275,32 +230,4 @@ - - - - - - - - - - - - - - - - - - - - - - diff --git a/JSBSimSystem.xsd b/JSBSimSystem.xsd index 60be377f9f..8e6c488921 100644 --- a/JSBSimSystem.xsd +++ b/JSBSimSystem.xsd @@ -4,763 +4,14 @@ - - - - The system definition can be present any number of times in an aircraft - definition. This section is used to define an arbitrary system, such as - navigation, guidance, or control avionics, electrical systems, etc. The - system, autopilot, and flight_control sections of a configuration file - are all built the same way, using channel elements that contain strings - of component definitions. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - The name for a channel is simply a brief, descriptive, name. The name - is not used for anything other than display. - - - - - The execute attribute value refers to a property that evaluates to a - boolean indicating whether the channel should execute or not. If this - attribute is not supplied, the channel always executes. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - The aerosurface scale component maps an input value (which must fall within the span specified in the domain element) - to an output value that falls within the span specified in the range element. For example, if the actual input value is 30% of - the distance from the minimum to the maximum domain value, the output would be the value corresponding - to 30% of the span of the range, from the minimum range value. - - - - - - - - - - - The Gain element may contain a fixed numeric value, or it may be a property name. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Specifies the proportional constant value or property. - - - The integrator control action gain. - - - - - - - Specifies a rectangular integrator. - Specifies a trapezoidal integrator. - Specifies an Adams-Bashforth second order integrator. [default] - Specifies an Adams-Bashforth third order integrator. - - - - - - - - - The derivative control action gain. - - - - The trigger element provides a way to specify a property that controls - how the integrator works, and is designed for wind-up protection. If - the value of the property supplied to the trigger element is 0, there - is no effect. If the value of the trigger property is non-zero, - (positive or negative) then the integrator does not integrate and - holds the last value. If the trigger property value is negative, the - integrator value is reset to 0.0. - - - - - - pvdot is the process variable time derivative. If not specified, - the derivative control action will be determined from the change - in the input from the last time step (divided by the time step - size). If pvdot is specified, the specified value will be used - instead. The difference may be minimal in practice - UNLESS there - is an unnatural step change in the input value. For instance, if - the control input (process variable) is alpha, an alphadot value - is calculated as mentioned from the previous value. If pvdot is - explicitly specified as alphadot (alphadot is calculated and is - available as a native property in JSBSim) the results can be - smoother - particularly if there is a step change in the error - signal (the input) due to a step change in the target state. To - be clear, pvdot is meant to be the time derivative of the - input parameter. If the input to the PID controller is pitch rate - then pvdot should be pitch acceleration. If altitude is the input - then pvdot should be altitude rate. - - - - - - - - - - - - - - Specifies a standard PID controller where the output is defined - as: Output = Kp * (Input + Integrator_value + Kd*Dval), where - Dval is the time derivative of the input signel. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - The Gain element may contain a fixed numeric value, or it may be a property name. - - - - - - - - - - - - - - - - - - - - The Gain element may contain a fixed numeric value, or it may be a property name. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - An actuator component models a general purpose mechanical effector. The actuator can - exhibit a lag, can be rate- and position-limited, can feature a bias, can have a deadband, - and it can feature hysteresis. - - - - - - - - - - The rate limit can be specified as a numeric value or as a property. - Further, an "incr" or "decr" sense attribute to specify which - direction the rate limit should apply to. - - - - - - - The sense attribute determines which direction the rate - limit applies to. If no sense is given, the rate limit - applies to both directions equally. If "incr" is specified - then the rate limit applies only to the rate of increase. - If "decr" is specified, then the rate limit applies only to - a decreasing rate. The decreasing rate limit - if given - is - assumed to be negative - no negative sign is required. - - - - Specify this type when the rate limit applies to an increasing rate. - Specify this type when the rate limit applies to a decreasing rate. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - The width value specifies the width of the deadband - i.e. - the total span about zero where the input will be mapped to zero output. - - - - - - - The noise can be entered as a percentage of the signal, or as an absolute value. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - This element specifies a minimum and/or a maximum limit that the - associated component will be allowed to have. The result will be - clipped to the specified limits. - - - - - - - - - + - The domain defines the minimum and maximum input value allowed. + The system definition can be present any number of times in an aircraft + definition. This section is used to define an arbitrary system, such as + navigation, guidance, or control avionics, electrical systems, etc. The + system, autopilot, and flight_control sections of a configuration file are + all built the same way, using channel elements that contain strings of + component definitions. - - - - - - - - - - The range defines the minimum and maximum output value mapped.. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - diff --git a/aircraft/737/737.xml b/aircraft/737/737.xml index 364b39ecb0..3d853eca7b 100644 --- a/aircraft/737/737.xml +++ b/aircraft/737/737.xml @@ -3,17 +3,16 @@ - + Dave Culp Aeromatic - 2006-01-04 + + 2006-01-04 $Revision: 1.43 $ Models a Boeing 737. - - GPL (General Public License) - http://www.gnu.org/licenses/gpl.html - This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or @@ -115,7 +114,7 @@ 120000 10000 20000 - + 0.0 RIGHT 1 @@ -844,7 +843,7 @@ - - + + - fcs/aileron-cmd-norm - fcs/elevator-cmd-norm - fcs/rudder-cmd-norm - fcs/throttle-cmd-norm[0] + fcs/aileron-cmd-norm + fcs/elevator-cmd-norm + fcs/rudder-cmd-norm + fcs/throttle-cmd-norm[0] fcs/throttle-cmd-norm[1] - simulation/terminate - + simulation/terminate + - diff --git a/aircraft/787-8/787-8.xml b/aircraft/787-8/787-8.xml index 8e317186bd..3b358d9650 100644 --- a/aircraft/787-8/787-8.xml +++ b/aircraft/787-8/787-8.xml @@ -6,7 +6,7 @@ Narendran Muraleedharan, Dwayne Gable and Nicky Ivy - 2011-12-29 + 2011-12-29 $Revision: 1.10 $ Flight Dynamics Model for the Boeing 787-8 @@ -64,7 +64,7 @@ 350 - + -898.32 0 51.22 @@ -76,7 +76,7 @@ 1800 - + -591 0 78.8 @@ -87,7 +87,7 @@ 6400 - + -216.7 0 78.8 @@ -98,7 +98,7 @@ 25000 - + 157.6 0 78.8 @@ -110,7 +110,7 @@ 10000 - + -394 0 -39.4 @@ -121,7 +121,7 @@ 5000 - + 157.6 0 -39.4 @@ -245,6 +245,21 @@ + + + + -612.06718 + 0 + -100 + + + 1 + 0 + 0 + + + + @@ -422,8 +437,8 @@ aero/qbar-psf - 3.0000 0.0000 - 11.0000 2.0000 + 3.0000 0.0000 + 11.0000 2.0000
@@ -433,8 +448,8 @@ aero/qbar-psf - 3.0000 0.0000 - 11.0000 0.0000 + 3.0000 0.0000 + 11.0000 0.0000
@@ -453,8 +468,8 @@ aero/qbar-psf - 2.9900 0.0000 - 3.0000 1.0000 + 2.9900 0.0000 + 3.0000 1.0000
@@ -566,19 +581,17 @@ Change_in_lift_due_to_ground_effect - - - aero/h_b-mac-ft - - 0.0000 1.3000 - 0.1000 1.2500 - 0.1500 1.1000 - 0.2000 1.1200 - 1.1000 1.1000 - 1.2000 1.0000 - -
- + + aero/h_b-mac-ft + + 0.0000 1.3000 + 0.1000 1.2500 + 0.1500 1.1000 + 0.2000 1.1200 + 1.1000 1.1000 + 1.2000 1.0000 + +
@@ -893,8 +906,8 @@ velocities/mach - 0.0000 -1.3000 - 2.0000 -0.3200 + 0.0000 -1.3000 + 2.0000 -0.3200
@@ -977,19 +990,4 @@ - - - - -612.06718 - 0 - -100 - - - 1 - 0 - 0 - - - - diff --git a/aircraft/A320/A320.xml b/aircraft/A320/A320.xml index b922f4667f..bac2be8e06 100644 --- a/aircraft/A320/A320.xml +++ b/aircraft/A320/A320.xml @@ -6,7 +6,7 @@ Unknown - 2003-01-01 + 2003-01-01 Version Airbus A320 diff --git a/aircraft/B17/B17.xml b/aircraft/B17/B17.xml index c7f29c897b..8beda93a85 100644 --- a/aircraft/B17/B17.xml +++ b/aircraft/B17/B17.xml @@ -6,7 +6,7 @@ Aeromatic v 0.9, refined by Jon Berndt - 2008-12-22 + 2008-12-22 $Revision: 1.8 $ Models a Boeing B-17G. @@ -246,9 +246,9 @@ - + - B-17 Pilot's Manual "Left Outboard Tank 1" (54 US Gallons) + 24.7 -45.8 @@ -259,7 +259,7 @@ - B-17 Pilot's Manual "Left Outboard Tank 2" (54 US Gallons) + 24.7 -43.8 @@ -270,7 +270,7 @@ - B-17 Pilot's Manual "Left Outboard Tank 3" (54 US Gallons) + 24.7 -41.9 @@ -281,7 +281,7 @@ - B-17 Pilot's Manual "Left Outboard Tank 4" (54 US Gallons) + 24.7 -40.0 @@ -292,7 +292,7 @@ - B-17 Pilot's Manual "Left Outboard Tank 5" (54 US Gallons) + 24.7 -37.7 @@ -303,7 +303,7 @@ - B-17 Pilot's Manual "Left Inboard Tank 6" (67.5 US Gallons) + 24.7 -35.8 @@ -314,7 +314,7 @@ - B-17 Pilot's Manual "Left Inboard Tank 7" (67.5 US Gallons) + 24.7 -33.9 @@ -325,7 +325,7 @@ - B-17 Pilot's Manual "Left Inboard Tank 8" (67.5 US Gallons) + 24.7 -32.0 @@ -336,7 +336,7 @@ - B-17 Pilot's Manual "Left Inboard Tank 9" (67.5 US Gallons) + 24.7 -30.1 @@ -347,7 +347,7 @@ - B-17 Pilot's Manual "Left Outboard Engine tank" (425 US Gallons) + 22.4 -25.8 @@ -358,7 +358,7 @@ - B-17 Pilot's Manual "Left Inboard Engine tank" (213 US Gallons) + 22.4 -14.3 @@ -369,7 +369,7 @@ - B-17 Pilot's Manual "Left Inboard Engine 2 Feeder tank" (212 US Gallons) + 25.0 -14.3 @@ -382,7 +382,7 @@ - B-17 Pilot's Manual "Right Inboard Engine Feeder tank" (212 US Gallons) + 25.0 14.3 @@ -393,7 +393,7 @@ - B-17 Pilot's Manual "Right Inboard Engine tank" (213 US Gallons) + 22.4 14.3 @@ -404,7 +404,7 @@ - B-17 Pilot's Manual "Right Outboard Engine tank" (425 US Gallons) + 22.4 25.8 @@ -415,7 +415,7 @@ - B-17 Pilot's Manual "Right Inboard Tank 9" (67.5 US Gallons) + 24.7 30.1 @@ -426,7 +426,7 @@ - B-17 Pilot's Manual "Rightt Inboard Tank 8" (67.5 US Gallons) + 24.7 32.0 @@ -437,7 +437,7 @@ - B-17 Pilot's Manual "Right Inboard Tank 7" (67.5 US Gallons) + 24.7 33.9 @@ -448,7 +448,7 @@ - B-17 Pilot's Manual "Right Inboard Tank 6" (67.5 US Gallons) + 24.7 35.8 @@ -460,7 +460,7 @@ - B-17 Pilot's Manual "Right Outboard Tank 5" (54 US Gallons) + 24.7 37.7 @@ -472,7 +472,7 @@ - B-17 Pilot's Manual "Right Outboard Tank 4" (54 US Gallons) + 24.7 40.0 @@ -483,7 +483,7 @@ - B-17 Pilot's Manual "Right Outboard Tank 3" (54 US Gallons) + 24.7 41.9 @@ -494,7 +494,7 @@ - B-17 Pilot's Manual "Right Outboard Tank 2" (54 US Gallons) + 24.7 43.8 @@ -505,7 +505,7 @@ - B-17 Pilot's Manual "Right Outboard Tank 1" (54 US Gallons) + 24.7 45.8 @@ -740,7 +740,7 @@ - + @@ -1090,15 +1090,15 @@ ON ON - ON - ON ON - ON - ON OFF - ON ON + ON + ON + ON + ON + ON aero/angle/right_wing_tip_alpha - + diff --git a/aircraft/B747/B747.xml b/aircraft/B747/B747.xml index 36b31bf2e7..774173dd50 100644 --- a/aircraft/B747/B747.xml +++ b/aircraft/B747/B747.xml @@ -6,13 +6,12 @@ Unknown - 2002-01-01 + + 2002-01-01 $Id: B747.xml,v 1.25 2012/12/22 15:22:17 jberndt Exp $ Boeing 747 - - GPL (General Public License) - http://www.gnu.org/licenses/gpl.html - This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or @@ -355,21 +354,21 @@ fcs/flap-pos-deg - - fcs/flap-pos-deg - - 0 - 30 - - - 0 - 1 - - fcs/flap-pos-norm - - + + fcs/flap-pos-deg + + 0 + 30 + + + 0 + 1 + + fcs/flap-pos-norm + + gear/gear-cmd-norm diff --git a/aircraft/Boeing314/Boeing314.xml b/aircraft/Boeing314/Boeing314.xml index 6213e154ab..4d5fa36eb2 100644 --- a/aircraft/Boeing314/Boeing314.xml +++ b/aircraft/Boeing314/Boeing314.xml @@ -6,15 +6,14 @@ - 11 September 2009 + + 2009-09-11 1.05 Boeing314A - - GPL (General Public License) - http://www.gnu.org/licenses/gpl.html - This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or @@ -93,26 +92,26 @@ - Artificial coefficients start by A. - + Not possible : - buoyancy by weak spring, because that can rear up at rest - (and speed makes water as hard as concrete). + (and speed makes water as hard as concrete). - rebound by hard spring, because static can be unstable with empty weight. - + - + Engine limits : * maximum except take-off (straight line manifold pressure variation) : 33.2 in. hg. 2100 rpm (1200 hp) at 5400 ft, 35.0 in. hg. 2100 rpm (1200 hp) at sea level. * take-off (2 minutes), 42.5 in. hg. 2400 rpm (1550 hp). Airspeed limits : * level flight or climb 178 mph (155 kt) true, glide or dive 212 mph (184 kt) true. * flaps extended (40 or less) 121 mph (105 kt) true. - * flaps extended (more than 40) 105 mph (91 kt) true. + * flaps extended (more than 40) 105 mph (91 kt) true. Weight limits : landing 80000 lb, take-off 84000 lb. Fuel capacity : 5448 gallons (32688 lb) : 2 tanks at 600 gallons (3600 lb) each, in wing stubs; @@ -146,13 +145,13 @@ diameter 14'9-3/8" maximum 14'5-5/8" minimum (1928 lb). * Hamilton standard 3 blade constant speed, 6159A-0 to 6159A-3 inclusive, diameter 14'3/8" maximum 13'8-3/4" minimum (1819 lb). - + - + Same model as B-314, except for engine, powerplane installation, engine mount, and inner structural details. @@ -171,8 +170,8 @@ Propeller : Hamilton standard 3 blade constant speed, 6243A-3 to 6243A-6 inclusive, diameter 14'9-3/8" maximum 14'5-5/8" minimum (1928 lb). - - + + - http://case.pr.erau.edu/reports/US_reports/1940/1943.02.22_PanAmericanAirways_Boeing-314.pdf (crash - 22 february 1943 Lisbon, Portugal) : @@ -217,7 +216,7 @@ Normal range : 3500 miles. - http://www.flyingclippers.com/B314.html/ - + Ceiling : cruise 13400 ft, maximum 19600 ft, climb 562 ft/min. Crew : 6-10. Payload : 40-74 (36 night) passengers. @@ -236,7 +235,7 @@ - http://www.southernoregonwarbirds.org/fa3.html/ (Franck Varnum flew during WWII). - + The sponsons (the short fins sticking out of the sides of the fuselage) provide lateral stability on the water. They were filled with gasoline and as a result were not at all that buoyant. If you had to taxi to downwind, on the turn to downwind the wind could get under the upwind wing @@ -262,7 +261,7 @@ - http://www.pilotfriend.com/flight_training/frames2/seaplane_main_frame.htm/ : How to fly seaplanes and amphibians. - + - + Pilot's eyepoint location, in aircraft's own coord system, FROM cg. X, Y, Z, in inches @@ -300,11 +299,11 @@ Add ac_wingincidence : 1/20 of wing chord. Htailarm : distance from CG to horizontal tail tip. - + 2867 152 - 21.57 2.86 + 21.57 458.72 22.91 516.06 @@ -328,13 +327,13 @@ - + Center of gravity location, empty weight, in aircraft's own structural coord system. X, Y, Z, in inches; X is positive out the tail, Y positive out the right wing. Put in comment payload, to test at empty weight. - + 2.31442e+06 1.34649e+06 3.59608e+06 @@ -349,7 +348,7 @@ 1500 - + 460.0 0 -31.8 @@ -358,7 +357,7 @@ - + Left/right sponsons at 70% MAC and 1/4 wing : higher at 3/4 hull height (tilt at rest). The hump and step gears replaces the nose and rear gears, when the hull raises on the step. @@ -372,7 +371,7 @@ Disabling the filters restores the brakes. CAUTION : changing gear height or spring affects rest h_b-mac-ft ! - + 66.4 @@ -465,12 +464,30 @@ + + + anchor at nose tip. + + + + 0 + 0 + 0 + + + -1 + 0 + -1 + + + + - + propeller at 1/5 of length, 1/10 and 2/10 of wing span. 1 tank feeds 1 engine, plus floor and sponson (left or right). - + 0 4 @@ -539,15 +556,13 @@ - + - - wing tanks behind the engines. - + 502 -364.8 @@ -585,9 +600,7 @@ 3600 - - inboard tank (floor). - + 502 0 @@ -597,9 +610,7 @@ 5760 - - ouboard tanks (hydro-stabilizer). - + 502 -182.4 @@ -622,15 +633,13 @@ systems/hull/anchor - - anchor opposes to propeller and inertia. - + - -1 forces/fbx-gear-lbs + -1 @@ -663,9 +672,7 @@ fcs/pitch-trim-sum 0.01745 - - replaced -0.35/0.30 by real -25/25 deg. - + -25 25 @@ -761,9 +768,7 @@ fcs/flap-cmd-norm - - changed 15/30 deg to 15/40/55 (real is above 40). - + 0 @@ -814,7 +819,7 @@ - + Hydrodynamics depends of 4 coefficients, related to gear height and spring. h_b-mac-ft at rest (with the 84000 lbs/ft spring) : @@ -827,9 +832,7 @@ 0.0690 is also 0.0490 + 0.020, where 3.04' (from the keel to step) / wing span (152') = 0.020; - - Hull resistance in water until the step : - maximum at 42 % of takeoff speed : hump at 42 kt full load (100 kt) and 34 kt empty load (80 kt). @@ -867,7 +870,7 @@ - 96.0/106, 7.0/59. - 99.5/106, 5.0/59. - 106.0/106, 0.0/59. (lift-off) - + Hull_resistance @@ -927,19 +930,19 @@
