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737-800-26.xml
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737-800-26.xml
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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="737-800" version="2.0" release="ALPHA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Aeromatic v 3.3.10 </author>
<filecreationdate> 24 Apr 2018 </filecreationdate>
<version>$Revision: 1.80 $</version>
<description> Models a 737-800 with CFM56-7B26 engines. </description>
</fileheader>
<!--
File: 737-800.xml
Inputs:
name: 737-800
type: Multi-engine Passenger Jet Airliner, Transonic Jet Transport
stall speed: unspecified
max weight: 174230.28 lb
length: 129.59 ft
wing:
span: 112.60 ft
area: 1340.97 sq-ft
mean chord: 11.92 ft
aspect ratio: 9.45:1
taper ratio: 0.16:1
incidence: 2.00 degrees
dihedral: 6.00 degrees
sweep: 25.02 degrees
no. engines: 2
engine type: Turbine Engine
engine layout: wings
control type: Conventional with Yaw Damper
gear type: tricycle
steering type: steering
retractable?: yes
Outputs:
wing loading: 129.93 lb/sq-ft
- thickness ratio: 15.00%
payload: 34652.83 lbs
CL-alpha: 5.38 per radian
CL-0: 0.20
CL-max: 1.20
CD-0: 0.02
K: 0.04
Mcrit: 0.79
min. turn radius -nan ft
max. turn rate: -nan deg/s
-->
<metrics>
<wingarea unit="FT2"> 1340.97 </wingarea>
<wingspan unit="FT" > 112.60 </wingspan>
<wing_incidence unit="DEG"> 2.00 </wing_incidence>
<chord unit="FT" > 11.92 </chord>
<htailarea unit="FT2"> 352.84 </htailarea>
<htailarm unit="FT" > 58.06 </htailarm>
<vtailarea unit="FT2"> 268.19 </vtailarea>
<vtailarm unit="FT" > 53.57 </vtailarm>
<location name="AERORP" unit="IN">
<x> 734 </x> <!-- 25% MAC -->
<y> 0 </y>
<z>-6.71 </z> <!-- BWL 201.39 -->
</location>
<location name="EYEPOINT" unit="IN">
<x> 98 </x>
<y> -20 </y>
<z> 56.18 </z>
</location>
<location name="VRP" unit="M">
<x> 19.8099 </x>
<y> 0 </y>
<z> 0.0785 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 51558484.00 </ixx>
<iyy unit="SLUG*FT2"> 248060032.00 </iyy>
<izz unit="SLUG*FT2"> 299850240.00 </izz>
<ixy unit="SLUG*FT2"> 0 </ixy>
<ixz unit="SLUG*FT2"> 110000 </ixz>
<iyz unit="SLUG*FT2"> 0 </iyz>
<emptywt unit="LBS" > 91315.66 </emptywt>
<location name="CG" unit="IN">
<x> 729.56 </x> <!-- based on real info about EI-RUA aircraft. 2 pilots and 5 cabin crew included -->
<y> 0 </y>
<z> 0 </z>
</location>
<pointmass name="Cabin Zone 0A"> <!-- Business class (8 pax max) Row 1-2 -->
<weight unit="LBS"> 1324 </weight>
<location name="POINTMASS" unit="IN">
<x> 301.5 </x>
<y> 0 </y>
<z> 27.5 </z>
</location>
</pointmass>
<pointmass name="Cabin Zone 0B"> <!-- Tourist class (54 pax max) Row 10-19 -->
<weight unit="LBS"> 1324 </weight>
<location name="POINTMASS" unit="IN">
<x> 541 </x>
<y> 0 </y>
<z> 27.5 </z>
</location>
</pointmass>
<pointmass name="Cabin Zone 0C"> <!-- Economy class (96 pax max) Row 20-36 -->
<weight unit="LBS"> 1324 </weight>
<location name="POINTMASS" unit="IN">
<x> 874 </x>
<y> 0 </y>
<z> 27.5 </z>
</location>
</pointmass>
