zhaohuwei
/
QG4
1
0
Fork 0
Code Issues Pull Requests Projects Releases Wiki Activity
地面站终端 App
You can not select more than 25 topics Topics must start with a letter or number, can include dashes ('-') and can be up to 35 characters long.
8560 Commits
2 Branches
0 Tags
363 MiB
Tree: 21978bb469
Branches Tags
${ item.name }
Create tag ${ searchTerm }
Create branch ${ searchTerm }
from '21978bb469'
${ noResults }
QG4/flightgear/Aircraft/EasyStar/easystar.xml

643 lines
18 KiB
Raw Blame History

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="EasyStar" version="2.0" release="ALPHA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Ron Jensen Aeromatic v 0.91 </author>
<filecreationdate> 2010-03-28 </filecreationdate>
<version>$Revison: $</version>
<description> Models a EasyStar. </description>
</fileheader>
<!--
File: EasyStar.xml
Inputs:
name: EasyStar
type: glider
max weight: 1.5 lb
wing span: 4.5 ft
length: 2.92 ft
wing area: 2.57 sq-ft
gear type: tricycle
retractable?: no
# engines: 1
engine type: electric
engine layout: middle fuselage
yaw damper? no
Outputs:
wing loading: 0.58 lb/sq-ft
CL-alpha: 5.5 per radian
CL-0: 0.25
CL-max: 1.4
CD-0: 0.012
K: 0.023
-->
<metrics>
<wingarea unit="FT2"> 2.570 </wingarea>
<wingspan unit="FT" > 4.500 </wingspan>
<wing_incidence> 0.000 </wing_incidence>
<chord unit="FT" > 0.571 </chord>
<htailarea unit="FT2"> 0.384 </htailarea>
<htailarm unit="FT" > 1.752 </htailarm>
<vtailarea unit="FT2"> 0.257 </vtailarea>
<vtailarm unit="FT" > 1.752 </vtailarm>
<location name="AERORP" unit="M"><!-- 1/4 chord is ~ 0.6 -->
<x> 0.080 </x>
<y> 0.00 </y>
<z> 0.00 </z>
</location>
<location name="EYEPOINT" unit="M">
<x> -0.1 </x>
<y> 0.00 </y>
<z> 0.00 </z>
</location>
<location name="VRP" unit="M">
<x>0</x>
<y>0</y>
<z>0</z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 1.636 </ixx>
<iyy unit="SLUG*FT2"> 0.649 </iyy>
<izz unit="SLUG*FT2"> 2.125 </izz>
<emptywt unit="LBS" > 0.9 </emptywt>
<location name="CG" unit="M">
<x> 0.078</x>
<y> 0.00 </y>
<z> -0.035 </z>
</location>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="MAIN">
<location unit="M">
<x> 0.1 </x>
<y> 0.0 </y>
<z> -0.1 </z>
</location>
<static_friction> 0.800 </static_friction>
<dynamic_friction> 0.500 </dynamic_friction>
<rolling_friction> 0.500 </rolling_friction>
<spring_coeff unit="LBS/FT"> 20.0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 7.0 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 4.0 </damping_coeff_rebound>
<max_steer unit="DEG">0</max_steer>
<brake_group>NONE</brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="NOSE">
<location unit="M">
<x> -0.26 </x>
<y> 0.00 </y>
<z> -0.06 </z>
</location>
<static_friction> 0.800 </static_friction>
<dynamic_friction> 0.500 </dynamic_friction>
<rolling_friction> 0.500 </rolling_friction>
<spring_coeff unit="LBS/FT"> 20.0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 7.0 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 4.0 </damping_coeff_rebound>
<max_steer unit="DEG">0</max_steer>
<brake_group>NONE</brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="TAIL">
<location unit="M">
<x> 0.6 </x>
<y> 0.0 </y>
<z> -0.082 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 20.0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 7.0 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 4.0 </damping_coeff_rebound>
</contact>
<contact type="STRUCTURE" name="LEFT_WING">
<location unit="M">
<x> 0.14 </x>
<y> -0.707 </y>
<z> 0.08 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 20.0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 7.0 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 4.0 </damping_coeff_rebound>
</contact>
<contact type="STRUCTURE" name="RIGHT_WING">
<location unit="M">
<x> 0.14 </x>
<y> 0.707 </y>
<z> -0.08 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 20.0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 7.0 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 4.0 </damping_coeff_rebound>
</contact>
</ground_reactions>
<propulsion>
<engine file="ElecMot400">
<location unit="M">
<x> 0.216 </x>
<y> 0.00 </y>
<z> 0.040 </z>
</location>
<orient unit="DEG">
<pitch>-10.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>0</feed>
<thruster file="prop6x5">
<location unit="M">
<x> 0.238 </x>
<y> 0.00 </y>
<z> 0.042 </z>
</location>
<orient unit="DEG">
<pitch>-10.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<tank type="FUEL" number="0">
<location unit="M">
<x> 0.078 </x>
<y> 0.00 </y>
<z>-0.04 </z>
</location>
<capacity unit="LBS"> .60 </capacity>
<contents unit="LBS"> .60 </contents>
</tank>
</propulsion>
<flight_control name="FCS: EasyStar">
<channel name="Pitch">
<summer name="Pitch Trim Sum">
<input>fcs/elevator-cmd-norm</input>
<input>fcs/pitch-trim-cmd-norm</input>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
</summer>
<aerosurface_scale name="Elevator Control">
<input>fcs/pitch-trim-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="elevator normalization">
<input>fcs/elevator-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/elevator-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Yaw">
<summer name="Rudder Command Sum">
<input>-fcs/aileron-cmd-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min> -1.0 </min>
<max> 1.0 </max>
</clipto>
</summer>
<aerosurface_scale name="Rudder Control">
<input>fcs/rudder-command-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="rudder normalization">
<input>fcs/rudder-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/rudder-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Throttle">