- - The hull goes on its step : - - hydrodynamic lift. - - 80 % when going out of water. - - 1st altitude = h_b-mac-ft at rest. - - 2nd altitude : in the middle. - - 3rd altitude : 3.04' (from the keel) / wing span (152') = 0.020; - the planing layer is thin. - - Not implemented : - - drag when the bow plunges into a wave hump (nose down). - - drag when after body digs the water (nose up). - + Step_lift @@ -961,13 +964,13 @@
- - The hull goes on its step : - - as sponson gets out water, additional lift. - - sponson in water reduces lift : 0.02/0.029 rad at rest. - - on step, the possible roll is higher (sponson touching water). - - after lift off, no loss by water. - + Sponson_lift @@ -999,17 +1002,17 @@
- - The bow climbs over the wave hump : - - strong pitch (positiv moment) until the hump (nose up on the hump), - then light nose down (negativ moment). - - the center of buoyancy shifts with speed : - near center of gravity (step) at rest, then aft the step (afterbody) - when ploughing the wave hump; finally forwards the step (forebody), once planing on the step. - - 80 % when going out of water. - - similar to NACA TN 512, figure 13. - + Step_moment @@ -1035,9 +1038,7 @@
- - created to help the takeoff at full load. - + Change_in_lift_due_to_ground_effect @@ -1052,15 +1053,15 @@
- - Compensates compression of nose gear by speed : - - enough strong to make rise the bow, and have an effect on flight commands. - - 80 % when going out of water. - - hydrodynamic lift indirectly provides weathervaning if wing has enough alpha. - In reality, cross wind applied on the center of gravity (CG), is opposed by the water acting on a sinking float. - Hence a momment around the center of buoyancy (CB). - - gear reaction code seems not appropriate in this case. - + Compression_correction @@ -1086,18 +1087,18 @@
- - NACA report 1103 (rebound on touch-down ) : - - figure 2, khi 3 and 15 deg. - gamma, velocity angle over water : 0 - 80 deg, horizontal is 0. - - figure 6, tau 6 deg (used as 3 deg) and tau 12 deg (used as 15 deg). - tau, bow pitch over water : 3 - 15 deg, horizontal is 0. - - khi = (sin(tau) / sin(gamma)) x cos(tau + gamma) : - - no rebound when flight path near vertical (energy absorbed by water). - - maximum near planing condition. - - favoured by bow pitch. - + Rebound_due_to_khi @@ -1124,11 +1125,11 @@ - - - more drag inside water than air (ratio 7/1). - - increases the takeoff distance. - - could depend of weight. - + Drag_at_hump @@ -1139,9 +1140,7 @@ - - added. - + Drag_at_zero_lift @@ -1150,10 +1149,10 @@ 0.0274 - - - renamed from CDo. - - substracted Cdo 0.0274. - + Drag_due_to_alpha @@ -1172,9 +1171,7 @@ - - 1/10 of wing. - + Sponson_drag_at_zero_lift @@ -1184,9 +1181,7 @@ 0.0027 - - 1/10 of wing. - + Drag_due_to_sponson @@ -1266,10 +1261,10 @@
- - - drag is always positiv. - - divide by 10. - + Drag_due_to_Elevator_Deflection @@ -1296,10 +1291,10 @@ - - - and missing lift for flaps. - - introducing roll quickly reduces lift at landing. - + Lift_at_step @@ -1311,9 +1306,7 @@ - - created. - + Lift_at_zero_alpha @@ -1323,9 +1316,7 @@ 0.2400 - - substracted CLo 0.240. - + Lift_due_to_alpha @@ -1344,10 +1335,10 @@ - - - and missing lift for flaps. - - 1/10 of wing. - + Sponson_lift_at_zero_alpha @@ -1358,10 +1349,10 @@ 0.0240 - - - and missing lift for flaps. - - 1/10 of wing. - + Lift_due_to_sponson @@ -1381,10 +1372,10 @@ - - - unchanged. - - 0.9 is the value to takeoff at 2/3 full load; water provides the missing lift. - + Delta_Lift_due_to_flaps @@ -1488,9 +1479,7 @@ - - could depend of weight. - + Compression @@ -1502,11 +1491,11 @@ - - - rest 0 ft/min. - - maximum 700 ft/min. - - before hydrodynamic lift. - + Rebound_due_to_vertical_speed @@ -1626,23 +1615,4 @@ - - - - anchor at nose tip. - - - - 0 - 0 - 0 - - - -1 - 0 - -1 - - - - diff --git a/aircraft/C130/C130.xml b/aircraft/C130/C130.xml index 5a23597dae..24fd1ebd85 100644 --- a/aircraft/C130/C130.xml +++ b/aircraft/C130/C130.xml @@ -6,7 +6,7 @@ Unknown - 2004-01-01 + 2004-01-01 $Id: C130.xml,v 1.12 2012/12/22 15:22:18 jberndt Exp $ Models a Lockheed C-130 Hercules. diff --git a/aircraft/Camel/sopwithCamel1F1jsb.xml b/aircraft/Camel/Camel.xml similarity index 88% rename from aircraft/Camel/sopwithCamel1F1jsb.xml rename to aircraft/Camel/Camel.xml index 6b3c34933b..c766f95c62 100644 --- a/aircraft/Camel/sopwithCamel1F1jsb.xml +++ b/aircraft/Camel/Camel.xml @@ -4,7 +4,7 @@ ************************************************************************ -JSBSim aerodynamic model for a Sopwith Camel 1F1 +JSBSim aerodynamic model for a Sopwith Camel 1F1 Version: 1.6 @@ -12,7 +12,7 @@ Author: Brent Hugh, 6 May 2013 Goal: Create a flight model of the Camel that would incorporate as many of the documented combat flight characteristics of the Camel as possible, and in as realistic a way as possible. -Sources & Acknowledgements: See SopwithCamel-Realistic-JSBSim-Flight-Model-Notes.txt in the Docs subdirectory, other docs in that directory, and the notes below. +Sources & Acknowledgements: See SopwithCamel-Realistic-JSBSim-Flight-Model-Notes.txt in the Docs subdirectory, other docs in that directory, and the notes below. ************************************************************************ @@ -22,7 +22,7 @@ Sources & Acknowledgements: See SopwithCamel-Realistic-JSBSim-Flight-Model-Notes - - + Brent Hugh - 2011-10-29 - Sopwith Camel with Weapons, matches available data for climb, max speed, general handling + 2011-10-29 Version 1.6 + Sopwith Camel with Weapons, matches available data for climb, max speed, general handling @@ -162,42 +162,42 @@ http://www.theaerodrome.com/forum/aircraft/45869-sopwith-camel-myth-6.html --> 212.6948698 - + 26.91 - + + 2.5 + 9.01 - - 2.5 - - + + 19.6 - + 12.38 - - - - + - 5 + 5 13.66 @@ -218,19 +218,19 @@ for the rudder to contribute very much to yaw stability. - + + design feature so remains unchanged. --> 740 182.7 366.9 + 0 0 0 - 0 1210 - 0 - + 30 0 10.62 @@ -458,7 +458,7 @@ for the rudder to contribute very much to yaw stability. 0 - + 30 @@ -573,59 +573,59 @@ for the rudder to contribute very much to yaw stability. 0 - + 0 + + 0 + 0 + 0 + + + 0 + 0 + 0 + -1 - - 0 - 0 - 0 - - - 0 - 0 - 0 - @@ -723,7 +723,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the fcs/aileron-cmd-norm fcs/roll-trim-cmd-norm - + @@ -742,7 +742,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the fcs/left-aileron-pos-rad - + fcs/roll-trim-sum @@ -817,7 +817,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the - fcs/throttle-cmd-norm @@ -833,59 +833,55 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the - - + + - + - + Change_in_drag_due_to_ground_effect - - - aero/h_b-mac-ft - - 0.0000 0.4800 - 0.1000 0.5150 - 0.1500 0.6290 - 0.2000 0.7090 - 0.3000 0.8150 - 0.4000 0.8820 - 0.5000 0.9280 - 0.6000 0.9620 - 0.7000 0.9880 - 0.8000 1.0000 - -
- + + aero/h_b-mac-ft + + 0.0000 0.4800 + 0.1000 0.5150 + 0.1500 0.6290 + 0.2000 0.7090 + 0.3000 0.8150 + 0.4000 0.8820 + 0.5000 0.9280 + 0.6000 0.9620 + 0.7000 0.9880 + 0.8000 1.0000 + +
Change_in_u_due_to_ground_effect - - - aero/h_b-mac-ft - - 0.0000 1.2030 - 0.1000 1.1270 - 0.1500 1.0900 - 0.2000 1.0730 - 0.3000 1.0460 - 0.4000 1.0550 - 0.5000 1.0190 - 0.6000 1.0130 - 0.7000 1.0080 - 0.8000 1.0060 - 0.9000 1.0030 - 1.0000 1.0020 - 1.1000 1.0000 - -
- + + aero/h_b-mac-ft + + 0.0000 1.2030 + 0.1000 1.1270 + 0.1500 1.0900 + 0.2000 1.0730 + 0.3000 1.0460 + 0.4000 1.0550 + 0.5000 1.0190 + 0.6000 1.0130 + 0.7000 1.0080 + 0.8000 1.0060 + 0.9000 1.0030 + 1.0000 1.0020 + 1.1000 1.0000 + +
@@ -895,7 +891,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the propulsion/engine/prop-induced-velocity_fps propulsion/engine/prop-induced-velocity_fps - + q bar including the propulsion induced velocity. @@ -905,9 +901,9 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the atmosphere/rho-slugs_ft3 0.5 - - - + + + Lift due to alpha @@ -920,11 +916,11 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the - + --> + aero/alpha-deg - + - + @@ -1048,23 +1044,23 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the - + Drag at zero lift aero/qbar-psf metrics/Sw-sqft - - + 0.0378 - + Induced drag @@ -1101,7 +1097,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 1.5 - aero/alpha-deg + aero/alpha-deg -90 2.79 -60 1.39 @@ -1135,10 +1131,10 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 90 2.79 -
+ - + Drag due to mach @@ -1147,15 +1143,15 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the velocities/mach - 0 0 - 0.7 0 - 1.1 0.023 - 1.8 0.015 + 0 0 + 0.7 0 + 1.1 0.023 + 1.8 0.015
- + Drag due to sideslip @@ -1166,38 +1162,38 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the - + aero/beta-deg -180 0 -160 .2 - -90 1.2 - -30 0.15 - -10 0.02 + -90 1.2 + -30 0.15 + -10 0.02 0 0 10 0.02 - 30.0 0.15 + 30.0 0.15 90 1.2 160 .2 180 0 - + - + Drag due to Elevator Deflection - + aero/qbar-psf metrics/Sw-sqft @@ -1207,27 +1203,27 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 0.015 - - Drag due to Left Aileron Deflection - + aero/qbar-psf metrics/Sw-sqft fcs/left-aileron-pos-norm - @@ -1236,15 +1232,15 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the Drag due to Right Aileron Deflection - + aero/qbar-psf metrics/Sw-sqft fcs/right-aileron-pos-norm - 0.006 @@ -1252,7 +1248,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the - + Side force due to beta @@ -1266,40 +1262,40 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the -90 0 - -15 0.1370 - 0.0000 0.0000 + -15 0.1370 + 0.0000 0.0000 15 -0.1370 - 90 0 + 90 0 - - - - - - - + + + This reverses the roll moment of the propeller, which we have reversed to compensate for the reversed sense of the gyroscopic moment in JSBSim @@ -1307,9 +1303,9 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the -2 - - - + + + Roll moment due to beta @@ -1320,7 +1316,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the - + aero/beta-rad @@ -1330,27 +1326,27 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 0 0 .2 0.2 1 0 - 3.415 0 + 3.415 0
- - - + + + -0.1 - + - + + + - + - + - + 1.9 - + velocities/p-aero-rad_sec -100 -0.25 -6.28 -0.75 - -3 -0.4 - -2.14 -0.005 + -3 -0.4 + -2.14 -0.005 -1.9 -0.05 - - -1.1 -0.25 + + -1.1 -0.25 -0.01 -0.27 0 -.3 0.01 -0.27 - 1.1 -0.25 - - 1.9 -0.05 + 1.1 -0.25 + + 1.9 -0.05 2.14 -0.005 3 -0.4 6.28 -0.75 100 -0.25 - +
- + - + @@ -1452,14 +1448,14 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 0.35 0 - + aero/alpha-deg @@ -1490,18 +1486,18 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the fcs/left-aileron-pos-rad
velocities/mach - 0 0.10 - 2 0.01 + 0 0.10 + 2 0.01
- velocities/ve-kts @@ -1509,7 +1505,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 0 1 70 0.9 180 0.3 - 400 0 + 400 0
@@ -1550,9 +1546,9 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the #initially it will drop the right wing and then #roll to the left as the stall deepens. #this commented out for Camel. - - Camel: The idea of the r-aero-rad-_sec table is to turn the spin in the - direction the yaw is moving, ie if we're yawing towards the left wing then we drop the left wing. + + Camel: The idea of the r-aero-rad-_sec table is to turn the spin in the + direction the yaw is moving, ie if we're yawing towards the left wing then we drop the left wing. --> roll_moment_due_to_alpha @@ -1571,9 +1567,9 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the -.02 -1 0 0 .02 1 - 3.415 5 + 3.415 5 4 1 - + @@ -1581,7 +1577,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the aero/Re 0 1000000 10000000 20000000 - -180.0 0.0 -0.0005 -0.00025 -0.000025 + -180.0 0.0 -0.0005 -0.00025 -0.000025 -24.0 0.0 -0.0005 -0.00025 -0.000025 -17.8 0.0 -0.00025 -0.000125 -0.0000125 -11.8 0 0 0 0 @@ -1594,10 +1590,10 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the
- - + + - + Pitch moment due to alpha @@ -1605,7 +1601,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the metrics/Sw-sqft metrics/cbarw-ft - + aero/alpha-rad @@ -1615,20 +1611,20 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 0 0 .2 0.2 3.4 2.4 - 3.415 0 + 3.415 0
- - + + - + -0.5 - + Pitch moment due to elevator @@ -1645,42 +1641,42 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 0.0 -1.100 2.0 -0.275 - Camel had a powerful and sensitive elevator - --> - + - 0 -0.5 + 0 -0.5 2 -0.15 - - - + forces/load-factor - + -100 0.01 -10 0.2 -1 1 - 0 1 + 0 1 1 1 10 0.2 100 0.01
- + aero/alpha-deg @@ -1705,27 +1701,27 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the aero/ci2velvelocities/q-aero-rad_sec - - + + -12 - +
velocities/q-aero-rad_sec -32.14 0.2 - -4 0.2 + -4 0.2 -2 0.02 - -1.57 0.2 + -1.57 0.2 -0.7 0.2 - -0.25 0.2 + -0.25 0.2 0 .4 - 0.25 0.2 + 0.25 0.2 0.7 0.2 - 1.57 0.2 + 1.57 0.2 2 0.02 4 0.2 - 32.14 0.2 + 32.14 0.2