<pointmass name="Cargo compartment 1A"> <!-- max 553 kg/1218 lbs -->
<weight unit="LBS"> 500 </weight>
<location name="POINTMASS" unit="IN">
<x> 284 </x>
<y> 0 </y>
<z> -30 </z>
</location>
</pointmass>
<pointmass name="Cargo compartment 1B"> <!-- max 336 kg/741 lbs -->
<weight unit="LBS"> 200 </weight>
<location name="POINTMASS" unit="IN">
<x> 334 </x>
<y> 0 </y>
<z> -30 </z>
</location>
</pointmass>
<pointmass name="Cargo compartment 2"> <!-- max 2670 kg/5887 lbs -->
<weight unit="LBS"> 2500 </weight>
<location name="POINTMASS" unit="IN">
<x> 464 </x>
<y> 0 </y>
<z> -30 </z>
</location>
</pointmass>
<pointmass name="Cargo compartment 3"> <!-- max 4086 kg/9008 lbs -->
<weight unit="LBS"> 4000 </weight>
<location name="POINTMASS" unit="IN">
<x> 932.5 </x>
<y> 0 </y>
<z> -30 </z>
</location>
</pointmass>
<pointmass name="Cargo compartment 4A"> <!-- max 362 kg/798 lbs -->
<weight unit="LBS"> 400 </weight>
<location name="POINTMASS" unit="IN">
<x> 1097.5 </x>
<y> 0 </y>
<z> -30 </z>
</location>
</pointmass>
<pointmass name="Cargo compartment 4B"> <!-- max 402 kg/886 lbs -->
<weight unit="LBS"> 200 </weight>
<location name="POINTMASS" unit="IN">
<x> 1175.5 </x>
<y> 0 </y>
<z> -30 </z>
</location>
</pointmass>
</mass_balance>
<propulsion>
<engine file="CFM56-7B26">
<location unit="IN">
<x> 715.6 </x> <!-- value from simulator data -->
<y> -193.68 </y> <!-- value from simulator data -->
<z> -52.38 </z> <!-- BWL 155.72 -->
</location>
<orient unit="DEG">
<roll> 0 </roll>
<pitch> 0 </pitch>
<yaw> 1 </yaw>
</orient>
<feed>3</feed>
<thruster file="direct">
<location unit="IN">
<x> 715.6 </x> <!-- value from simulator data -->
<y> -193.68 </y> <!-- value from simulator data -->
<z> -52.38 </z> <!-- BWL 155.72 -->
</location>
<orient unit="DEG">
<roll> 0 </roll>
<pitch> 0 </pitch>
<yaw> 1 </yaw>
</orient>
</thruster>
</engine>
<engine file="CFM56-7B26">
<location unit="IN">
<x> 715.6 </x> <!-- value from simulator data -->
<y> 193.68 </y> <!-- value from simulator data -->
<z> -52.38 </z> <!-- BWL 155.72 -->
</location>
<orient unit="DEG">
<roll> 0 </roll>
<pitch> 0 </pitch>
<yaw> -1 </yaw>
</orient>
<feed>4</feed>
<thruster file="direct">
<location unit="IN">
<x> 715.6 </x> <!-- value from simulator data -->
<y> 193.68 </y> <!-- value from simulator data -->
<z> -52.38 </z> <!-- BWL 155.72 -->
</location>
<orient unit="DEG">
<roll> 0 </roll>
<pitch> 0 </pitch>
<yaw> -1 </yaw>
</orient>
</thruster>
</engine>
<tank type="FUEL"><!-- Left wing tank -->
<location unit="IN">
<x> 767.01 </x> <!-- based on trimsheet calculation. Correct value -->
<y> -350 </y>
<z> 26.58 </z>
</location>
<drain_location unit="IN">
<x> 703.09</x> <!-- based on trimsheet calculation. Correct value -->
<y> -200 </y>
<z> 10.91 </z>
</drain_location>
<capacity unit="LBS"> 8630 </capacity>
<contents unit="LBS"> 8630 </contents>
<temperature> 59.0 </temperature> <!-- Fuel temp in degrees F -->
</tank>
<tank type="FUEL"><!-- Right wing tank -->
<location unit="IN">
<x> 767.01 </x> <!-- based on trimsheet calculation. Correct value -->
<y> 350 </y>
<z> 26.58 </z>
</location>