<aerosurface_scale name="throttle cook">
<input>fcs/throttle-cmd-norm</input>
<zero_centered>0</zero_centered>
<domain>
<min> 0.0 </min>
<max> 1.0 </max>
</domain>
<range>
<min> -0.1 </min>
<max> 1.0 </max>
</range>
<output>fcs/throttle-pos-norm</output>
</aerosurface_scale>
</channel>
</flight_control>
<aerodynamics>
<function name="aero/function/ground-effect-factor-lift">
<description>Change in lift due to ground effect factor</description>
<product>
<table>
<independentVar lookup="row">aero/h_b-mac-ft</independentVar>
<tableData>
0.0 1.203
0.1 1.127
0.15 1.090
0.2 1.073
0.3 1.046
0.4 1.055
0.5 1.019
0.6 1.013
0.7 1.008
0.8 1.006
0.9 1.003
1.0 1.002
1.1 1.0
</tableData>
</table>
</product>
</function>
<function name="aero/function/ground-effect-factor-drag">
<description>Change in drag due to ground effect</description>
<product>
<table>
<independentVar lookup="row">aero/h_b-mac-ft</independentVar>
<tableData>
0.0 0.480
0.1 0.515
0.15 0.629
0.2 0.709
0.3 0.815
0.4 0.882
0.5 0.928
0.6 0.962
0.7 0.988
0.8 1.0
0.9 1.0
1.0 1.0
1.1 1.0
</tableData>
</table>
</product>
</function>
<axis name="LIFT">
<function name="aero/coefficient/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/ground-effect-factor-lift</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-3.1416 0.0
-2.62 0.86
-2.36 1.0
-2.09 0.86
-1.57 -0.00
-1.05 -0.86
-0.79 -1.0
-0.52 -0.50
-0.39 -0.38
-0.20 -0.850
0.00 0.250
0.21 1.400
0.60 0.710
0.79 1.0
1.05 0.86
1.57 0.00
2.09 -0.86
2.36 -1.0
2.62 -0.86
3.1416 0.0
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLde">
<description>Lift_due_to_Elevator_Deflection</description>
<product>
<property>aero/function/ground-effect-factor-lift</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<value>0.2</value>
</product>
</function>
</axis>
<axis name="DRAG">
<function name="aero/coefficient/CD0">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/ground-effect-factor-drag</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-3.1416 0.012
-1.57 1.500
-0.21 0.016
0.00 0.012
0.21 0.016
1.57 1.500
3.1416 0.012
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDi">
<description>Induced_drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/cl-squared</property>
<value>0.023</value>
</product>
</function>
<function name="aero/coefficient/CDmach">
<description>Drag_due_to_mach</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.00 0.000
0.7 0.000
1.10 0.023
1.80 0.015
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDbeta">
<description>Drag_due_to_sideslip</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/beta-rad</independentVar>
<tableData>
-3.1416 0.0
-1.57 1.230
-0.26 0.050
0.00 0.000
0.26 0.050
1.57 1.230
3.1416 0.0
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDde">
<description>Drag_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<abs><property>fcs/elevator-pos-rad</property></abs>
<value>0.04</value>
</product>
</function>
</axis>
<axis name="SIDE">
<function name="aero/coefficient/CYb">
<description>Side_force_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/beta-rad</property>
<value>-1</value>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/coefficient/Clb">
<description>Roll_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<value> -0.1</value>
</product>
</function>
<function name="aero/coefficient/Clp">
<description>Roll_moment_due_to_roll_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<value>-0.4</value>
</product>
</function>
<function name="aero/coefficient/Clr">
<description>Roll_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>0.15</value>
</product>
</function>
<function name="aero/coefficient/Cldr">
<description>Roll_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value>0.01</value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/coefficient/Cmalpha">
<description>Pitch_moment_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table >
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-3.14 0.0
-2.62 0.2252
-2.36 0.26
-2.09 0.2252
-1.57 0.0
-1.05 -0.2252
-0.79 -0.26
-0.52 -0.2252
-0.39 -0.1838
-0.26 -0.2588
0.0 0.0
0.26 0.2588
0.39 0.1838
0.52 0.2252
0.79 0.26
1.05 0.2252
1.57 0.0
2.09 -0.2252
2.36 -0.26
2.62 -0.2252
3.14 0.0
</tableData>
</table>
<value>-0.5</value>
</product>
</function>
<function name="aero/coefficient/Cmde">
<description>Pitch_moment_due_to_elevator</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elevator-pos-rad</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.0 -0.800
2.0 -0.200
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmq">
<description>Pitch_moment_due_to_pitch_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>velocities/q-aero-rad_sec</property>
<value>-9</value>
</product>
</function>
<function name="aero/coefficient/Cmadot">
<description>Pitch_moment_due_to_alpha_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>aero/alphadot-rad_sec</property>
<value>-12</value>
</product>
</function>
</axis>
<axis name="YAW">
<function name="aero/coefficient/Cnb">
<description>Yaw_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<value>0.12</value>
</product>
</function>
<function name="aero/coefficient/Cnr">
<description>Yaw_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>-0.15</value>
</product>
</function>
<function name="aero/coefficient/Cndr">
<description>Yaw_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value>-0.03</value>
</product>
</function>
</axis>
</aerodynamics>
</fdm_config>