@@ -1733,7 +1729,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the - + Pitch moment due to alpha rate @@ -1742,52 +1738,52 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the metrics/cbarw-ft aero/ci2vel - + aero/alphadot-rad_sec - -32.14 -.75 + -32.14 -.75 - -.5 -.5 + -.5 -.5 0 0 - .5 .5 - 32.14 .75 + .5 .5 + 32.14 .75
- - + + -7 - - + We're modeling it here as simply reduced elevator effectiveness starting at + that speed (130 mph = 0.17 mach) - which may not be the best way. --> + Pitch moment due to burble at high speeds 1200 - + --> velocities/ve-kts - + 0 0 - + We're modeling it here as simply bumps up/down in pitch starting at + that speed (130 mph = 0.196 mach= 113 kts). --> 112.96688 0 113.5432416 -0.5 114.1196033 0.5 @@ -2005,11 +2001,11 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the
- - - + - + - - + + Yaw moment due to beta @@ -2032,7 +2028,7 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the aero/beta-rad - + 0.06 @@ -2040,76 +2036,76 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the Yaw moment due to yaw rate - aero/qbar-psf0 + aero/qbar-psf metrics/Sw-sqft metrics/bw-ft aero/bi2vel - - + + - + velocities/r-aero-rad_sec - 1.9 + 1.9 velocities/r-aero-rad_sec - + -32.14 -0.50 -4 -0.5 - -1.25 -0.06 + -1.25 -0.06 -1 -0.003 - -.97 -0.01 - -0.7 -0.03 + -.97 -0.01 + -0.7 -0.03 -0.25 -0.05 - -0.1 -0.40 + -0.1 -0.40 0 -0.5 0.1 -0.40 - 0.25 -0.05 + 0.25 -0.05 0.7 -0.03 - .97 -0.01 + .97 -0.01 1 -0.003 1.25 -0.06 4 -.5 32.14 -0.5 - + + -->
- + - + @@ -2148,12 +2144,12 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the Two data points on the rudder: - We know that some used FULL RUDDER on takeoff, easing it off after becoming airborne. - We know that both R & L turns at max turn rate used FULL RUDDER. - + - The rudder was considered rather small and ineffective; consideration was given to increasing its size - + All these put a rather low bound how on effective the rudder was. - - Cessna 172 has rudder area 7.43 sq ft, 27ft 2 in in length; Whereas Camel is 4.9 sq ft. X 18ft 6 in in length + + Cessna 172 has rudder area 7.43 sq ft, 27ft 2 in in length; Whereas Camel is 4.9 sq ft. X 18ft 6 in in length --> -0.05 @@ -2166,12 +2162,12 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 50 1 105 0.95 180 0.5 - 500 0 + 500 0 --> - + aero/alpha-deg @@ -2181,9 +2177,9 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 14 0.7 90 0.01 -
- - + + + @@ -2199,24 +2195,24 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 180 -.7
- + Adverse yaw @@ -2232,16 +2228,16 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 0 1 70 0.9 180 0.3 - 400 0 + 400 0 - + - - - + - + - - + + Yaw_moment_due_to_alpha-beta @@ -2270,10 +2266,10 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the aero/qbar-psf metrics/Sw-sqft metrics/bw-ft - + - - + +
velocities/p-aero-rad_sec -100 1 @@ -2283,16 +2279,16 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 3.2 0 5 3 100 1 - -
- - - - aero/alpha-deg - aero/beta-deg - aero/Re - - + +
+ + + + aero/alpha-deg + aero/beta-deg + aero/Re + + -50 -5 -2 2.5 6 52 -27 0 0.005 0.003 -0.003 -0.005 0 -15 0 0.005 0.003 -0.003 -0.005 0 @@ -2311,8 +2307,8 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 19.5 0 0.00625 0.013 -0.013 -0.00625 0 21.5 0 0.0075 0.015 -0.015 -0.0075 0 27 0 0.00125 0.005 -0.005 -0.00125 0 - - + + -50 -5 -2 2.5 6 52 -27 0 0.005 0.003 -0.003 -0.005 0 -15 0 0.005 0.003 -0.003 -0.005 0 @@ -2331,8 +2327,8 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 19.5 0 0.04 0.026 -0.026 -0.04 0 21.5 0 0.05 0.03 -0.03 -0.05 0 27 0 0.02 0.01 -0.01 -0.02 0 - - + + -50 -5 -2 2.5 6 52 -27 0 0.005 0.003 -0.003 -0.005 0 -15 0 0.005 0.003 -0.003 -0.005 0 @@ -2351,8 +2347,8 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 19.5 0 0.035 0.025 -0.025 -0.035 0 21.5 0 0.04 0.03 -0.03 -0.04 0 27 0 0.02 0.01 -0.01 -0.02 0 - - + + -50 -5 -2 2.5 6 52 -27 0 0.005 0.003 -0.003 -0.005 0 -15 0 0.005 0.003 -0.003 -0.005 0 @@ -2371,8 +2367,8 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 19.5 0 0.03 0.023 -0.023 -0.03 0 21.5 0 0.05 0.03 -0.03 -0.05 0 27 0 0.02 0.01 -0.01 -0.02 0 - - + + -50 -5 -2 2.5 6 52 -27 0 0.05 0.03 -0.03 -0.05 0 -15 0 0.05 0.03 -0.03 -0.05 0 @@ -2391,8 +2387,8 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 19.5 0 0.03 0.02 -0.02 -0.03 0 21.5 0 0.05 0.03 -0.03 -0.05 0 27 0 0.02 0.01 -0.01 -0.02 0 - - + + -50 -5 -2 2.5 6 52 -27 0 0.05 0.03 -0.03 -0.05 0 -15 0 0.05 0.03 -0.03 -0.05 0 @@ -2411,18 +2407,18 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 19.5 0 0.03 0.02 -0.02 -0.03 0 21.5 0 0.05 0.03 -0.03 -0.05 0 27 0 0.02 0.01 -0.01 -0.02 0 - - -
+ + + - - - + + + Yaw moment due to roll rate @@ -2435,14 +2431,14 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the 0.035 1 - + aero/alpha-deg @@ -2464,8 +2460,8 @@ We're modeling the 130 HP Clerget here, so 30 imp. gal in one tank and 7 in the
- - + + diff --git a/aircraft/Concorde/Concorde.xml b/aircraft/Concorde/Concorde.xml index 2fbd21c5c4..54cc3222b0 100644 --- a/aircraft/Concorde/Concorde.xml +++ b/aircraft/Concorde/Concorde.xml @@ -6,14 +6,13 @@ - 14 August 2010 + + 2010-08-14 1.13 Aerospatiale/British Aerospace Concorde - - GPL (General Public License) - http://www.gnu.org/licenses/gpl.html - Nose gear is longer. Air intake effect, which allows more drag at Mach 1.3-2.0. @@ -84,7 +83,7 @@ author="FAA" title="http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet" date="9 January 1979"/> - + Vlo (landing gear operation) : 270 kt. Vle (landing gear extended) : 270 kt. Vmc (minimum control speed with engine inoperative) @@ -120,8 +119,8 @@ Systems 827 1021 69.43 ........................................................ Totals 211200 lb 211797 lb 56.23 - - + + - http://perso.wanadoo.fr/hsors/FS_Soft/FAQ-FS2K2-Decode_Forum.txt/ Ron Freimuth (for MSFS) : @@ -178,8 +177,8 @@ The moments of inertia had been changed, as an attempt to solve the autopilot roll. - - + + - http://www.concordesst.com/ : Length : overall 202'4", nose to cockpit 24'. @@ -249,8 +248,8 @@ Mas oil pressure : continued operation 5 PSI, takeoff 10 PSI. Max fuel temperature : startup -40 degC, advance above idle -40 degC, continued operation 50 degC. - - + + - http://www.alpa.org/alpa/DesktopModules/ViewDocument.aspx?DocumentID=814 : Mass gross weight : takeoff lasts 45 s, V1 165 kt, VR 195 kt, V2 220. @@ -270,8 +269,8 @@ At Mach 2.04, fuel flow is 45200 lb/h. Heathrow to Kennedy : 3h50. VREF is 162 kt at 275000 lb. - - + + - http://www.concorde-jet.com/ : Nose : O deg visor up supersonic, 0 deg visor down subsonic, @@ -281,8 +280,8 @@ Subsonic cruise : Mach 0.93. Fuel : capacity 95680 kg, 20500 kg/h, 10000 at arrival. Aero reference point steps back of 2 m at Mach 2. - - + + - http://www.club-concorde.org/ : Min runway : takeoff 3600 m, landing : 2200 m.. @@ -290,13 +289,13 @@ Max climbing rate : 1525 m/minute. Takeoff speed : 214 kt. Landing speed : 130 kt, max 162 kt. - + - + Droop nose : 0.53 m. Front gear from nose (without droop nose) : 18.7 m. Main gear from front gear : 18.2 m. @@ -306,13 +305,13 @@ TABLE A corresponds to an effective filling at 95% of tanks (94% for tank 5). It is possible to surpass fuel gauges with 1660 additional liters. - + - + - http://www.aoe.vt.edu/~mason/Mason_f/ConfigAeroSupersonicNotes.pdf/ (Willian H. Mason) : CG (without CG (with Aerodynamic @@ -327,8 +326,8 @@ 2.0 53.5 58.5 62.0 (all positions in % of aerodynamic chord C0, 90.748 feet). - - + + - http://www.titanic.com/story/159/Concorde/ : Runway : 11200 ft takeoff, 7300 ft landing. @@ -337,8 +336,8 @@ Areas (sq ft) : wings (gross) 3856, elevons (total) 344.44, fin (excluding dorsal fin) 365, rudder 112. - - + + - http://www.dft.gov.uk/stellent/groups/dft_avsafety/documents/page/dft_avsafety_029047.hcsp/ (incident report, 13 june 2003) : @@ -353,13 +352,13 @@ transfers fuel from the main transfer tanks to the collector tanks at a rate sufficiently high to ensure that the collectors tanks are always maintained in a near full condition. - + - + - http://www.nasa.gov/centers/dryden/pdf/87877main_H-913.pdf : The lift curve (delta wing) shifts downwards, temporarily at Mach 1.06, and completely near Mach 1.65. @@ -368,13 +367,13 @@ - cruise Mach 3 at 70,000 feet. - wider canards. - wingtips fold from 0 deg at Mach 0.75 to 65.70 deg at Mach 1.5 (transonic 25.30 deg). - + - + Pilot's eyepoint location, in aircraft's own coord system, FROM cg. X, Y, Z, in inches @@ -399,16 +398,16 @@ Htailarm : distance from CG to horizontal tail tip, none (5 ft). Vtailarm : distance from CG to vertical tail tip. - + 3856.0000 83.8300 + 2.86 90.7500 0.0000 5.0000 365.0000 5.0000 - 2.86 736.22 @@ -428,11 +427,11 @@ - + Center of gravity location, empty weight, in aircraft's own structural coord system. X, Y, Z, in inches; X is positive out the tail, Y positive out the right wing. - + 1432000.0000 19034000.0000 @@ -448,7 +447,7 @@ 29500 - + 1299.4 0 -32.5 @@ -457,14 +456,14 @@ - + - => real nose (18.7 m = 736.2 in.), wing (18.7 m + 18.2 m = 1452.8 in.). - gear height determined by 3D model, supposed at scale. - tyre diameter of main gears, at 3/42 of the length between the gears (18.2 m) = 51.2 in. - adjust the front spring, to be horizontal at full load. - + @@ -557,9 +556,7 @@ 1 - - additional contact points, for crash detection when gear retracted. - + @@ -611,15 +608,381 @@ + + + + 736.2000 + 0.0000 + -100.0000 + + + 1 + 0 + 0 + + + + + + + + + + fcs/ground-idle + fcs/intake-subsonic-pos + + + 13 + + + 1821.0000 + -249.4000 + -52.0000 + + + 0.0 + 0.0 + 0.0 + + + + + 14 + + + 1821.0000 + -184.5000 + -52.0000 + + + 0.0 + 0.0 + 0.0 + + + + + 15 + + + 1821.0000 + 184.5000 + -52.0000 + + + 0.0 + 0.0 + 0.0 + + + + + 16 + + + 1821.0000 + 249.4000 + -52.0000 + + + 0.0 + 0.0 + 0.0 + + + + + + + + + + + 1170.0000 + -114.0000 + -12.0000 + + 50 + 9255.0100 + 9255.0100 + 59 + + + + + 1565.0000 + -76.0000 + -12.0000 + + 50 + 10075.1300 + 10075.1300 + 59 + + + + + 1565.0000 + 76.0000 + -12.0000 + + 50 + 10075.1300 + 10075.1300 + 59 + + + + + 1170.0000 + 114.0000 + -12.0000 + + 50 + 9255.0100 + 9255.0100 + 59 + + + + + 1274.0000 + -152.0000 + -12.0000 + + 100 + 15873.2800 + 15873.2800 + + + + + 1463.0000 + -76.0000 + -12.0000 + + 150 + 25544.9600 + 25544.9600 + + + + + 1441.0000 + 152.0000 + -12.0000 + + 100 + 16325.2300 + 16325.2300 + + + + + 1245.0000 + 76.0000 + -12.0000 + + 150 + 28302.9500 + 28302.9500 + + + + + 920.0000 + 0.0000 + -12.0000 + + 150 + 24462.4900 + 24462.4900 + + + + + 1068.0000 + 0.0000 + -12.0000 + + 50 + 26329.8100 + 26329.8100 + + + + + 1977.0000 + 0.0000 + -12.0000 + + 50 + 22961.1400 + 19735.3100 + + + + + 1551.0000 + -380.0000 + -12.0000 + + 100 + 4905.2900 + 4905.2900 + + + + + 1551.0000 + 380.0000 + -12.0000 + + 100 + 4905.2900 + 4905.2900 + + + + + + + 1170.0 + -114.0 + -12.0 + + 46 + 46 + + + + 1565.0 + -76.0 + -12.0 + + 46 + 46 + + + + 1565.0 + 76.0 + -12.0 + + 46 + 46 + + + + 1170.0 + 114.0 + -12.0 + + 46 + 46 + + + systems/NWS/engaged systems/NWS/hydraulics - + default is rudder pedal (flight). - + fcs/rudder-cmd-norm systems/NWS/engaged @@ -632,11 +995,11 @@ - + - default is no wheel steering (flight). - default is hydraulics. - rudder steering at 10 deg. - + fcs/rudder-cmd-norm
systems/NWS/engaged @@ -651,10 +1014,10 @@ - + /sim/model/pushback/target-speed-fps - /sim/model/pushback/position-norm + /sim/model/pushback/position-norm /sim/model/pushback/kp /sim/model/pushback/ki /sim/model/pushback/kd @@ -720,9 +1083,7 @@ fcs/elevator-surface 0.0175 - - => change -0.35/0.30 to -22.5/22.5 deg real. - + -22.5000 22.5000 @@ -758,9 +1119,7 @@ fcs/aileron-surface 0.0175 - - => change 0.35 to 22.5 deg real. - + -22.5000 22.5000 @@ -779,9 +1138,7 @@ -fcs/aileron-surface 0.0175 - - => change 0.35 to 22.5 deg real. - + -22.5000 22.5000 @@ -868,9 +1225,7 @@ fcs/rudder-surface 0.0175 - - => change 0.35 to 29 deg real. - + -29.0000 29.0000 @@ -891,9 +1246,7 @@ fcs/flap-cmd-norm - - changed 30 deg / 3 positions : use flaps as nose. - + 0.0000 @@ -929,9 +1282,7 @@ gear/gear-cmd-norm - - => up in 12 s. - + 0.0000 @@ -944,382 +1295,29 @@ gear/gear-pos-norm - - fcs/speedbrake-cmd-norm - - - 0.0000 - - - - 1.0000 - - - - fcs/speedbrake-pos-norm - - - - - - - - - - after FCS, which creates the intake command variable. - - air intake on (supersonic) by default. - - - - - Engine center at 5/7 of length (2428 in.), -2/5 of fuselage height (130 in.). - - Border aligned with main gear track (304 in. / 2). - => real engine diameter is 1.65 m = (11 - 7.7) / 2. - - Thruster center 3/4 of length (2428 in.), aligned with engines. - - - fcs/ground-idle - fcs/intake-subsonic-pos - - - 13 - - - 1821.0000 - -249.4000 - -52.0000 - - - 0.0 - 0.0 - 0.0 - - - - - 14 - - - 1821.0000 - -184.5000 - -52.0000 - - - 0.0 - 0.0 - 0.0 - - - - - 15 - - - 1821.0000 - 184.5000 - -52.0000 - - - 0.0 - 0.0 - 0.0 - - - - - 16 - - - 1821.0000 - 249.4000 - -52.0000 - - - 0.0 - 0.0 - 0.0 - - - - - - The parameters are gear track, and tank 5 radius; - to check against engine center. - - => Real length is arm, % of MAC (see table above) : real MAC (C0 1089 in.) - starts at 18.7 m (736.2 in.). - => Real half gear track is 7.7 m / 2 (151.6 in.). - - Configuration for take off with maximum weight : - all tanks full, except tank 11 at 86%. - - - - - Tank 1 : - - 1/2 radius of tank 5. - - align 3/4 of gear track. - - => 39.80 % MAC. - - - - 1170.0000 - -114.0000 - -12.0000 - - 50 - 9255.0100 - 9255.0100 - 59 - - - - Tank 2 : - - 1/2 radius of tank 5. - - align 1/2 of gear track. - - near engine center. - - => 76.10 % MAC. - - - 1565.0000 - -76.0000 - -12.0000 - - 50 - 10075.1300 - 10075.1300 - 59 - - - - Tank 3 : - - 1/2 radius of tank 5. - - align 1/2 of gear track. - - near engine center. - - => 76.10 % MAC. - - - 1565.0000 - 76.0000 - -12.0000 - - 50 - 10075.1300 - 10075.1300 - 59 - - - - Tank 4 : - - 1/2 radius of tank 5. - - align 3/4 of gear track. - - => 39.80 % MAC - - - 1170.0000 - 114.0000 - -12.0000 - - 50 - 9255.0100 - 9255.0100 - 59 - - - - Tank 5 : - - center + radius = gear position. - - => 49.40 % MAC. - - - 1274.0000 - -152.0000 - -12.0000 - - 100 - 15873.2800 - 15873.2800 - - - - Tank 6 : - - 3/2 radius of tank 5. - - align 1/2 of gear track. - - before engine center. - - => 66.70 % MAC. - - - 1463.0000 - -76.0000 - -12.0000 - - 150 - 25544.9600 - 25544.9600 - - - - Tank 7 : - - radius of tank 5. - - before engine center. - - => 64.70 % MAC. - - - 1441.0000 - 152.0000 - -12.0000 - - 100 - 16325.2300 - 16325.2300 - - - - Tank 8 : - - 3/2 radius of tank 5. - - align 1/2 of gear track. - - => 46.70 % MAC. - - - 1245.0000 - 76.0000 - -12.0000 - - 150 - 28302.9500 - 28302.9500 - - - - Tank 9 : - - 3/2 radius of tank 5. - - centred on plane axis. - - => 16.90 % MAC - - - 920.0000 - 0.0000 - -12.0000 - - 150 - 24462.4900 - 24462.4900 - - - - Tank 10 : - - 1/2 radius of tank 5. - - centered on plane axis. - - => 30.50 % MAC - - - 1068.0000 - 0.0000 - -12.0000 - - 50 - 26329.8100 - 26329.8100 - - - - Tank 11 : - - 1/2 radius of tank 5. - - centered on plane axis. - - => 113.90 % MAC - - - 1977.0000 - 0.0000 - -12.0000 - - 50 - 22961.1400 - 19735.3100 - - - - Tank 5A : - - radius of tank 5. - - align 5/2 of gear track. - - => 74.80 % MAC - - - 1551.0000 - -380.0000 - -12.0000 - - 100 - 4905.2900 - 4905.2900 - - - - Tank 7A : - - radius of tank 5. - - align 5/2 of gear track. - - => 74.80 % MAC - - - 1551.0000 - 380.0000 - -12.0000 - - 100 - 4905.2900 - 4905.2900 - + + fcs/speedbrake-cmd-norm + + + 0.0000 + + + + 1.0000 + + + + fcs/speedbrake-pos-norm + - - LP valve to emulate cross feed of engine : - - position like the engine tank. - - not empty, to avoid stop at launch. - - can feed 75000 kg/h per engine (takeoff with reheat X 3 speed up) : - 25000 x 3 / 3600 = 46 lb content, if supplied every 1 s from other tanks. - + - - - 1170.0 - -114.0 - -12.0 - - 46 - 46 - - - - 1565.0 - -76.0 - -12.0 - - 46 - 46 - - - - 1565.0 - 76.0 - -12.0 - - 46 - 46 - - - - 1170.0 - 114.0 - -12.0 - - 46 - 46 - - + - - added : => real -5.5 to 16.5 deg. - + -5.5 16.5 @@ -1341,12 +1339,12 @@ - + Change_in_lift_due_to_ground_effect