<drain_location unit="IN">
<x> 703.09</x> <!-- based on trimsheet calculation. Correct value -->
<y> 200 </y>
<z> 10.91 </z>
</drain_location>
<capacity unit="LBS"> 8630 </capacity>
<contents unit="LBS"> 8630 </contents>
<temperature> 59.0 </temperature> <!-- Fuel temp in degrees F -->
</tank>
<tank type="FUEL"><!-- Center tank -->
<location unit="IN">
<x> 675.41 </x> <!-- based on trimsheet calculation. Correct value -->
<y> 0 </y>
<z> -19.54 </z>
</location>
<drain_location unit="IN">
<x> 675.46 </x> <!-- based on trimsheet calculation. Correct value -->
<y> 0 </y>
<z> -97.4 </z>
</drain_location>
<capacity unit="LBS"> 28803 </capacity>
<contents unit="LBS"> 9000 </contents>
<temperature> 59.0 </temperature> <!-- Fuel temp in degrees F -->
</tank>
<tank type="FUEL"><!-- Feed pipe for left engine -->
<location unit="IN">
<x> 700 </x>
<y>-193 </y>
<z> -40 </z>
</location>
<capacity unit="LBS"> 0.5 </capacity>
<contents unit="LBS"> 0.25 </contents>
</tank>
<tank type="FUEL"><!-- Feed pipe for right engine -->
<location unit="IN">
<x> 700 </x>
<y> 193 </y>
<z> -40 </z>
</location>
<capacity unit="LBS"> 0.5 </capacity>
<contents unit="LBS"> 0.25 </contents>
</tank>
</propulsion>
<ground_reactions>
<contact name="Nose Gear" type="BOGEY"> <!-- from AMM - maximum NLG compression is 15.5 in -->
<location unit="IN">
<x> 161 </x>
<y> 0 </y>
<z> -110.83 </z> <!-- BWL 106.57 -->
</location>
<static_friction> 0.40 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<strut_force>
<function>
<sum>
<product>
<value>-1</value>
<table>
<independentVar>gear/unit[0]/compression-ft</independentVar>
<tableData>
0 0
0.042 840
0.083 969
0.125 1108
0.167 1256
0.208 1414
0.25 1585
0.292 1770
0.333 1969
0.375 2185
0.417 2421
0.458 2679
0.5 2962
0.542 3274
0.583 3621
0.625 4007
0.667 4440
0.708 4930
0.75 5488
0.792 6129
0.833 6873
0.875 7748
0.917 8792
0.958 10059
1 11627
1.042 13620
1.083 16238
1.125 19828
1.167 25055
1.208 33371
1.25 48660
1.292 86030
1.3 200000
</tableData>
</table>
</product>
<ifthen>
<ge>
<property> gear/unit[0]/compression-velocity-fps </property>
<value> 0.0 </value>
</ge>
<product>
<value> -8000 </value>
<property> gear/unit[0]/compression-velocity-fps </property>
</product>
<product>
<value> -12000 </value>
<property> gear/unit[0]/compression-velocity-fps </property>
</product>
</ifthen>
</sum>
</function>
</strut_force>
<max_steer unit="DEG"> 78 </max_steer>
<brake_group> NONE </brake_group>
<retractable>1</retractable>
</contact>
<contact name="Left Main Gear" type="BOGEY"> <!-- from AMM - maximum MLG compression is 16 in -->
<location unit="IN">
<x> 775 </x>
<y> -112.5 </y>
<z> -113.99 </z> <!-- BWL 98.31 -->
</location>
<static_friction> 0.40 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<strut_force>
<function>
<sum>
<product>
<value>-1</value>
<table>
<independentVar>gear/unit[1]/compression-ft</independentVar>
<tableData>
0 0
0.042 555
0.083 1160
0.125 1804
0.167 2490
0.208 3222
0.25 4005
0.292 4844
0.333 5747
0.375 6719
0.417 7770
0.458 8910
0.5 10150
0.542 11504
0.583 12989