@@ -1362,14 +1360,14 @@ - + Drag_at_zero_lift @@ -1398,7 +1396,7 @@ 0.042 - + Drag_due_to_mach @@ -1429,9 +1427,7 @@
- - nose drag. - + Drag_due_to_flaps @@ -1450,9 +1446,7 @@ 0.0110 - - 0.0170 replaced by 0.0 : ctrl-B enables speedbrakes. - + Drag_due_to_speedbrakes @@ -1479,10 +1473,10 @@ - + Drag_due_to_Elevator_Deflection @@ -1509,7 +1503,7 @@ - + Lift_due_to_alpha @@ -1539,9 +1533,7 @@ - - changed 1.5 to 0.0 : used flaps as nose. - + Delta_Lift_due_to_flaps @@ -1551,9 +1543,7 @@ 0.0000 - - -0.0800 replaced by 0.0 : ctrl-B enables speedbrakes. - + Delta_Lift_due_to_speedbrake @@ -1730,19 +1720,4 @@ - - - - - 736.2000 - 0.0000 - -100.0000 - - - 1 - 0 - 0 - - - diff --git a/aircraft/DHC6/DHC6.xml b/aircraft/DHC6/DHC6.xml index 924c3fcd61..115614fa5a 100644 --- a/aircraft/DHC6/DHC6.xml +++ b/aircraft/DHC6/DHC6.xml @@ -12,7 +12,7 @@ stall speed: 74.00kts max weight: 12500.00 lb length: 51.75 ft - wing: + wing: span: 65.00 ft area: 422.50 sq-ft mean chord: 6.47 ft @@ -44,7 +44,7 @@ Erik Hofman - 2003-01-01 + 2003-01-01 $Id: DHC6.xml,v 1.24 2016/11/29 17:38:48 ehofman Exp $ DeHavilland DHC-6 @@ -107,7 +107,7 @@ 230 - + 93.6 -18.2 8.4 @@ -222,7 +222,7 @@ - + @@ -690,7 +690,7 @@ - + Yaw_moment_due_to_beta aero/qbar-psf diff --git a/aircraft/F450/F450.xml b/aircraft/F450/F450.xml index 87313dcbb2..5875bf9b25 100644 --- a/aircraft/F450/F450.xml +++ b/aircraft/F450/F450.xml @@ -1,6 +1,7 @@ - + + @@ -9,16 +10,15 @@ - - - + - + + diff --git a/aircraft/F4N/F4N.xml b/aircraft/F4N/F4N.xml index 84a6db4b4d..9dd9ddc1bf 100644 --- a/aircraft/F4N/F4N.xml +++ b/aircraft/F4N/F4N.xml @@ -7,7 +7,7 @@ Aeromatic v 0.9 David Culp - 2007-01-16 + 2007-01-16 0.0 Models a F4N. @@ -167,7 +167,7 @@ - + -260.0 @@ -180,7 +180,7 @@ 0.0 - + -250.0 @@ -193,7 +193,7 @@ 0.0 - + 230.0 @@ -206,9 +206,9 @@ 0.01 - + - + @@ -261,8 +261,8 @@ - - + + diff --git a/aircraft/J246/J246.xml b/aircraft/J246/J246.xml index becf7ba455..8b667b874e 100644 --- a/aircraft/J246/J246.xml +++ b/aircraft/J246/J246.xml @@ -6,10 +6,10 @@ Jon S. Berndt - 2010-01-14 + 2010-01-14 $Revision: 1.6 $ - Rough model of the DIRECT Jupiter-246 + Rough model of the DIRECT Jupiter-246 Lunar Crew Launch Vehicle Configuration. FOR EDUCATIONAL PURPOSES ONLY. This model is not sanctioned by nor is it a work of the DIRECT Launcher @@ -56,7 +56,7 @@ - + 137.22 - + 20.87 0.00 -36.22 @@ -116,38 +116,6 @@ - - - - 0 - - - 1 - - -68.90 - 0.00 - -24.41 - - - 0.00 - 0.00 - 0.00 - - - - - - - 0.00 - 0.00 - 0.00 - - 75.00 - 65.00 - - - - @@ -161,7 +129,6 @@ 0.02 220.00 110.00 - STEERABLE -30.00 NONE 0 @@ -227,6 +194,38 @@ + + + + 0 + + + + -68.90 + 0.00 + -24.41 + + + 0.00 + 0.00 + 0.00 + + 1 + + + + + + 0.00 + 0.00 + 0.00 + + 75.00 + 65.00 + + + + @@ -309,7 +308,7 @@ propulsion/engine/prop-induced-velocity_fps - + q bar including the propulsion induced velocity. @@ -789,8 +788,4 @@ - - - - diff --git a/aircraft/L17/L17.xml b/aircraft/L17/L17.xml index 611807d357..08c46a65a7 100644 --- a/aircraft/L17/L17.xml +++ b/aircraft/L17/L17.xml @@ -6,7 +6,7 @@ Originally from Bruce Jackson (LaRCSim)? - 2000-01-01 + 2000-01-01 $Revision: 1.9 $ Navion general aviation aircraft diff --git a/aircraft/L410/L410.xml b/aircraft/L410/L410.xml index 430970f168..a07f2a8b0d 100644 --- a/aircraft/L410/L410.xml +++ b/aircraft/L410/L410.xml @@ -7,7 +7,7 @@ Jiri Javurek, jjavurek@walterengines.com Jiri Javurek, javky@rozhled.cz Jon Berndt, jsb@hal-pc.org (conversion to v2.0 only) - 2005-11-01 + 2005-11-01 4.0 Czech Republic LET 410 Light Twin @@ -467,7 +467,6 @@ /engines/engine[0]/thruster/torque - -0.0571 /instrumentation/engine/eng-n-koef @@ -475,12 +474,12 @@ 1.0000 1.0000
+ -0.0571 /instrumentation/engine/indicated-pshaft1-perc /engines/engine[1]/thruster/torque - -0.0571 /instrumentation/engine/eng-n-koef @@ -488,6 +487,7 @@ 1.0000 1.0000
+ -0.0571 /instrumentation/engine/indicated-pshaft2-perc @@ -517,7 +517,6 @@ /engines/engine[0]/fuel-flow_pph - 0.4536 /instrumentation/engine/eng-n-koef @@ -525,12 +524,12 @@ 1.0000 1.0000
+ 0.4536 /instrumentation/engine/indicated-fuelfl1-kgph /engines/engine[1]/fuel-flow_pph - 0.4536 /instrumentation/engine/eng-n-koef @@ -538,12 +537,12 @@ 1.0000 1.0000
+ 0.4536 /instrumentation/engine/indicated-fuelfl2-kgph /consumables/fuel/tank/level-lb - 0.4536 /instrumentation/engine/eng-n-koef @@ -551,12 +550,12 @@ 1.0000 1.0000
+ 0.4536 /instrumentation/engine/indicated-fuel1-kg /consumables/fuel/tank[1]/level-lb - 0.4536 /instrumentation/engine/eng-n-koef @@ -564,6 +563,7 @@ 1.0000 1.0000
+ 0.4536 /instrumentation/engine/indicated-fuel2-kg @@ -653,7 +653,6 @@ /controls/gear/brake-parking - 25.0000 /instrumentation/engine/eng-n-koef @@ -661,12 +660,12 @@ 1.0000 1.0000
+ 25.0000 /instrumentation/pressure/indicated-parkingbrake-kp_cm2 /controls/gear/brake-left - 45.0000 /instrumentation/engine/eng-n-koef @@ -674,12 +673,12 @@ 1.0000 1.0000
+ 45.0000 /instrumentation/pressure/indicated-leftbrake-kp_cm2 /controls/gear/brake-right - 45.0000 /instrumentation/engine/eng-n-koef @@ -687,6 +686,7 @@ 1.0000 1.0000
+ 45.0000 /instrumentation/pressure/indicated-rightbrake-kp_cm2 @@ -697,7 +697,6 @@ fcs/temp-oil1-1 - 0.5555 /instrumentation/engine/eng-n-koef @@ -705,6 +704,7 @@ 1.0000 1.0000
+ 0.5555 /instrumentation/temperature/indicated-oil1-degc @@ -715,7 +715,6 @@ fcs/temp-oil2-1 - 0.5555 /instrumentation/engine/eng-n-koef @@ -723,6 +722,7 @@ 1.0000 1.0000
+ 0.5555 /instrumentation/temperature/indicated-oil2-degc diff --git a/aircraft/MD11/MD11.xml b/aircraft/MD11/MD11.xml index b16533943c..4c8135d411 100644 --- a/aircraft/MD11/MD11.xml +++ b/aircraft/MD11/MD11.xml @@ -6,7 +6,7 @@ Unknown - 2003-01-01 + 2003-01-01 $Revision: 1.10 $ McDonnell Douglas MD-11 diff --git a/aircraft/OV10/OV10.xml b/aircraft/OV10/OV10.xml index ecf13695d5..d7ecf5ab6a 100644 --- a/aircraft/OV10/OV10.xml +++ b/aircraft/OV10/OV10.xml @@ -6,7 +6,7 @@ Dave Culp, based on Aero-Matic - 2001-01-01 + 2001-01-01 $Revision: 1.25 $ OV-10 Bronco @@ -139,7 +139,7 @@ - + 200 0 @@ -149,7 +149,7 @@ 1500 - + 200 0 @@ -159,7 +159,7 @@ 1500 - + 200 21.5 @@ -168,7 +168,7 @@ 500 500 - + 200 -21.5 @@ -178,7 +178,7 @@ 500 - + 200 35.8 @@ -187,7 +187,7 @@ 190 190 - + 200 -35.8 @@ -197,7 +197,7 @@ 190 - + 90 0 @@ -206,7 +206,7 @@ 191 191 - + 150 0 @@ -216,7 +216,7 @@ 192 - + 249.6 0 @@ -226,7 +226,7 @@ 200 - + 249.6 0 @@ -547,7 +547,7 @@ Lift_due_to_Elevator_Deflection aero/qbar-psf - fcs/elevator-pos-norm + fcs/elevator-pos-norm 0.2000 diff --git a/aircraft/Pterosaur/Pterosaur.xml b/aircraft/Pterosaur/Pterosaur.xml index e0eb1c57f5..c99fd7eee1 100644 --- a/aircraft/Pterosaur/Pterosaur.xml +++ b/aircraft/Pterosaur/Pterosaur.xml @@ -7,7 +7,7 @@ Aeromatic v 2.9.9 - 27 Oct 2015 + 2015-10-27 $Revision: 1.5 $ Models a Pterosaur. @@ -110,27 +110,6 @@ - - - - 0 - - - 1 - - 36.00 - 0.00 - 0.00 - - - 0.00 - 0.00 - 0.00 - - - - - @@ -251,6 +230,42 @@ + + + + 188.99 + 0.00 + -9.84 + + + 1 + 0 + 0 + + + + + + + + 0 + + + + 36.00 + 0.00 + 0.00 + + + 0.00 + 0.00 + 0.00 + + 1 + + + + @@ -612,20 +627,4 @@ - - - - - 188.99 - 0.00 - -9.84 - - - 1 - 0 - 0 - - - - diff --git a/aircraft/SGS/SGS.xml b/aircraft/SGS/SGS.xml index 1daa388119..ee0dfe1247 100644 --- a/aircraft/SGS/SGS.xml +++ b/aircraft/SGS/SGS.xml @@ -61,7 +61,7 @@ 0 - + 0 0 0 diff --git a/aircraft/Short_S23/Short_S23.xml b/aircraft/Short_S23/Short_S23.xml index f3b1629511..542758a1b2 100644 --- a/aircraft/Short_S23/Short_S23.xml +++ b/aircraft/Short_S23/Short_S23.xml @@ -9,16 +9,16 @@ it under the terms of the GNU General Public License as published by the Free Software Foundation; either version 2 of the License, or (at your option) any later version. - + This program is distributed in the hope that it will be useful, but WITHOUT ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU General Public License for more details. - + You should have received a copy of the GNU General Public License along with this program; if not, write to the Free Software Foundation, Inc., 59 Temple Place, Suite 330, Boston, MA 02111-1307 USA - + --> Anders Gidenstam / DATCOM+ / Aeromatic v 0.9 anders at gidenstam dot org + 2008-11-05 $Id: Short_S23.xml,v 1.48 2018/11/12 19:51:36 anders Exp $ Models a Short S.23 flying boat. - - GPL - http://www.gnu.org/licenses/gpl.html - This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or restricted data. It has been validated only to the extent that it may seem - to "fly right", and possibly to comply to published, publicly known, + to "fly right", and possibly to comply to published, publicly known, performance data (maximum speed, endurance, etc.). Thus, this model is meant for educational and entertainment purposes only. @@ -112,13 +111,13 @@ --> - + 85 @@ -360,9 +359,9 @@ - + The hydrodynamic interactions of the hull are modelled by external forces. - + @@ -414,19 +413,81 @@ + + + + + 8.68 + 0.00 + 0.00 + + + 1.0 + 0.0 + 0.0 + + + + + 8.68 + 0.00 + 0.00 + + + 0.0 + 1.0 + 0.0 + + + + + 8.68 + 0.00 + 0.00 + + + 0.0 + 0.0 + -1.0 + + + + + + 0.0 + 1.0 + 0.0 + + + + + 1.0 + 0.0 + 0.0 + + + + + 0.0 + 0.0 + 1.0 + + + + + - + Propeller location from the plans by [Cassidy:2004:FE]. Fuel tank location and capacity according to [Cassidy:2004:FE]. Mainplane incidence to thrust line: 1 deg 52 min. [Short:RN-3-1-37] Mainplane incidence to hull datum line: 3 deg. [Short:RN-3-1-37] - + 8 - -1 6.30 -7.50 @@ -437,13 +498,13 @@ 0.00 0.00 + -1 9 - -1 6.00 -3.98 @@ -454,13 +515,13 @@ 0.00 0.00 + -1 10 - -1 6.00 3.98 @@ -471,13 +532,13 @@ 0.00 0.00 + -1 11 - -1 6.30 7.50 @@ -488,13 +549,14 @@ 0.00 0.00 + -1 - + @@ -659,7 +721,7 @@ - + The flight control system creates the properties needed by the Aeromatic generated aerodynamic section as well as those needed by the DATCOM+ generated aerodynamic section. @@ -669,7 +731,7 @@ Elevator : +/-18 deg Rudder : +/-22.5 deg - + @@ -809,7 +871,7 @@ 1.0 - + fcs/rudder/cmd-sum-norm @@ -842,69 +904,6 @@ - - - - - 8.68 - 0.00 - 0.00 - - - 1.0 - 0.0 - 0.0 - - - - - 8.68 - 0.00 - 0.00 - - - 0.0 - 1.0 - 0.0 - - - - - 8.68 - 0.00 - 0.00 - - - 0.0 - 0.0 - -1.0 - - - - - - 0.0 - 1.0 - 0.0 - - - - - 1.0 - 0.0 - 0.0 - - - - - 0.0 - 0.0 - 1.0 - - - - - diff --git a/aircraft/Shuttle/Shuttle.xml b/aircraft/Shuttle/Shuttle.xml index f1c96406a5..000f60863d 100644 --- a/aircraft/Shuttle/Shuttle.xml +++ b/aircraft/Shuttle/Shuttle.xml @@ -6,13 +6,12 @@ Jon Berndt - 2001-01-01 + + 2001-01-01 $Revision: 1.2 $ Space Shuttle - - GPL (General Public License) - http://www.gnu.org/licenses/gpl.html - This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or @@ -140,7 +139,6 @@ fcs/pitch-gain-1 - 0.017 fcs/elevator-pos-rad @@ -168,6 +166,7 @@ 0.697 -33.433
+ 0.017 diff --git a/aircraft/Submarine_Scout/Submarine_Scout.xml b/aircraft/Submarine_Scout/Submarine_Scout.xml index 5bb534d55e..36fb8535cf 100644 --- a/aircraft/Submarine_Scout/Submarine_Scout.xml +++ b/aircraft/Submarine_Scout/Submarine_Scout.xml @@ -9,16 +9,16 @@ it under the terms of the GNU General Public License as published by the Free Software Foundation; either version 2 of the License, or (at your option) any later version. - + This program is distributed in the hope that it will be useful, but WITHOUT ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU General Public License for more details. - + You should have received a copy of the GNU General Public License along with this program; if not, write to the Free Software Foundation, Inc., 59 Temple Place, Suite 330, Boston, MA 02111-1307 USA - + --> - - Submarine Scout Zero class airship for JSBSim. - Anders Gidenstam anders at gidenstam dot org + 2007-02-11 2024-01-10 - - GPL v2+ - http://www.gnu.org/licenses/old-licenses/gpl-2.0.html - + Submarine Scout Zero class airship for JSBSim. + This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or @@ -84,17 +82,15 @@ - + NOTE: The center of the bow of the envelope is the origo of the body coordinate system. x/y/z = back/right/up The nose of the car is at (13.70, 0.0, -6.85) m - - According to [Whale:1919:BA] the horizontal and vertical fins of a - S.S. B.E.2C ship were of the same size and measured 16' by 8'6" and + S.S. B.E.2C ship were of the same size and measured 16' by 8'6" and the rudder/elevators measured 4' by 8'6" each. The vertical fin of a S.S. Zero might be longer. @@ -107,9 +103,7 @@ - S.S. Zero 45 mph - Endurance - S.S. Zero: expected 17 hours. Record: 50:55 - - From [AHT, http://www.aht.ndirect.co.uk/airships/Technical%20Spec/SSZ%20Airship.htm]: @@ -130,7 +124,7 @@ Top speed 53 mph Climb 1,200 feet per minute Turning circle 40 seconds minimum, 230 diameter - + 65.0 9.1 @@ -168,17 +162,12 @@ --> - - + According to [VentryKo:1982:AS] the SS Zero class had a useful lift of 1344lbs (~610kg). Considering that the lift of 1 m^3 hydrogen approximately is 1 kg that leaves 1370kg of lift for the structure itself. - - - 733.50 - The empty weight is estimated to consist of: - The weight of the envelope (70000 ft^3), which according to [ADA:1917:Handbook] consists of @@ -193,9 +182,7 @@ Total with 4 planes 2009 lb The car, engine and planes will be added as point masses. - - % Very rough estimation model of the empty weight CG and inertia tensor. % Assume the empty weight of is to 100% a cylindrical shell. @@ -214,7 +201,7 @@ % Very rough estimation model of Ixx, Iyy and Izz relative the CG. Ixx = m * r^2 - + Iyy = 1/2*m * r^2 + 1/12*m*l^2 Izz = 1/2*m * r^2 + 1/12*m*l^2 @@ -222,8 +209,7 @@ Ixy = 0 Ixz = 0 Iyz = 0 - - + 14853.0 124160.0 @@ -231,7 +217,7 @@ 0.0 0.0 0.0 - + 733.50 21.850 0.000 @@ -241,23 +227,23 @@ - + + 100 17.22 0.0 -7.20 - 100 + 0.0 0.0 0.0 -1.0 - 0.0 - + + 0.0 43.7 0.0 -1.0 - 0.0 - + 110.0 - + 17.00 -0.57 -7.35 @@ -308,7 +294,7 @@ 110.0 - + 17.00 0.57 -7.35 @@ -320,7 +306,7 @@ --> 85.0 - + 14.9 0.0 -6.85 @@ -328,7 +314,7 @@ 85.0 - + 16.17 0.0 -6.85 @@ -336,7 +322,7 @@ 85.0 - + 17.22 0.0 -6.85 @@ -346,35 +332,34 @@ - + 601.0 - + 18.60 0.00 -6.10 - + 599.0 - + 16.20 0.00 -7.85 @@ -383,17 +368,248 @@ + + + + + + + + 14.7 + 0.0 + -8.2 + + 1.0 + 2.0 + 0.8 + 50000 + 10000 + 0.0 + NONE + 0 + + + + + 16.6 + 0.0 + -8.2 + + 1.0 + 2.0 + 0.8 + 50000 + 10000 + 0.0 + NONE + 0 + + + + + 18.4 + 0.0 + -8.2 + + 1.0 + 2.0 + 0.8 + 50000 + 10000 + 0.0 + NONE + 0 + + + + + + + 0.0 + 0.0 + 0.0 + + 0.2 + 0.2 + 0.2 + 100000 + 20000 + 0.0 + NONE + 0 + + + + + 43.7 + 0.0 + 0.0 + + 0.2 + 0.2 + 0.2 + 100000 + 20000 + 0.0 + NONE + 0 + + + + + 35.6 + 0.0 + -5.6 + + 0.2 + 0.2 + 0.2 + 100000 + 20000 + 0.0 + NONE + 0 + + + + + 13.7 + 0.0 + -6.85 + + 0.5 + 0.5 + 0.5 + 25000 + 10000 + 0.0 + NONE + 0 + + + + + + + + + + + + 0.0 + 0.0 + 0.0 + + + 1.0 + 0.0 + 0.0 + + + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 1.0 + 0.0 + + + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 1.0 + + + + + + 20.0 + 0.0 + 0.0 + + + 1.0 + 0.0 + 0.0 + + + + + 20.0 + 0.0 + 0.0 + + + 0.0 + 1.0 + 0.0 + + + + + 20.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 1.0 + + + + + + 0.0 + 1.0 + 0.0 + + + + + 1.0 + 0.0 + 0.0 + + + + + 0.0 + 0.0 + 1.0 + + + + + - + NOTE: The cell is placed based on the envelope centroid location as computed by BRLCAD. The automatic valves are implemented using a system. - - + Envelope and gas control for a S.S. B.E.2C according to [Whale:1919:BA]: - Ripping panel at the top of the envelope towards the front - 14'5" by 8' @@ -404,12 +620,11 @@ - 2 gas valves one at the bottom and one at the top of the envelope - Bottom valve automatically opens at 30 - 35mm water pressure. - Top valve is manual only - - + Envelope and ballonet volumes according to [Mowthrope:1998:Battlebags]: - Envelope 70,000 feet^3 - 2 Ballonets 9,800 feet^3 each - + environment/sun-angle-rad @@ -592,144 +807,17 @@ - - - - - - - - 14.7 - 0.0 - -8.2 - - 1.0 - 2.0 - 0.8 - 50000 - 10000 - 0.0 - NONE - 0 - - - - - 16.6 - 0.0 - -8.2 - - 1.0 - 2.0 - 0.8 - 50000 - 10000 - 0.0 - NONE - 0 - - - - - 18.4 - 0.0 - -8.2 - - 1.0 - 2.0 - 0.8 - 50000 - 10000 - 0.0 - NONE - 0 - - - - - - - 0.0 - 0.0 - 0.0 - - 0.2 - 0.2 - 0.2 - 100000 - 20000 - 0.0 - NONE - 0 - - - - - 43.7 - 0.0 - 0.0 - - 0.2 - 0.2 - 0.2 - 100000 - 20000 - 0.0 - NONE - 0 - - - - - 35.6 - 0.0 - -5.6 - - 0.2 - 0.2 - 0.2 - 100000 - 20000 - 0.0 - NONE - 0 - - - - - 13.7 - 0.0 - -6.85 - - 0.5 - 0.5 - 0.5 - 25000 - 10000 - 0.0 - NONE - 0 - - - - - + - - + + Propulsion installation information for S.S. Zero from [Whale:1919:BA]: - Water-cooled Rolls Royce Hawk - 75hp @@ -745,7 +833,7 @@ - Capacity? S.S. B.E.2C: 60 (UK?) gallons. - 2 tanks. Total capacity 120 (UK?) gallons [AHT, www.aht.ndirect.co.uk]. - 2, 4 or 6 tanks for S.S.Zero [Mowthrope:1998:Battlebags] (at 60 gal UK?) - + @@ -796,7 +884,7 @@ --> - + Instrumentation for a S.S. B.E.2C according to [Whale:1919:BA]: Pilot: - watch @@ -819,8 +907,8 @@ Observer/Wireless operator: - radio w. range up to 50-60 miles. - - Lewis machine gun - + - Lewis machine gun + @@ -878,16 +966,16 @@ ==== Flight control system ================================================= --> - + The real aircraft did not have any autopilot. This autopilot is mostly intended for scripted flights in JSBSim/standalone. The autopilot is only minimally tuned. - + - + "Two ballonets are provided, one forward and one aft, the capacity of each being 6,375 cubic feet. The supply of air for filling these is taken from the propeller draught by a slanting aluminium @@ -912,11 +1000,10 @@ "One ripping panel is fitted, which is situated on the top of the envelope towards the nose. It has a length of 14 feet 5 inches and a breadth of about 8 inches." [Whale:1919:BA] on the S.S.B.E. 2C. - - + The slip stream pressure calculation does not take the direction of the relative wind into account. - + @@ -1085,111 +1172,6 @@ - - - - - - - - 0.0 - 0.0 - 0.0 - - - 1.0 - 0.0 - 0.0 - - - - - 0.0 - 0.0 - 0.0 - - - 0.0 - 1.0 - 0.0 - - - - - 0.0 - 0.0 - 0.0 - - - 0.0 - 0.0 - 1.0 - - - - - - 20.0 - 0.0 - 0.0 - - - 1.0 - 0.0 - 0.0 - - - - - 20.0 - 0.0 - 0.0 - - - 0.0 - 1.0 - 0.0 - - - - - 20.0 - 0.0 - 0.0 - - - 0.0 - 0.0 - 1.0 - - - - - - 0.0 - 1.0 - 0.0 - - - - - 1.0 - 0.0 - 0.0 - - - - - 0.0 - 0.0 - 1.0 - - - - - diff --git a/aircraft/T37/T37.xml b/aircraft/T37/T37.xml index 66c396d9ca..768bab5c0b 100644 --- a/aircraft/T37/T37.xml +++ b/aircraft/T37/T37.xml @@ -34,7 +34,7 @@ Erik Hofman - 2001-01-01 + 2001-01-01 $Revision: 1.27 $ T-37 trainer diff --git a/aircraft/X15/X15.xml b/aircraft/X15/X15.xml index 6f0f4a705a..c33ac05bc4 100644 --- a/aircraft/X15/X15.xml +++ b/aircraft/X15/X15.xml @@ -6,7 +6,7 @@ Jon Berndt - 1998-07-01 + 1998-07-01 $Revision: 1.59 $ Models the X-15 hypersonic research aircraft @@ -58,7 +58,7 @@ -590 0 - 14560 + 14560 345 0 @@ -161,13 +161,13 @@ 0 - + - + ap/elevator-cmd fcs/elevator-cmd-norm @@ -193,7 +193,6 @@ fcs/pitch-gain-1 - 0.017 fcs/elevator-pos-rad @@ -221,6 +220,7 @@ 0.697 -33.433
+ 0.017 @@ -331,11 +331,11 @@ fcs/rudder-pos-rad - + - + - + diff --git a/aircraft/XB-70/XB-70.xml b/aircraft/XB-70/XB-70.xml index 8bd5595712..20f35da3c8 100644 --- a/aircraft/XB-70/XB-70.xml +++ b/aircraft/XB-70/XB-70.xml @@ -6,7 +6,7 @@ Jon Berndt/Aeromatic - 2004-01-01 + 2004-01-01 $Revision: 1.9 $ XB-70 bomber flight model approximation Anders Gidenstam anders at gidenstam dot org + 2008-06-10 2023-12-07 JSBSim model of a NT-07 airship. - - GPL v2+ - http://www.gnu.org/licenses/old-licenses/gpl-2.0.html - This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or restricted data. It has been validated only to the extent that it may seem - to "fly right", and possibly to comply to published, publicly known, + to "fly right", and possibly to comply to published, publicly known, performance data (maximum speed, endurance, etc.). This model is distributed in the hope that it will be useful, @@ -90,7 +89,7 @@ - + NOTE: The center of the mooring coupler at bow of the hull is the origo of the body coordinate system. x/y/z = back/right/up @@ -98,9 +97,7 @@ According to [FAA:2008:AS1CE] the datum of the Construction Coordinate System is 5.000 m ahead of the nose of the ship with the horizontal reference line running parallel to the airship center line. - - Some general data from http://www.zeppelinflug.de/seiten/D/zeppnt_techn.htm Note: My 2 view drawing is of a smaller NT-01 (6.5m shorter). It looks like these 6.5 meters were added in the center section @@ -149,7 +146,7 @@ [PV2007_7879.pdf] Propeller diameter 2700mm. - + 1000.0 14.1 @@ -188,7 +185,7 @@ - + Maximum weights according to [FAA:2008:AS1CE] and [EASA:2008:TC_LZ_N07]: Maximum airship equilibrium (normal condition) weight 16,865 lbs (7650 kg) Maximum car (gondola) gross weight 5,390 lbs (2690 kg) @@ -196,8 +193,7 @@ In Flight 1,102 lbs (500 kg) Take off and landing 882 lbs (400 kg) Maximum static lightness -441 lbs (-200 kg) - - + C.G. Range according to [FAA:2008:AS1CE]: Take off and Landing Maximum Forward 39.150 m (1344.5 GE /fdm/jsbsim/inertia/cg-x-in) @@ -207,19 +203,13 @@ Maximum Aft 39.900 m Note: C.G locations in the Construction Coordinate System with reference datum 5.000 m ahead of the nose of the ship. - - 1500 - - The empty weight is estimated to consist of: - The weight of the envelope and frame, guesstimated to 1500 kg. - The frame weighs ~1000kg. The car and engines etc will be added as point masses. - - % Very rough estimation model of the empty weight CG and inertia tensor. % Assume the empty weight of is to 100% a cylindrical shell. @@ -238,7 +228,7 @@ % Very rough estimation model of Ixx, Iyy and Izz relative the CG. Ixx = m * r^2 - + Iyy = 1/2*m * r^2 + 1/12*m*l^2 Izz = 1/2*m * r^2 + 1/12*m*l^2 @@ -247,7 +237,7 @@ Ixz = 0 Iyz = 0 - + 74554.0 740400.0 @@ -255,6 +245,7 @@ 0.0 0.0 0.0 + 1500 37.500 @@ -265,7 +256,7 @@ - + + 2000 37.5 0.0 -8.70 - 2000 + 500 0.0 0.0 -1.0 - 500 - + + 500 75.0 0.0 -1.0 - 500 - - + 85.0 - + 17.38 -0.45 -8.25 @@ -345,7 +335,7 @@ 85.0 - + 17.38 0.45 -8.25 @@ -353,20 +343,20 @@ 500.0 - + 21.0 0.0 -8.5 - 250.0 - + 26.4 -6.6 -3.4 @@ -374,7 +364,7 @@ 250.0 - + 26.4 6.6 -3.4 @@ -382,21 +372,21 @@ 250.0 - + 73.0 0.0 0.0 - 60.0 - + 0.0 0.0 0.0 @@ -405,7 +395,7 @@ 1650.0 - + 22.0 0.0 -8.7 @@ -414,7 +404,7 @@ 180.0 - + 63.2 0.0 5.0 @@ -423,7 +413,7 @@ 180.0 - + 63.2 -4.5 -2.1 @@ -432,7 +422,7 @@ 180.0 - + 63.2 4.5 -2.1 @@ -537,130 +527,143 @@ - - - - - - 0 - - - 25.5 - -8.6 - -3.5 - - - 0.0 - 0.0 - 0.0 - - - - - - 1 - - - 25.5 - 8.6 - -3.5 - - - 0.0 - 0.0 - 0.0 - - - - - - 2 - - - 74.9 - 0.0 - 0.0 - - - 0.0 - 0.0 - 0.0 - - - - - - - - - 73.64 - -1.10 - 0.20 - - - 0.0 - 0.0 - -90.0 - - - + - - - Fuel capacity according to [FAA:2008:AS1CE]: - 110.95 (US)gallons usable at gondola station 29.3 m (LH) - 110.95 (US)gallons usable at gondola station 29.3 m (RH) - 84.57 (US)gallons usable at gondola station 76.6 m (Aft) - The unusable fuel is included in the empty weight. - (NOTE: Account for it here, anyway) - + + + 0.0 + 0.0 + 0.0 + + + 1.0 + 0.0 + 0.0 + + + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 1.0 + 0.0 + + + + + 0.0 + 0.0 + 0.0 + + + 0.0 + 0.0 + 1.0 + + - + - 26.4 - -6.6 - -3.4 + 34.3 + 0.0 + 0.0 - - 275.0 - 250.0 - - + + 1.0 + 0.0 + 0.0 + + + - 26.4 - 6.6 - -3.4 + 34.3 + 0.0 + 0.0 - - 275.0 - 250.0 - - + + 0.0 + 1.0 + 0.0 + + + - 70.0 + 34.3 0.0 0.0 - - 275.0 - 250.0 - + + 0.0 + 0.0 + 1.0 + + - + + + 34.3 + 0.0 + -0.3048 + + + 1.0 + 0.0 + 0.0 + + + + + 34.3 + 0.0 + 0.3048 + + + 1.0 + 0.0 + 0.0 + + + + + + 34.3 + -0.3048 + 0.0 + + + 1.0 + 0.0 + 0.0 + + + + + 34.3 + 0.3048 + 0.0 + + + 1.0 + 0.0 + 0.0 + + + + - + Envelope and ballonet according to [EASA:2008:TC_LZ_N07]: Volume envelope 8,450 m^3 ballonet fwd 600 m^3, or @@ -673,8 +676,7 @@ Height 19.4 m Buoyancy Centre 34.15 m aft of bow. - - + Envelope and ballonet according to [FAA:2008:AS1CE]: Envelope Volume 298,409 ft^3 (8450 m^3) @@ -686,10 +688,9 @@ Volume 56,504 ft^3 aft Lifting Gas Helium, recommended minimum purity 94% - - + NOTE: The ballonets are placed based on a guess. - + environment/sun-angle-rad @@ -708,7 +709,7 @@ 40.50 7.05 7.05 - 600.0 + 600.0 0.0075 0.95 @@ -763,7 +764,7 @@ - + @@ -777,7 +778,7 @@ 15.0 5.00 3.50 - 550.0 + 550.0 0.01 0.8 @@ -830,7 +831,7 @@ 15.0 5.00 3.50 - 550.0 + 550.0 0.01 0.8 @@ -878,6 +879,125 @@ + + + + + + + + 0 + + + 25.5 + -8.6 + -3.5 + + + 0.0 + 0.0 + 0.0 + + + + + + 1 + + + 25.5 + 8.6 + -3.5 + + + 0.0 + 0.0 + 0.0 + + + + + + 2 + + + 74.9 + 0.0 + 0.0 + + + 0.0 + 0.0 + 0.0 + + + + + + + + + 73.64 + -1.10 + 0.20 + + + 0.0 + 0.0 + -90.0 + + + + + + + + + + 26.4 + -6.6 + -3.4 + + + 275.0 + 250.0 + + + + 26.4 + 6.6 + -3.4 + + + 275.0 + 250.0 + + + + 70.0 + 0.0 + 0.0 + + + 275.0 + 250.0 + + + + @@ -968,7 +1088,7 @@ - + Controls according to [FAA:2008:AS1CE]: Control Surface Movements +/- 20 degrees. Vectored Thrust Movements @@ -976,7 +1096,7 @@ Aft Engine 0 (aft horizontal) to 90 degrees down. Avoid sustained operation with forward swivel angles between 43 and 57 degrees during normal operation. - + @@ -986,7 +1106,7 @@ fcs/copilot/pitch-cmd-norm fcs/copilot/yaw-cmd-norm - + - - - - - - 0.0 - 0.0 - 0.0 - - - 1.0 - 0.0 - 0.0 - - - - - 0.0 - 0.0 - 0.0 - - - 0.0 - 1.0 - 0.0 - - - - - 0.0 - 0.0 - 0.0 - - - 0.0 - 0.0 - 1.0 - - - - - - 34.3 - 0.0 - 0.0 - - - 1.0 - 0.0 - 0.0 - - - - - 34.3 - 0.0 - 0.0 - - - 0.0 - 1.0 - 0.0 - - - - - 34.3 - 0.0 - 0.0 - - - 0.0 - 0.0 - 1.0 - - - - - - 34.3 - 0.0 - -0.3048 - - - 1.0 - 0.0 - 0.0 - - - - - 34.3 - 0.0 - 0.3048 - - - 1.0 - 0.0 - 0.0 - - - - - - 34.3 - -0.3048 - 0.0 - - - 1.0 - 0.0 - 0.0 - - - - - 34.3 - 0.3048 - 0.0 - - - 1.0 - 0.0 - 0.0 - - - - - diff --git a/aircraft/ah1s/ah1s.xml b/aircraft/ah1s/ah1s.xml index d179354d32..cb7d244a55 100644 --- a/aircraft/ah1s/ah1s.xml +++ b/aircraft/ah1s/ah1s.xml @@ -1,9 +1,37 @@ - + Thomas Kreitler t.kreitler at web 056 de + + + + 2010-10-07 $Revision: 1.5 $ Models a Bell209/AH1S helicopter. @@ -33,39 +61,8 @@ Estimation of fuselage moments is rather fair. - - GPL - http://www.gnu.org/licenses/gpl.html - - - - - - - + 16.60 10.75 @@ -93,7 +90,7 @@ 0.0 - + 2593.0 14320.0 @@ -107,7 +104,7 @@ 75.0 - + @@ -178,10 +175,10 @@ 2000.0 - + - + 0 1 @@ -195,7 +192,7 @@ 90.0 0.0 - 1 + 1 @@ -213,7 +210,7 @@ 0.0 90.0 - 1 + 1 - aero/coefficient/CD0_fus + aero/coefficient/CD0_fus aero/coefficient/CDa90_fus aero/coefficient/CDb90_fus - @@ -1132,7 +1129,7 @@ - + @@ -1220,5 +1217,5 @@ - + diff --git a/aircraft/ball/ball.xml b/aircraft/ball/ball.xml index c265d73b6e..675ee85f33 100644 --- a/aircraft/ball/ball.xml +++ b/aircraft/ball/ball.xml @@ -6,7 +6,7 @@ Jon Berndt - 2004-06-01 + 2004-06-01 Version 1.0 Test file @@ -63,7 +63,7 @@ 10 - + 0 0 0 @@ -71,7 +71,7 @@ 0 - + 0 -5 0 @@ -101,7 +101,7 @@ fcs/parachute_reef_pos_norm propulsion/rocket_thrust - + @@ -141,7 +141,7 @@ 0 @@ -151,9 +151,9 @@ - + - + @@ -163,7 +163,7 @@ external_reactions/rocket/x - + @@ -185,7 +185,7 @@ - + @@ -204,13 +204,12 @@ ON ON - ON - ON ON ON + ON + ON position/vrp-gc-latitude_deg position/vrp-longitude_deg position/vrp-radius-ft - diff --git a/aircraft/c172p/c172p.xml b/aircraft/c172p/c172p.xml index 05c368b6a0..979e5fc1f0 100644 --- a/aircraft/c172p/c172p.xml +++ b/aircraft/c172p/c172p.xml @@ -6,7 +6,7 @@ Unknown - 2002-01-01 + 2002-01-01 $Id: c172p.xml,v 1.29 2013/10/25 15:32:49 jentron Exp $ Cessna C-172 @@ -63,7 +63,7 @@ 180 - + 36 -14 24 @@ -71,7 +71,7 @@ 0 - + 36 14 24 @@ -79,7 +79,7 @@ 0 - + 70 -14 24 @@ -87,7 +87,7 @@ 0 - + 70 14 24 @@ -95,7 +95,7 @@ 0 - + 95 0 24 @@ -459,7 +459,7 @@ propulsion/engine/prop-induced-velocity_fps propulsion/engine/prop-induced-velocity_fps - + q bar including the propulsion induced velocity. @@ -469,7 +469,7 @@ atmosphere/rho-slugs_ft3 0.5 - + diff --git a/aircraft/c172r/c172r.xml b/aircraft/c172r/c172r.xml index 7855f22c8d..4bfa3e69d2 100644 --- a/aircraft/c172r/c172r.xml +++ b/aircraft/c172r/c172r.xml @@ -6,7 +6,7 @@ Unknown - 2002-01-01 + 2002-01-01 $Id: c172r.xml,v 1.20 2012/12/22 15:22:20 jberndt Exp $ Cessna C-172r @@ -60,7 +60,7 @@ 180 - + 36 -14 24 @@ -68,7 +68,7 @@ 180 - + 36 14 24 @@ -76,7 +76,7 @@ 120 - + 95 0 24 diff --git a/aircraft/c172x/c172x.xml b/aircraft/c172x/c172x.xml index 7beab6db50..8f121c16eb 100644 --- a/aircraft/c172x/c172x.xml +++ b/aircraft/c172x/c172x.xml @@ -8,6 +8,9 @@ + 1999-01-01 + $Revision: 1.91 $ + Models a 1982 Cessna 172P. This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or @@ -19,9 +22,6 @@ This simulation model is not endorsed by the manufacturer. This model is not to be sold. - 1999-01-01 - $Revision: 1.91 $ - Models a 1982 Cessna 172P. - + @@ -271,7 +271,7 @@ 130 - + @@ -284,28 +284,30 @@ - - - -

propulsion/tank[0]/contents-lbs

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- - - + + + + +

propulsion/tank[0]/contents-lbs

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+ + + + + + +

propulsion/tank[1]/contents-lbs

+

propulsion/tank[1]/density-lbs_per_gal

+ + + + @@ -326,14 +328,14 @@ - + guidance/roll-angle-limit guidance/roll-rate-limit - + @@ -380,7 +382,7 @@ ap/aileron_cmd - ap/roll-cmd-norm-output + ap/roll-cmd-norm-output fcs/aileron-cmd-norm fcs/roll-trim-cmd-norm @@ -398,19 +400,19 @@ 15 - + The input to this actuator is in radians. fcs/left-aileron-control 1.57 - 0.005 + 0.005 -0.350 0.260 fcs/left-aileron-pos-rad - + The output from this control is in radians. -fcs/roll-trim-sum @@ -425,20 +427,24 @@ The input to this actuator is in radians. fcs/right-aileron-control 1.57 - 0.005 + 0.005 -0.350 0.260 fcs/right-aileron-pos-rad - - + + fcs/left-aileron-pos-rad -fcs/right-aileron-pos-rad - 0.5 - + + + fcs/delta-aileron-pos + 0.5 + + @@ -1269,7 +1275,6 @@ OFF OFF OFF - + --> - diff --git a/aircraft/c182/c182.xml b/aircraft/c182/c182.xml index 8ec49edc78..57c15acf20 100644 --- a/aircraft/c182/c182.xml +++ b/aircraft/c182/c182.xml @@ -6,7 +6,7 @@ Unknown - 2002-01-01 + 2002-01-01 $Id: c182.xml,v 1.24 2012/12/22 15:22:21 jberndt Exp $ Cessna C-182 @@ -60,7 +60,7 @@ 180 - + 36 -14 24 diff --git a/aircraft/c310/c310.xml b/aircraft/c310/c310.xml index e57249cf99..74bf16c6e6 100644 --- a/aircraft/c310/c310.xml +++ b/aircraft/c310/c310.xml @@ -8,7 +8,10 @@ David Megginson Tony Peden Jon Berndt - 2001-11-24 + + 2001-11-24 $Revision: 1.64 $ Models a C310 light twin. The airplane has a wingspan of 35.98 feet, wing area of 178 square feet, @@ -19,9 +22,6 @@ The horizontal tail is all-movable, with a deflection range of 4 to -14 degrees. Control deflection range for the ailerons is 14 to -18 degrees. Normal rudder deflection range is +/-27 degrees. - This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or @@ -324,7 +324,7 @@ - + ap/roll-pid-kp ap/roll-pid-ki ap/roll-pid-kd @@ -624,7 +624,7 @@ 0.3491 0.1097 0.785 0.707 1.57 1.00 - 3.14 0.01 + 3.14 0.01 @@ -759,7 +759,7 @@ -3.1416 0.0 -2.356 0.97 -1.57 0.0 - -0.785 -0.970 + -0.785 -0.970 -0.3000 -1.0100 -0.2820 -1.1720 -0.2470 -1.0870 diff --git a/aircraft/dr1/dr1.xml b/aircraft/dr1/dr1.xml index 637925453f..1273c2828c 100644 --- a/aircraft/dr1/dr1.xml +++ b/aircraft/dr1/dr1.xml @@ -6,7 +6,7 @@ Ron Jensen, Erik Hofman, Aeromatic v 0.9 - 2008-07-26 + 2008-07-26 $Revison: $ Models a Fokker Dr.1. diff --git a/aircraft/f104/f104.xml b/aircraft/f104/f104.xml index e8572133b0..502f274598 100644 --- a/aircraft/f104/f104.xml +++ b/aircraft/f104/f104.xml @@ -95,7 +95,7 @@ 125 - + 389 -148 -52 @@ -104,7 +104,7 @@ 125 - + 389 148 -52 diff --git a/aircraft/f15/f15.xml b/aircraft/f15/f15.xml index 53022d7b49..97a6339659 100644 --- a/aircraft/f15/f15.xml +++ b/aircraft/f15/f15.xml @@ -6,7 +6,7 @@ Erik Hofman - 2005-01-01 + 2005-01-01 $Revision: 1.31 $ McDonnell Douglas F-15 Eagle @@ -61,7 +61,7 @@ 230 - + -398.45 0 20 diff --git a/aircraft/f16/f16.xml b/aircraft/f16/f16.xml index d860b57d3f..405446e67b 100644 --- a/aircraft/f16/f16.xml +++ b/aircraft/f16/f16.xml @@ -6,22 +6,21 @@ Erik Hofman - 2001-12-28 + + 2001-12-28 $Revision: 1.95 $ - - GPL (General Public License) - http://www.gnu.org/licenses/gpl.html - Models an F-16A Block-32 (Basic US configuration) This model was created using data that is, or has been, publically available by means of technical reports, textbooks, image graphs or - published code. This aircraft description file is in no way related + published code. This aircraft description file is in no way related to the manufacturer of the real aircraft. Neither the name of (any of) the authors nor the names of (any of) the manufacturers may be used to endorse or promote products derived from this file. - + The data is provided ''as is'' and any express or implied warranties, including, but not limitted to the implied warranties of merchantability and fitness for a particular purpose are disclaimed. @@ -74,7 +73,7 @@ 230 - + -336.2 0 0 @@ -405,7 +404,7 @@ fcs/aileron-pos-rad - + @@ -464,7 +463,7 @@ fcs/left-flaperon-norm fcs/right-flaperon-norm - + fcs/flaperon-summer 1.4324 @@ -514,7 +513,7 @@ @@ -616,7 +615,7 @@ 1 - + @@ -801,7 +800,7 @@ - + @@ -876,7 +875,7 @@ - aero/alpha-deg ge 53 + aero/alpha-deg ge 53 velocities/v-fps le 18 @@ -952,7 +951,7 @@ fcs/hook-pos-norm - + @@ -1346,7 +1345,7 @@ aero/alpha-rad -0.1750 0.3645 - -0.0870 0.3678 + -0.0870 0.3678 0.0000 0.3684 0.0870 0.2522 0.1750 0.2710 @@ -1940,4 +1939,3 @@ --> - diff --git a/aircraft/f22/f22.xml b/aircraft/f22/f22.xml index 81d8d0ec84..45b19d448d 100644 --- a/aircraft/f22/f22.xml +++ b/aircraft/f22/f22.xml @@ -6,13 +6,12 @@ Brian Mills + 2009-05-24 $Revision: 1.38 $ Models an F-22A Raptor - - GPL (General Public License) - http://www.gnu.org/licenses/gpl.html - This model was created using data that is, or has been, publically available by means of technical reports, textbooks, image graphs or @@ -21,13 +20,13 @@ Neither the name of (any of) the authors nor the names of (any of) the manufacturers may be used to endorse or promote products derived from this file. - + The data is provided ''as is'' and any express or implied warranties, including, but not limitted to the implied warranties of merchantability and fitness for a particular purpose are disclaimed. - + 840.0 44.49 @@ -66,14 +65,14 @@ 230 - + 148.8 0 20 - + @@ -181,7 +180,7 @@ fcs/aileron-cmd-limiter @@ -242,7 +241,7 @@ 180 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 - 0 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 + 0 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 -90 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 -25 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 -20 0.6 0.85 1 1 1 1 1 1 1 @@ -250,7 +249,7 @@ -10 0.6 0.85 2.5 3.14 3.14 3.14 3.14 2.617 2.1 0 0.6 0.85 2.5 3.66 4 4 3.14 2.617 2.1 10 0.6 0.85 2.5 3.14 3.14 3.14 3.14 2.617 2.1 - 15 0.6 0.85 2.5 2.617 2.617 2.617 2.617 2.617 2.1 + 15 0.6 0.85 2.5 2.617 2.617 2.617 2.617 2.617 2.1 20 0.6 0.85 2.1 2.1 2.1 2.1 2.1 2.1 2.1 25 0.6 0.85 1.5 1.5 1.5 1.5 1.5 1.5 1.5 30 0.6 0.85 1.3 1.3 1.3 1.3 1.3 1.3 1.3 @@ -260,7 +259,7 @@ 180 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 - 0 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 + 0 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6 -90 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 -25 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 -20 0.6 0.85 1 1 1 1 1 1 1 @@ -268,7 +267,7 @@ -10 0.6 0.85 1.5 1.5 2 2.25 2.25 2.25 2 0 0.6 0.85 1.5 2 2.5 2.5 2.75 2.75 2.5 10 0.6 0.85 1.5 1.5 2 2.25 2.25 2.25 2 - 15 0.6 0.85 1.5 2 2 2 2 2 2 + 15 0.6 0.85 1.5 2 2 2 2 2 2 20 0.6 0.85 1 1.25 1.5 2 2 2 2 25 0.6 0.85 1 1.25 1.5 1.5 1.5 1.5 1.5 30 0.6 0.85 1 1 1.3 1.3 1.3 1.3 1.3 @@ -281,7 +280,7 @@ - + fcs/roll-cmd-filter fcs/roll-cmd-limit @@ -298,7 +297,7 @@ -4 4 - + fcs/roll-rate-cmd @@ -313,7 +312,7 @@ -4 4 - + @@ -345,7 +344,7 @@ position/h-sl-ft 0 36000 - 0 -0.436 -0.436 + 0 -0.436 -0.436 0.4 -0.349 -0.349 0.8 -0.1745 -0.1745 1.0 -0.1 -0.1 @@ -391,7 +390,7 @@ fcs/yaw-rate-integrator - + @@ -400,8 +399,8 @@ velocities/mach 0 0.4 0.8 1.0 2.0 - -0.440 0.872 0.7 0.35 0.2 0.2 - -0.436 0 0.7 0.35 0.2 0.2 + -0.440 0.872 0.7 0.35 0.2 0.2 + -0.436 0 0.7 0.35 0.2 0.2 -0.360 0 0.7 0.35 0.2 0.2 -0.349 0 0 0.35 0.2 0.2 -0.180 0 0 0.35 0.2 0.2 @@ -523,11 +522,11 @@ - + -5 5 - + @@ -599,7 +598,7 @@ - + fcs/yaw-cmd-summer -0.2 @@ -665,7 +664,7 @@ -5 5 - + @@ -679,14 +678,14 @@ 1 - + fcs/yaw-reg-scale 0 2.673 - + - + -1 1 @@ -701,7 +700,7 @@ fcs/rudder-pos-norm - + fcs/rudder-act @@ -713,7 +712,7 @@ - + @@ -781,7 +780,7 @@ 0.2 0.8727 0.5236 0.349 0.4 0.8727 0.5236 0.349 0.6 0.8727 0.7 0.349 - 0.8 0.8727 0.7 0.349 + 0.8 0.8727 0.7 0.349 1.0 0.7845 0.7 0.4363 1.2 0.611 0.611 0.4363 1.4 0.611 0.5236 0.349 @@ -797,22 +796,22 @@ fcs/elevator-cmd-limiter -fcs/pitch-cmd-limiter - - + + velocities/machfcs/g-load-norm - 0 0.4 0.8 1.0 1.2 1.4 1.6 1.8 2.0 + 0 0.4 0.8 1.0 1.2 1.4 1.6 1.8 2.0 -3.75 0 0 0 0 0 0 0 0 0 -3.5 1 1 1 1 0 0 0 0 0 -3.25 1 1 1 1 1 1 0 0 0 -3.0 1 1 1 1 1 1 1 1 1 0 1 1 1 1 1 1 1 1 1 7 1 1 1 1 1 1 1 1 1 - 7.25 1 1 1 1 1 -0.1 -0.1 -0.1 -0.1 + 7.25 1 1 1 1 1 -0.1 -0.1 -0.1 -0.1 7.5 1 1 1 1 1 -0.1 -0.1 -0.1 -0.1 7.75 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1 8.0 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1 @@ -823,12 +822,12 @@ 9.25 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1 9.5 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1 9.75 -0.1 -0.1 -0.1 -0.1 -0.1 -0.1 0 0 0 - 10.0 -1 -1 -1 -1 -1 -1 -1 -1 -1 + 10.0 -1 -1 -1 -1 -1 -1 -1 -1 -1
- + fcs/pitch-rate-cmd fcs/pitch-cmd-g-limiter @@ -837,8 +836,8 @@ 0.8727 - - + + @@ -862,7 +861,7 @@ -0.5236 0.8727 - + fcs/q-gear-down-limiter @@ -894,7 +893,7 @@ - + @@ -1274,7 +1273,7 @@ 45000 50000 0.92 0 0 - 0.95 0 1.5 + 0.95 0 1.5 1.00 0 2.5 1.10 0 3.5 1.15 0 4 @@ -1288,7 +1287,7 @@ 1.55 0 0.7 1.60 0 0.65 1.7 0 0.6 - 1.8 0 0.6 + 1.8 0 0.6 1.9 0 0.6 2.0 0 0.6 @@ -1316,7 +1315,7 @@
- + fcs/ss-trim @@ -1350,7 +1349,7 @@ fcs/tvc-pos-norm - + fcs/tvc-pos-norm @@ -1387,13 +1386,13 @@ aero/qbar-psf atmosphere/P-psf - -9.05 + -9.05 1.45 - + fcs/lef-transfer-function 0.01745 @@ -1402,7 +1401,7 @@ 0.6108 - + @@ -1410,7 +1409,7 @@ gear/gear-pos-norm gt 0 - gear/gear-pos-norm == 0 + gear/gear-pos-norm == 0 velocities/mach gt 0.9 @@ -1494,7 +1493,7 @@ fcs/throttle-adjust fcs/tvc-inhibit - fcs/throttle-override + fcs/throttle-override @@ -1554,9 +1553,9 @@ fcs/thrust-norm - + - + @@ -1606,7 +1605,7 @@ fcs/flap-pos-norm - + fcs/flap-controller fcs/speedbrake-flap @@ -1702,7 +1701,7 @@ 1 fcs/speedbrake-rudder - + fcs/speedbrake-pos-norm 1 @@ -1758,7 +1757,7 @@ 0.9000 0.035 1.0000 0.045 1.1000 0.1 - 1.2000 0.105 + 1.2000 0.105 1.3000 0.11 @@ -2007,7 +2006,7 @@ - + Side_force_due_to_beta @@ -2082,7 +2081,7 @@ - + @@ -2202,13 +2201,13 @@ -0.1745 -0.4279 0.0000 0.1346 0.7854 2.00 - 1.3963 1.0726 - + 1.3963 1.0726 + - + Lift_due_to_horizontal_tail_deflection @@ -2219,23 +2218,23 @@ aero/alpha-rad fcs/elevator-pos-rad - - -0.175 -0.428 - -0.087 -0.135 - 0.000 0.135 - 0.087 0.414 - 0.175 0.725 - 0.262 1.041 - 0.349 1.327 - 0.436 1.547 - 0.524 1.737 - 0.611 1.829 - 0.698 1.930 - 0.785 2.000 - 0.8727 1.982 - 1.0472 1.830 - 1.2217 1.548 - 1.3963 1.073 + + -0.175 -0.428 + -0.087 -0.135 + 0.000 0.135 + 0.087 0.414 + 0.175 0.725 + 0.262 1.041 + 0.349 1.327 + 0.436 1.547 + 0.524 1.737 + 0.611 1.829 + 0.698 1.930 + 0.785 2.000 + 0.8727 1.982 + 1.0472 1.830 + 1.2217 1.548 + 1.3963 1.073 @@ -2252,7 +2251,7 @@ - + Roll_moment_due_to_beta @@ -2430,12 +2429,12 @@ - + Pitch_moment_due_to_horizontal_tail_deflection - + aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft @@ -2464,7 +2463,7 @@ 1.5 - + Pitch_moment_due_to_thrust_vectoring @@ -2506,7 +2505,7 @@ aero/alpha-rad velocities/mach - + 0.6000 0.0000 0.8000 0.0974 0.9000 -0.3323 @@ -2527,7 +2526,7 @@ velocities/q-aero-rad_sec
aero/alpha-rad - + -0.1750 -7.2100 -0.0870 -5.4000 0.0000 -5.2300 @@ -2561,7 +2560,7 @@
- + @@ -2666,7 +2665,7 @@ aero/alpha-rad - + -0.1745 -0.048 -0.0873 -0.045 0.0000 -0.045 diff --git a/aircraft/fokker100/fokker100.xml b/aircraft/fokker100/fokker100.xml index ea6a84c9f4..62092107d8 100644 --- a/aircraft/fokker100/fokker100.xml +++ b/aircraft/fokker100/fokker100.xml @@ -93,7 +93,7 @@ 230 - + 122.04 -30.0 66.0 @@ -101,7 +101,7 @@ 230 - + 122.04 30.0 66.0 @@ -109,7 +109,7 @@ 400 - + 218 32.0 66.0 @@ -550,7 +550,7 @@ - + Change_in_drag_due_to_ground_effect @@ -787,7 +787,7 @@ aero/alpha-rad fcs/flap-pos-deg - 0.000 25.0 42.0 + 0.000 25.0 42.0 0.00 0.217 0.837 1.269 0.17 1.109 1.701 2.173 0.21 1.270 1.827 2.308 diff --git a/aircraft/fokker50/fokker50.xml b/aircraft/fokker50/fokker50.xml index eb8b751eac..be432dc827 100644 --- a/aircraft/fokker50/fokker50.xml +++ b/aircraft/fokker50/fokker50.xml @@ -11,7 +11,7 @@ Erik Hofman - 2002-01-01 + 2002-01-01 $Revision: 1.22 $ Fokker 50 commercial turboprop airliner @@ -180,9 +180,9 @@ - --> + 0 - + 497.072 -190.298 @@ -195,9 +195,9 @@ - + 1 - + 497.072 190.298 @@ -229,7 +229,7 @@ 4576 1100 7586.0 - + 790.80 0.00 -29.07 - + @@ -244,14 +244,14 @@ - + guidance/roll-angle-limit guidance/roll-rate-limit - + @@ -260,7 +260,7 @@ - ap/elevator_cmd + ap/elevator_cmd fcs/elevator-cmd-norm fcs/pitch-trim-cmd-norm @@ -504,7 +504,7 @@
- + Change_in_lift_due_to_ground_effect @@ -891,31 +891,30 @@ - aero/alphadot-deg_sec - aero/betadot-deg_sec - velocities/ve-kts - velocities/vc-kts - velocities/mach - aero/beta-deg - aero/alpha-deg - velocities/vtrue-kts - gear/gear-cmd-norm - aero/coefficient/CLalpha - position/h-agl-ft - - - OFF - OFF - OFF - OFF - OFF - OFF - OFF - OFF - OFF - OFF - OFF - OFF - ON + OFF + OFF + OFF + OFF + OFF + OFF + ON + OFF + OFF + OFF + OFF + OFF + OFF + + aero/alphadot-deg_sec + aero/betadot-deg_sec + velocities/ve-kts + velocities/vc-kts + velocities/mach + aero/beta-deg + aero/alpha-deg + velocities/vtrue-kts + gear/gear-cmd-norm + aero/coefficient/CLalpha + position/h-agl-ft - \ No newline at end of file + diff --git a/aircraft/minisgs/minisgs.xml b/aircraft/minisgs/minisgs.xml index 7c923262d3..3a7e211dc3 100644 --- a/aircraft/minisgs/minisgs.xml +++ b/aircraft/minisgs/minisgs.xml @@ -61,7 +61,7 @@ 0 - + 0 0 0 diff --git a/aircraft/mk82/mk82.xml b/aircraft/mk82/mk82.xml index 784c30a827..d1640b6c37 100644 --- a/aircraft/mk82/mk82.xml +++ b/aircraft/mk82/mk82.xml @@ -6,7 +6,7 @@ Unknown - 2001-01-01 + 2001-01-01 $Revision: 1.13 $ Mk-82 @@ -108,19 +108,19 @@
velocities/mach - 0.2000 0.1400 - 0.4000 0.1390 - 0.8000 0.1440 - 0.9000 0.1490 - 0.9500 0.2110 - 0.9800 0.2520 - 1.0000 0.2810 - 1.0200 0.3050 - 1.0500 0.3270 - 1.1000 0.3590 - 1.2000 0.3730 - 1.4000 0.4180 - 1.6000 0.2750 + 0.2000 0.1400 + 0.4000 0.1390 + 0.8000 0.1440 + 0.9000 0.1490 + 0.9500 0.2110 + 0.9800 0.2520 + 1.0000 0.2810 + 1.0200 0.3050 + 1.0500 0.3270 + 1.1000 0.3590 + 1.2000 0.3730 + 1.4000 0.4180 + 1.6000 0.2750
@@ -135,17 +135,17 @@ aero/alpha-rad velocities/mach - 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 - 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 - 0.1750 0.1560 0.1500 0.1070 0.1050 0.1030 0.1020 0.1020 0.1010 0.0990 0.0980 0.1110 0.1600 0.1190 - 0.3490 0.6730 0.5730 0.4500 0.4510 0.4440 0.4430 0.4450 0.4430 0.4450 0.4470 0.6230 0.8560 0.7290 - 0.5240 1.4760 1.3320 1.1990 1.4870 1.5370 1.6100 1.6740 1.7090 1.7460 1.7740 1.9140 2.3430 1.9960 - 0.6980 2.1210 2.0970 2.8570 2.9140 2.9880 3.1060 3.2080 3.2780 3.3460 3.3770 3.5290 4.2260 3.5760 - 0.8730 2.5020 2.7550 4.5630 4.5610 4.6780 4.9210 5.1210 5.2740 5.4180 5.4270 5.5120 6.2080 5.3600 - 1.0470 2.9490 3.3400 6.2000 6.2250 6.3620 6.6550 6.8950 7.0660 7.2180 7.2770 7.4390 8.0250 7.1240 - 1.2220 3.2720 4.0200 7.6130 7.5170 7.6200 8.0050 8.3230 8.5590 8.7720 8.8950 9.0890 9.4860 8.6470 - 1.3960 3.4140 4.4490 8.5890 8.3450 8.5060 8.9530 9.3140 9.5900 9.8810 10.0510 10.1820 10.4330 9.7400 - 1.5530 3.3830 4.5250 8.9570 8.6620 8.8520 9.3210 9.6990 10.0120 10.3210 10.5040 10.5930 10.7020 10.1650 + 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 + 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 + 0.1750 0.1560 0.1500 0.1070 0.1050 0.1030 0.1020 0.1020 0.1010 0.0990 0.0980 0.1110 0.1600 0.1190 + 0.3490 0.6730 0.5730 0.4500 0.4510 0.4440 0.4430 0.4450 0.4430 0.4450 0.4470 0.6230 0.8560 0.7290 + 0.5240 1.4760 1.3320 1.1990 1.4870 1.5370 1.6100 1.6740 1.7090 1.7460 1.7740 1.9140 2.3430 1.9960 + 0.6980 2.1210 2.0970 2.8570 2.9140 2.9880 3.1060 3.2080 3.2780 3.3460 3.3770 3.5290 4.2260 3.5760 + 0.8730 2.5020 2.7550 4.5630 4.5610 4.6780 4.9210 5.1210 5.2740 5.4180 5.4270 5.5120 6.2080 5.3600 + 1.0470 2.9490 3.3400 6.2000 6.2250 6.3620 6.6550 6.8950 7.0660 7.2180 7.2770 7.4390 8.0250 7.1240 + 1.2220 3.2720 4.0200 7.6130 7.5170 7.6200 8.0050 8.3230 8.5590 8.7720 8.8950 9.0890 9.4860 8.6470 + 1.3960 3.4140 4.4490 8.5890 8.3450 8.5060 8.9530 9.3140 9.5900 9.8810 10.0510 10.1820 10.4330 9.7400 + 1.5530 3.3830 4.5250 8.9570 8.6620 8.8520 9.3210 9.6990 10.0120 10.3210 10.5040 10.5930 10.7020 10.1650 @@ -163,17 +163,17 @@ aero/alpha-rad velocities/mach - 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 - 0.0000 -4.5720 -4.7780 -2.8390 -2.7830 -2.7820 -2.7820 -2.8020 -2.7880 -2.7260 -2.6240 -2.1270 -3.7510 -1.8680 - 0.1750 -3.4650 -3.4620 -2.5390 -2.5700 -2.5920 -2.6220 -2.6620 -2.6740 -2.6870 -2.6990 -3.2400 -5.0870 -3.5300 - 0.3490 -4.0330 -3.1760 -2.3060 -2.4370 -2.4890 -2.5570 -2.6210 -2.6490 -2.7270 -2.8330 -4.4100 -6.4600 -5.2600 - 0.5240 -3.7880 -3.2320 -2.9470 -4.1930 -4.5100 -4.8660 -5.1520 -5.3400 -5.5510 -5.7630 -6.4010 -7.7820 -6.4780 - 0.6980 -3.1380 -3.0860 -4.9400 -5.1690 -5.4310 -5.7500 -6.0080 -6.2040 -6.4040 -6.5570 -6.9630 -7.8090 -6.5080 - 0.8730 -2.9750 -3.2000 -5.2580 -5.3000 -5.5000 -5.8190 -6.0770 -6.2740 -6.4640 -6.5150 -6.6640 -7.2910 -6.2470 - 1.0470 -2.7910 -3.0190 -4.9470 -4.9880 -5.1250 -5.3530 -5.5420 -5.6700 -5.7860 -5.8440 -6.0050 -6.4240 -5.6280 - 1.2220 -2.5860 -2.8680 -4.3030 -4.2850 -4.3540 -4.5250 -4.6730 -4.7700 -4.8570 -4.9100 -5.0550 -5.3130 -4.7050 - 1.3960 -2.3880 -2.5850 -3.4120 -3.3890 -3.4360 -3.5320 -3.6200 -3.6690 -3.7200 -3.7470 -3.8640 -4.0610 -3.5780 - 1.5530 -2.2370 -2.2840 -2.4930 -2.5160 -2.5300 -2.5510 -2.5830 -2.5840 -2.5840 -2.5790 -2.7030 -2.9020 -2.4700 + 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 + 0.0000 -4.5720 -4.7780 -2.8390 -2.7830 -2.7820 -2.7820 -2.8020 -2.7880 -2.7260 -2.6240 -2.1270 -3.7510 -1.8680 + 0.1750 -3.4650 -3.4620 -2.5390 -2.5700 -2.5920 -2.6220 -2.6620 -2.6740 -2.6870 -2.6990 -3.2400 -5.0870 -3.5300 + 0.3490 -4.0330 -3.1760 -2.3060 -2.4370 -2.4890 -2.5570 -2.6210 -2.6490 -2.7270 -2.8330 -4.4100 -6.4600 -5.2600 + 0.5240 -3.7880 -3.2320 -2.9470 -4.1930 -4.5100 -4.8660 -5.1520 -5.3400 -5.5510 -5.7630 -6.4010 -7.7820 -6.4780 + 0.6980 -3.1380 -3.0860 -4.9400 -5.1690 -5.4310 -5.7500 -6.0080 -6.2040 -6.4040 -6.5570 -6.9630 -7.8090 -6.5080 + 0.8730 -2.9750 -3.2000 -5.2580 -5.3000 -5.5000 -5.8190 -6.0770 -6.2740 -6.4640 -6.5150 -6.6640 -7.2910 -6.2470 + 1.0470 -2.7910 -3.0190 -4.9470 -4.9880 -5.1250 -5.3530 -5.5420 -5.6700 -5.7860 -5.8440 -6.0050 -6.4240 -5.6280 + 1.2220 -2.5860 -2.8680 -4.3030 -4.2850 -4.3540 -4.5250 -4.6730 -4.7700 -4.8570 -4.9100 -5.0550 -5.3130 -4.7050 + 1.3960 -2.3880 -2.5850 -3.4120 -3.3890 -3.4360 -3.5320 -3.6200 -3.6690 -3.7200 -3.7470 -3.8640 -4.0610 -3.5780 + 1.5530 -2.2370 -2.2840 -2.4930 -2.5160 -2.5300 -2.5510 -2.5830 -2.5840 -2.5840 -2.5790 -2.7030 -2.9020 -2.4700 @@ -191,17 +191,17 @@ aero/alpha-rad velocities/mach - 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 - 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 - 0.1750 0.8920 0.8530 0.6050 0.5960 0.5830 0.5770 0.5780 0.5720 0.5640 0.5510 0.6290 0.0000 0.0000 - 0.3490 1.8910 1.5980 1.2390 1.2460 1.2240 1.2220 1.2310 1.2240 1.2300 1.2340 1.7500 0.9180 0.6530 - 0.5240 2.6800 2.3890 2.1310 2.7150 2.8200 2.9670 3.0950 3.1670 3.2450 3.3060 3.5860 2.3710 1.9530 - 0.6980 2.7130 2.6710 3.8650 3.9660 4.0880 4.2740 4.4320 4.5460 4.6580 4.7190 4.9500 4.0820 3.3810 - 0.8730 2.2200 2.4250 4.1130 4.1320 4.2580 4.4950 4.6880 4.8340 4.9760 5.0020 5.1060 5.0580 4.1590 - 1.0470 1.7770 1.9990 3.7420 3.7690 3.8700 4.0620 4.2180 4.3260 4.4280 4.4760 4.5890 5.2690 4.4650 - 1.2220 1.2300 1.5000 2.8490 2.8190 2.8740 3.0280 3.1540 3.2430 3.3290 3.3840 3.4650 4.7080 4.1210 - 1.3960 0.6120 0.7940 1.5350 1.4940 1.5310 1.6170 1.6850 1.7320 1.7870 1.8230 1.8500 3.5210 3.1700 - 1.5530 0.0470 0.0670 0.1450 0.1400 0.1440 0.1520 0.1590 0.1600 0.1650 0.1690 0.1720 1.8770 1.7320 + 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 + 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 + 0.1750 0.8920 0.8530 0.6050 0.5960 0.5830 0.5770 0.5780 0.5720 0.5640 0.5510 0.6290 0.0000 0.0000 + 0.3490 1.8910 1.5980 1.2390 1.2460 1.2240 1.2220 1.2310 1.2240 1.2300 1.2340 1.7500 0.9180 0.6530 + 0.5240 2.6800 2.3890 2.1310 2.7150 2.8200 2.9670 3.0950 3.1670 3.2450 3.3060 3.5860 2.3710 1.9530 + 0.6980 2.7130 2.6710 3.8650 3.9660 4.0880 4.2740 4.4320 4.5460 4.6580 4.7190 4.9500 4.0820 3.3810 + 0.8730 2.2200 2.4250 4.1130 4.1320 4.2580 4.4950 4.6880 4.8340 4.9760 5.0020 5.1060 5.0580 4.1590 + 1.0470 1.7770 1.9990 3.7420 3.7690 3.8700 4.0620 4.2180 4.3260 4.4280 4.4760 4.5890 5.2690 4.4650 + 1.2220 1.2300 1.5000 2.8490 2.8190 2.8740 3.0280 3.1540 3.2430 3.3290 3.3840 3.4650 4.7080 4.1210 + 1.3960 0.6120 0.7940 1.5350 1.4940 1.5310 1.6170 1.6850 1.7320 1.7870 1.8230 1.8500 3.5210 3.1700 + 1.5530 0.0470 0.0670 0.1450 0.1400 0.1440 0.1520 0.1590 0.1600 0.1650 0.1690 0.1720 1.8770 1.7320 @@ -220,17 +220,17 @@ aero/alpha-rad velocities/mach - 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 - 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 - 0.1750 0.1500 0.0890 0.0050 0.0110 0.0140 0.0160 0.0170 0.0170 0.0180 0.0190 0.0210 0.0370 0.0400 - 0.3490 -0.0550 -0.0550 -0.0370 -0.0290 -0.0270 -0.0240 -0.0220 -0.0200 -0.0160 -0.0100 0.0020 0.0350 0.0420 - 0.5240 -0.0280 -0.0200 0.0110 0.0160 0.0180 0.0190 0.0200 0.0210 0.0220 0.0180 0.0260 0.0500 0.0740 - 0.6980 0.2960 0.2760 0.2300 0.2210 0.2130 0.2090 0.2080 0.2040 0.1980 0.1880 0.1790 0.1560 0.1660 - 0.8730 0.3000 0.2920 0.2750 0.2730 0.2700 0.2690 0.2700 0.2680 0.2660 0.2610 0.2660 0.2690 0.2570 - 1.0470 0.2960 0.2980 0.3070 0.3110 0.3100 0.3110 0.3130 0.3120 0.3110 0.3080 0.3210 0.3390 0.3230 - 1.2220 0.3100 0.3120 0.3240 0.3290 0.3290 0.3300 0.3330 0.3320 0.3300 0.3280 0.3430 0.3650 0.3520 - 1.3960 0.3160 0.3170 0.3300 0.3360 0.3370 0.3380 0.3410 0.3400 0.3390 0.3380 0.3540 0.3780 0.3660 - 1.5530 0.3120 0.3130 0.3270 0.3320 0.3330 0.3340 0.3380 0.3370 0.3360 0.3340 0.3500 0.3740 0.3630 + 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 + 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 0.0000 + 0.1750 0.1500 0.0890 0.0050 0.0110 0.0140 0.0160 0.0170 0.0170 0.0180 0.0190 0.0210 0.0370 0.0400 + 0.3490 -0.0550 -0.0550 -0.0370 -0.0290 -0.0270 -0.0240 -0.0220 -0.0200 -0.0160 -0.0100 0.0020 0.0350 0.0420 + 0.5240 -0.0280 -0.0200 0.0110 0.0160 0.0180 0.0190 0.0200 0.0210 0.0220 0.0180 0.0260 0.0500 0.0740 + 0.6980 0.2960 0.2760 0.2300 0.2210 0.2130 0.2090 0.2080 0.2040 0.1980 0.1880 0.1790 0.1560 0.1660 + 0.8730 0.3000 0.2920 0.2750 0.2730 0.2700 0.2690 0.2700 0.2680 0.2660 0.2610 0.2660 0.2690 0.2570 + 1.0470 0.2960 0.2980 0.3070 0.3110 0.3100 0.3110 0.3130 0.3120 0.3110 0.3080 0.3210 0.3390 0.3230 + 1.2220 0.3100 0.3120 0.3240 0.3290 0.3290 0.3300 0.3330 0.3320 0.3300 0.3280 0.3430 0.3650 0.3520 + 1.3960 0.3160 0.3170 0.3300 0.3360 0.3370 0.3380 0.3410 0.3400 0.3390 0.3380 0.3540 0.3780 0.3660 + 1.5530 0.3120 0.3130 0.3270 0.3320 0.3330 0.3340 0.3380 0.3370 0.3360 0.3340 0.3500 0.3740 0.3630 @@ -249,17 +249,17 @@ aero/alpha-rad velocities/mach - 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 - 0.0000 -1.3720 -1.7830 -1.3250 -0.2610 -0.2670 -0.0530 -0.2280 -0.1110 0.3980 -0.0010 -1.6930 -3.6220 9.0240 - 0.1750 -3.6990 -3.7670 -2.3840 -1.2630 -1.1680 -0.9210 -1.0390 -0.8730 -0.3300 -0.5070 -1.5380 -2.5500 8.7340 - 0.3490 -6.2840 -6.2120 -4.5940 -3.4430 -3.2580 -2.9880 -3.0420 -2.8720 -2.3760 -2.4010 -3.1630 -3.7190 5.6670 - 0.5240 -6.6830 -6.6450 -5.4900 -4.8850 -4.7620 -4.5880 -4.6300 -4.5470 -4.2660 -4.3030 -5.0530 -5.7670 0.4580 - 0.6980 -1.3220 -1.7460 -2.7300 -3.1210 -3.2820 -3.3450 -3.4360 -3.5030 -3.5630 -3.7900 -4.5880 -6.0190 -3.9490 - 0.8730 0.4270 -0.0950 -2.1340 -2.9000 -3.1370 -3.3200 -3.3910 -3.5370 -3.8170 -3.9870 -4.4190 -5.6210 -7.8500 - 1.0470 -3.0160 -3.0290 -4.1670 -4.9730 -5.0950 -5.2690 -5.2630 -5.4040 -5.7450 -5.6550 -5.4110 -5.5440 -11.3800 - 1.2220 -4.2180 -4.1060 -5.2920 -6.2680 -6.3560 -6.5490 -6.5100 -6.6640 -7.0630 -6.8850 -6.3960 -6.1490 -14.1200 - 1.3960 -4.5480 -4.4880 -5.7950 -6.8090 -6.8780 -7.0910 -7.0530 -7.2180 -7.6500 -7.4550 -6.9020 -6.5500 -15.1500 - 1.5530 -4.5480 -4.5460 -5.8850 -6.8540 -6.9290 -7.1500 -7.1170 -7.2760 -7.7250 -7.5390 -6.9700 -6.6060 -15.1600 + 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 + 0.0000 -1.3720 -1.7830 -1.3250 -0.2610 -0.2670 -0.0530 -0.2280 -0.1110 0.3980 -0.0010 -1.6930 -3.6220 9.0240 + 0.1750 -3.6990 -3.7670 -2.3840 -1.2630 -1.1680 -0.9210 -1.0390 -0.8730 -0.3300 -0.5070 -1.5380 -2.5500 8.7340 + 0.3490 -6.2840 -6.2120 -4.5940 -3.4430 -3.2580 -2.9880 -3.0420 -2.8720 -2.3760 -2.4010 -3.1630 -3.7190 5.6670 + 0.5240 -6.6830 -6.6450 -5.4900 -4.8850 -4.7620 -4.5880 -4.6300 -4.5470 -4.2660 -4.3030 -5.0530 -5.7670 0.4580 + 0.6980 -1.3220 -1.7460 -2.7300 -3.1210 -3.2820 -3.3450 -3.4360 -3.5030 -3.5630 -3.7900 -4.5880 -6.0190 -3.9490 + 0.8730 0.4270 -0.0950 -2.1340 -2.9000 -3.1370 -3.3200 -3.3910 -3.5370 -3.8170 -3.9870 -4.4190 -5.6210 -7.8500 + 1.0470 -3.0160 -3.0290 -4.1670 -4.9730 -5.0950 -5.2690 -5.2630 -5.4040 -5.7450 -5.6550 -5.4110 -5.5440 -11.3800 + 1.2220 -4.2180 -4.1060 -5.2920 -6.2680 -6.3560 -6.5490 -6.5100 -6.6640 -7.0630 -6.8850 -6.3960 -6.1490 -14.1200 + 1.3960 -4.5480 -4.4880 -5.7950 -6.8090 -6.8780 -7.0910 -7.0530 -7.2180 -7.6500 -7.4550 -6.9020 -6.5500 -15.1500 + 1.5530 -4.5480 -4.5460 -5.8850 -6.8540 -6.9290 -7.1500 -7.1170 -7.2760 -7.7250 -7.5390 -6.9700 -6.6060 -15.1600 @@ -300,17 +300,17 @@ aero/alpha-rad velocities/mach - 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 - 0.0000 1.3720 1.7830 1.3250 0.2610 0.2670 0.0530 0.2280 0.1110 -0.3980 0.0010 1.6930 3.6220 -9.0240 - 0.1750 3.6990 3.7670 2.3840 1.2630 1.1680 0.9210 1.0390 0.8730 0.3300 0.5070 1.5380 2.5500 -8.7340 - 0.3490 6.2840 6.2120 4.5940 3.4430 3.2580 2.9880 3.0420 2.8720 2.3760 2.4010 3.1630 3.7190 -5.6670 - 0.5240 6.6830 6.6450 5.4900 4.8850 4.7620 4.5880 4.6300 4.5470 4.2660 4.3030 5.0530 5.7670 -0.4580 - 0.6980 1.3220 1.7460 2.7300 3.1210 3.2820 3.3450 3.4360 3.5030 3.5630 3.7900 4.5880 6.0190 3.9490 - 0.8730 -0.4270 0.0950 2.1340 2.9000 3.1370 3.3200 3.3910 3.5370 3.8170 3.9870 4.4190 5.6210 7.8500 - 1.0470 3.0160 3.0290 4.1670 4.9730 5.0950 5.2690 5.2630 5.4040 5.7450 5.6550 5.4110 5.5440 11.3800 - 1.2220 4.2180 4.1060 5.2920 6.2680 6.3560 6.5490 6.5100 6.6640 7.0630 6.8850 6.3960 6.1490 14.1200 - 1.3960 4.5480 4.4880 5.7950 6.8090 6.8780 7.0910 7.0530 7.2180 7.6500 7.4550 6.9020 6.5500 15.1500 - 1.5530 4.5480 4.5460 5.8850 6.8540 6.9290 7.1500 7.1170 7.2760 7.7250 7.5390 6.9700 6.6060 15.1600 + 0.2000 0.4000 0.8000 0.9000 0.9500 0.9800 1.0000 1.0200 1.0500 1.1000 1.2000 1.4000 1.6000 + 0.0000 1.3720 1.7830 1.3250 0.2610 0.2670 0.0530 0.2280 0.1110 -0.3980 0.0010 1.6930 3.6220 -9.0240 + 0.1750 3.6990 3.7670 2.3840 1.2630 1.1680 0.9210 1.0390 0.8730 0.3300 0.5070 1.5380 2.5500 -8.7340 + 0.3490 6.2840 6.2120 4.5940 3.4430 3.2580 2.9880 3.0420 2.8720 2.3760 2.4010 3.1630 3.7190 -5.6670 + 0.5240 6.6830 6.6450 5.4900 4.8850 4.7620 4.5880 4.6300 4.5470 4.2660 4.3030 5.0530 5.7670 -0.4580 + 0.6980 1.3220 1.7460 2.7300 3.1210 3.2820 3.3450 3.4360 3.5030 3.5630 3.7900 4.5880 6.0190 3.9490 + 0.8730 -0.4270 0.0950 2.1340 2.9000 3.1370 3.3200 3.3910 3.5370 3.8170 3.9870 4.4190 5.6210 7.8500 + 1.0470 3.0160 3.0290 4.1670 4.9730 5.0950 5.2690 5.2630 5.4040 5.7450 5.6550 5.4110 5.5440 11.3800 + 1.2220 4.2180 4.1060 5.2920 6.2680 6.3560 6.5490 6.5100 6.6640 7.0630 6.8850 6.3960 6.1490 14.1200 + 1.3960 4.5480 4.4880 5.7950 6.8090 6.8780 7.0910 7.0530 7.2180 7.6500 7.4550 6.9020 6.5500 15.1500 + 1.5530 4.5480 4.5460 5.8850 6.8540 6.9290 7.1500 7.1170 7.2760 7.7250 7.5390 6.9700 6.6060 15.1600 diff --git a/aircraft/p51d/p51d.xml b/aircraft/p51d/p51d.xml index daff6f8895..048612bdd3 100644 --- a/aircraft/p51d/p51d.xml +++ b/aircraft/p51d/p51d.xml @@ -2,7 +2,7 @@ + --> 110 @@ -481,9 +480,9 @@ Hal V. Engel hvengel@astound.net - + - + fcs/elevator-cmd-norm @@ -501,7 +500,7 @@ Hal V. Engel hvengel@astound.net 0.15 fcs/elevator-pos-rad - \ + fcs/elevator-pos-rad @@ -515,9 +514,9 @@ Hal V. Engel hvengel@astound.net fcs/elevator-pos-norm - + - + fcs/aileron-cmd-norm @@ -606,7 +605,7 @@ Hal V. Engel hvengel@astound.net - + fcs/flap-cmd-norm @@ -666,12 +665,12 @@ Hal V. Engel hvengel@astound.net gear/gear-pos-norm - - + + - + --> + - - + + @@ -768,7 +767,7 @@ Hal V. Engel hvengel@astound.net 0.07 aero/alpha-deg - + -90 0.25 -30 0.07 -15 0.03518 @@ -790,22 +789,22 @@ Hal V. Engel hvengel@astound.net
- + Drag_due_to_alpha aero/qbar-psf metrics/Sw-sqft 1.0 @@ -881,7 +880,7 @@ Hal V. Engel hvengel@astound.net - + Induced_drag @@ -891,7 +890,7 @@ Hal V. Engel hvengel@astound.net 0.0125 - + Drag_due_to_mach @@ -911,7 +910,7 @@ Hal V. Engel hvengel@astound.net - + Drag_due_to_flaps @@ -971,7 +970,7 @@ Hal V. Engel hvengel@astound.net - + Lift_due_to_alpha @@ -981,8 +980,8 @@ Hal V. Engel hvengel@astound.net 0.97 aero/alpha-deg @@ -1174,9 +1173,9 @@ Hal V. Engel hvengel@astound.net - - - + + + Pitch_moment_due_to_flaps @@ -1187,7 +1186,7 @@ Hal V. Engel hvengel@astound.net -0.0250 - + Pitch_moment_due_to_gear @@ -1200,19 +1199,19 @@ Hal V. Engel hvengel@astound.net - Pitch_moment_due_to_alpha + Pitch_moment_due_to_alpha aero/qbar-psf metrics/Sw-sqft metrics/cbarw-ft
- aero/alpha-deg - + aero/alpha-deg + -90.0 0.58700 -80.0 0.51700 -70.0 0.44700 @@ -1295,8 +1294,8 @@ Hal V. Engel hvengel@astound.net 80.0 -0.60300 90.0 -0.67300 -
--> - + + @@ -1328,7 +1327,7 @@ Hal V. Engel hvengel@astound.net 0.1 - + Pitch_moment_due_to_elevator @@ -1345,7 +1344,7 @@ Hal V. Engel hvengel@astound.net - + Pitch_moment_due_to_pitch_rate @@ -1357,7 +1356,7 @@ Hal V. Engel hvengel@astound.net -10.0000 - + - + @@ -1501,9 +1500,9 @@ Hal V. Engel hvengel@astound.net aero/qbar-psf metrics/Sw-sqft metrics/bw-ft - +
aero/alpha-deg - + -90.0 0.0 0.0 0.0 5.0 0.0 @@ -1515,6 +1514,5 @@ Hal V. Engel hvengel@astound.net - - + diff --git a/aircraft/pa28/pa28.xml b/aircraft/pa28/pa28.xml index aee23da13e..940ac890ab 100644 --- a/aircraft/pa28/pa28.xml +++ b/aircraft/pa28/pa28.xml @@ -6,7 +6,7 @@ Unknown - 2001-01-01 + 2001-01-01 $Revision: 1.18 $ Piper PA-28 general aviation aircraft @@ -60,7 +60,7 @@ 180 - + 81.6 -9.6 0 diff --git a/aircraft/paraglider/paraglider.xml b/aircraft/paraglider/paraglider.xml index ccaa39dd59..348420c759 100644 --- a/aircraft/paraglider/paraglider.xml +++ b/aircraft/paraglider/paraglider.xml @@ -6,7 +6,7 @@ David Culp, Erik Hofman - 2001-01-01 + 2001-01-01 2.1 (Powered) Paraglider - metrics/Sp-sqft + metrics/Sp-sqft - metrics/bp-ft + metrics/bp-ft @@ -390,7 +390,7 @@ 2 -0.051 4 -0.088 6 -0.107 - 8 -0.133 + 8 -0.133 10 -0.152
diff --git a/aircraft/pc7/pc7.xml b/aircraft/pc7/pc7.xml index 6901d7476e..7c390a48e5 100644 --- a/aircraft/pc7/pc7.xml +++ b/aircraft/pc7/pc7.xml @@ -7,7 +7,7 @@ Aeromatic v 3.3.0 - 06 Jun 2016 + 2016-06-06 $Revision: 1.18 $ Models a PC-7. @@ -31,7 +31,7 @@ stall speed: 75.05kts max weight: 5953.50 lb length: 32.09 ft - wing: + wing: span: 34.12 ft area: 178.68 sq-ft mean chord: 5.25 ft @@ -97,9 +97,9 @@ -9.63 - 2294.52 LBS should bring model up to entered max weight + 1147.26 - + 154.02 0.00 -9.63 @@ -107,47 +107,6 @@ - - - - 0 - - - 1 - - 36.00 - 0.00 - 0.00 - - - 0.00 - 0.00 - 0.00 - - - - - - - 154.02 - 0.00 - -9.63 - - 363.16 - 181.58 - - - - 154.02 - 0.00 - -9.63 - - 363.16 - 181.58 - - - - @@ -224,6 +183,47 @@ + + + + 0 + + + + 36.00 + 0.00 + 0.00 + + + 0.00 + 0.00 + 0.00 + + 1 + + + + + + 154.02 + 0.00 + -9.63 + + 363.16 + 181.58 + + + + 154.02 + 0.00 + -9.63 + + 363.16 + 181.58 + + + + @@ -805,8 +805,4 @@ - - - - diff --git a/aircraft/pogo-jsbsim/pogo-jsbsim.xml b/aircraft/pogo-jsbsim/pogo-jsbsim.xml index 1918cb4cf6..d8c3e24a3d 100644 --- a/aircraft/pogo-jsbsim/pogo-jsbsim.xml +++ b/aircraft/pogo-jsbsim/pogo-jsbsim.xml @@ -6,7 +6,7 @@ Aeromatic v 0.91 - 2009-07-24 + 2009-07-24 $Revision: 1.2 $ Models a Pogo. @@ -722,7 +722,7 @@ 0.35 -0.175 0.7 -0.175 1.57 0.0 - 2.36 0.175 + 2.36 0.175 3.14159 0.0 @@ -823,19 +823,19 @@ - OFF - OFF - OFF - OFF OFF - OFF - ON - ON - ON OFF + ON + OFF OFF ON + ON + OFF + OFF + OFF + ON + OFF OFF - + diff --git a/aircraft/sgs126/sgs126.xml b/aircraft/sgs126/sgs126.xml index 339b143542..d6ba7e87f2 100644 --- a/aircraft/sgs126/sgs126.xml +++ b/aircraft/sgs126/sgs126.xml @@ -6,7 +6,7 @@ Unknown - 2001-01-01 + 2001-01-01 $Revision: 1.13 $ SGS-126 glider diff --git a/aircraft/sgs233/sgs233.xml b/aircraft/sgs233/sgs233.xml index 2ce2087634..ef3dbfcf9c 100644 --- a/aircraft/sgs233/sgs233.xml +++ b/aircraft/sgs233/sgs233.xml @@ -6,7 +6,7 @@ Unknown - 2001-01-01 + 2001-01-01 $Revision: 1.10 $ SGS-233 glider @@ -60,7 +60,7 @@ 180 - + 43 0 4 @@ -68,7 +68,7 @@ 180 - + 85 0 4 diff --git a/aircraft/t6texan2/t6texan2.xml b/aircraft/t6texan2/t6texan2.xml index cfc1039908..3f789d8c90 100644 --- a/aircraft/t6texan2/t6texan2.xml +++ b/aircraft/t6texan2/t6texan2.xml @@ -6,7 +6,7 @@ Aeromatic / David Culp - 2001-01-01 + 2001-01-01 $Revision: 1.14 $ T-6 Texan trainer diff --git a/aircraft/weather-balloon/weather-balloon.xml b/aircraft/weather-balloon/weather-balloon.xml index 96a7da6545..3f05572541 100644 --- a/aircraft/weather-balloon/weather-balloon.xml +++ b/aircraft/weather-balloon/weather-balloon.xml @@ -6,12 +6,12 @@ Ron Jensen - 2011-12-11 - $Revision: 1.3 $ - Models a 6-foot weather balloon. + 2011-12-11 + $Revision: 1.3 $ + Models a 6-foot weather balloon. This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or @@ -22,7 +22,7 @@ This simulation model is not endorsed by the manufacturer. This model is not to be sold. - + References [1] BT-1039.12 http://library.gsfc.nasa.gov/Databases/Balloon/Data/BT1039.12.pdf @@ -83,12 +83,12 @@ 1.15 - + 0.0 0.0 -25.1 - + @@ -105,6 +105,80 @@ + + + + +

aero/qbar-psf

+

metrics/Schute-sqft

+ 1.4 + + + + 0 + 0 + -6.0 + + + + -1 + 0 + 0 + + + + + + + + 0.0 + 0.0 + 0.0 + + 133.0 + 133.0 + 133.0 + 3000.0 + 100000 + 0.02 + + + + + metrics/surface-sqft + 0.02 + + atmosphere/T-R + buoyant_forces/gas-cell/temp-R + + + + + + 0.1714e-8 + 0.05 + metrics/surface-sqft + + + atmosphere/T-R + 4.0 + + + buoyant_forces/gas-cell/temp-R + 4.0 + + + + + + + + @@ -207,17 +281,12 @@ - - - - - Drag. Table from [1] - 1.22 + 1.22 aero/qbar-psf metrics/Sref-sqft @@ -239,10 +308,6 @@ - - - - Roll_moment_due_to_roll_rate_(roll_damping) @@ -253,7 +318,7 @@ velocities/p-aero-rad_sec -0.09 - + Roll_moment_due_to_roll_rate_chute_(roll_damping) @@ -264,7 +329,7 @@ velocities/p-aero-rad_sec -0.4 - + @@ -288,7 +353,7 @@ velocities/q-aero-rad_sec -0.4 - + @@ -301,8 +366,8 @@ velocities/r-aero-rad_sec -0.05 - - + + Yaw_moment_due_to_yaw_rate_chute @@ -312,84 +377,8 @@ velocities/r-aero-rad_sec -0.05 - + - - - - - -

aero/qbar-psf

-

metrics/Schute-sqft

- 1.4 - - - - 0 - 0 - -6.0 - - - - -1 - 0 - 0 - - - - - - - - 0.0 - 0.0 - 0.0 - - 133.0 - 133.0 - 133.0 - 0.02 - 3000.0 - - - - - metrics/surface-sqft - 0.02 - - atmosphere/T-R - buoyant_forces/gas-cell/temp-R - - - - - - 0.1714e-8 - 0.05 - metrics/surface-sqft - - - atmosphere/T-R - 4.0 - - - buoyant_forces/gas-cell/temp-R - 4.0 - - - - - - 100000 - - - - diff --git a/aircraft/wrightFlyer1903/wrightFlyer1903.xml b/aircraft/wrightFlyer1903/wrightFlyer1903.xml index 63ce723471..d54679f22b 100644 --- a/aircraft/wrightFlyer1903/wrightFlyer1903.xml +++ b/aircraft/wrightFlyer1903/wrightFlyer1903.xml @@ -15,46 +15,46 @@ Wright Flyer data: (http://www.wright-brothers.org/Information_Desk/Help_with_Homework/Help_with_Homework_Intro/Flyer_Specifications_11x17.pdf) +++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++ - Dimensions: - 40 ft. 4 in (12.29 m) overall width - 21 ft. (6.40 m) overall length - 8 ft. 1 in. (2.46 m) height over wings + Dimensions: + 40 ft. 4 in (12.29 m) overall width + 21 ft. (6.40 m) overall length + 8 ft. 1 in. (2.46 m) height over wings 8 ft. 4 in. (2.54 m) height over sweep of propellers - 6 ft. 6 in. (1.98 m) wing chord - 1:20 wing camber + 6 ft. 6 in. (1.98 m) wing chord + 1:20 wing camber 3.25 degrees angle of incidence - 10 in. (0.25 m) wing anhedral (droop) + 10 in. (0.25 m) wing anhedral (droop) 6.2 ft (189 cm) (wing) separation 510 sq ft (47.4 sq. m) wing area 48 sq ft (4.6 sq m) double horizontal front rudder 21 sq ft (1.9 sq m) twin movable vertical rear rudders - Weights: - 605 lbs. (274.42 kg) Total weight without pilot - 16 lbs. (7.26 kg) fluids (water, gas, oil) - 145 lbs. (65.77 kg) average weight of pilots + Weights: + 605 lbs. (274.42 kg) Total weight without pilot + 16 lbs. (7.26 kg) fluids (water, gas, oil) + 145 lbs. (65.77 kg) average weight of pilots - Engine: - 4-cycle gasoline, 4 cylinders - 4 in. bore x 4 in. stroke (10.16 cm x 10.16 cm) - Aluminum-copper alloy crankcase - 12 hp at 1020 rpm - 152 lbs (68.95 kg) weight of engine - 18 lbs (8.16 kg) weight of magneto + Engine: + 4-cycle gasoline, 4 cylinders + 4 in. bore x 4 in. stroke (10.16 cm x 10.16 cm) + Aluminum-copper alloy crankcase + 12 hp at 1020 rpm + 152 lbs (68.95 kg) weight of engine + 18 lbs (8.16 kg) weight of magneto - Wing Loading: + Wing Loading: 1.47 lbs. per sq. ft. (7.18 kg per m2) - 62.5 lbs. (28.35 kg) per engine horsepower - - Propellers - Twin contra-rotating propellers - Pusher configuration - Driven by roller chain, 1-in. (2.54 cm) pitch - 8-tooth sprockets on crankshaft - 23-tooth sprockets on propeller shafts - 2-7/8:1 Engine to propeller rpm ratio - 980 rpm approx. engine speed in flight + 62.5 lbs. (28.35 kg) per engine horsepower + + Propellers + Twin contra-rotating propellers + Pusher configuration + Driven by roller chain, 1-in. (2.54 cm) pitch + 8-tooth sprockets on crankshaft + 23-tooth sprockets on propeller shafts + 2-7/8:1 Engine to propeller rpm ratio + 980 rpm approx. engine speed in flight 340 rpm approx. propeller speed in fligh Sources: @@ -77,7 +77,7 @@ Center", AIAA 38th Aerospace Sciences Meeting, AIAA Paper 2000-0512, 2000. - - Various other sources including + - Various other sources including http://www.wrightflyer.org/Papers/papers.html http://www.aae.uiuc.edu/m-selig/uiuc_lsat.html (low Re data) @@ -87,7 +87,7 @@ Flyer - Flyer specifications from the wright-brothers.org website. ************************************************************** - Unless otherwise specified the data is generated by Aeromatic2 + Unless otherwise specified the data is generated by Aeromatic2 ************************************************************** --> @@ -128,18 +128,18 @@ -23.0 - 145 lbs pilot + 145.0 - + -2.3 18.1 -30.9 - + - 152 lbs engine + 18 lbs magneto + 170.0 - + -4.9 -19.5 -27.6 @@ -340,7 +340,6 @@ --> - 1 64.35 0.00 @@ -351,6 +350,7 @@ 0.00 0.00 + 1 @@ -454,7 +454,7 @@ 1.1000 1.0000
- + Change_in_lift_due_to_ground_effect @@ -870,7 +870,7 @@ 0.439 0.13977 0.13977 0.667 0.12808 0.12808 - + -1.0 1.0 -0.989 -0.09 -0.09 -0.629 -0.13938 -0.13938 @@ -1081,9 +1081,4 @@ - - - - - diff --git a/aircraft/x24b/x24b.xml b/aircraft/x24b/x24b.xml index 07b0d91776..4f97f38e39 100644 --- a/aircraft/x24b/x24b.xml +++ b/aircraft/x24b/x24b.xml @@ -6,7 +6,7 @@ Jon Berndt - 2001-01-01 + 2001-01-01 $Revision: 1.14 $ X-24B research aircraft @@ -170,7 +170,6 @@ fcs/pitch-gain-1 - 0.017 fcs/elevator-pos-rad @@ -198,6 +197,7 @@ 0.697 -33.433
+ 0.017 diff --git a/tests/TestActuator.py b/tests/TestActuator.py index f902e8eddf..8b4ac6f938 100644 --- a/tests/TestActuator.py +++ b/tests/TestActuator.py @@ -174,7 +174,7 @@ def prepare_actuator(self): # Remove the hysteresis. We want to make sure we are measuring the # rate_limit and just that. - hysteresis_element = actuator_element.find('hysteresis') + hysteresis_element = actuator_element.find('hysteresis_width') actuator_element.remove(hysteresis_element) input_element = actuator_element.find('input') self.input_prop = actuator_element.attrib['name'].split('-')