0.625 14625
0.667 16435
0.708 18449
0.75 20705
0.792 23247
0.833 26135
0.875 29444
0.917 33273
0.958 37755
1 43073
1.042 49485
1.083 57368
1.125 67292
1.167 80169
1.208 97547
1.25 122286
1.292 160318
1.333 226295
1.35 500000
</tableData>
</table>
</product>
<ifthen>
<ge>
<property> gear/unit[1]/compression-velocity-fps </property>
<value> 0.0 </value>
</ge>
<product>
<value> -20000 </value>
<property> gear/unit[1]/compression-velocity-fps </property>
</product>
<product>
<value> -30000 </value>
<property> gear/unit[1]/compression-velocity-fps </property>
</product>
</ifthen>
</sum>
</function>
</strut_force>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>1</retractable>
</contact>
<contact name="Right Main Gear" type="BOGEY"> <!-- from AMM - maximum MLG compression is 16 in -->
<location unit="IN">
<x> 775 </x>
<y> 112.5 </y>
<z> -113.99 </z> <!-- BWL 98.31 -->
</location>
<static_friction> 0.40 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<strut_force>
<function>
<sum>
<product>
<value>-1</value>
<table>
<independentVar>gear/unit[2]/compression-ft</independentVar>
<tableData>
0 0
0.042 555
0.083 1160
0.125 1804
0.167 2490
0.208 3222
0.25 4005
0.292 4844
0.333 5747
0.375 6719
0.417 7770
0.458 8910
0.5 10150
0.542 11504
0.583 12989
0.625 14625
0.667 16435
0.708 18449
0.75 20705
0.792 23247
0.833 26135
0.875 29444
0.917 33273
0.958 37755
1 43073
1.042 49485
1.083 57368
1.125 67292
1.167 80169
1.208 97547
1.25 122286
1.292 160318
1.333 226295
1.35 500000
</tableData>
</table>
</product>
<ifthen>
<ge>
<property> gear/unit[2]/compression-velocity-fps </property>
<value> 0.0 </value>
</ge>
<product>
<value> -20000 </value>
<property> gear/unit[2]/compression-velocity-fps </property>
</product>
<product>
<value> -30000 </value>
<property> gear/unit[2]/compression-velocity-fps </property>
</product>
</ifthen>
</sum>
</function>
</strut_force>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="STRUCTURE" name="TAIL_SKID">
<location unit="IN">
<x> 1417.05 </x>
<y> 0 </y>
<z> -13.5 </z> <!-- BWL 194.60 -->
</location>
<static_friction> 1 </static_friction>
<dynamic_friction> 1 </dynamic_friction>
<rolling_friction> 0 </rolling_friction>
<spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 5000 </damping_coeff>
<max_steer unit="DEG"> 0 </max_steer>
<brake_group> NONE </brake_group>
<retractable> 0 </retractable>
</contact>
<contact type="STRUCTURE" name="NOSE">
<location unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<static_friction> 1 </static_friction>
<dynamic_friction> 1 </dynamic_friction>
<rolling_friction> 0 </rolling_friction>
<spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 5000 </damping_coeff>
<max_steer unit="DEG"> 0 </max_steer>
<brake_group> NONE </brake_group>
<retractable> 0 </retractable>
</contact>
</ground_reactions>
<system file="pushback"/>
<system file="fuel"/>
<system file="fmc"/>
<system file="hydraulics-jsb"/>
<flight_control name="FCS: 737">
<channel name="Pitch">
<summer name="Pitch Trim Sum Cmd">
<input>/controls/flight/elevator-sum</input>
<clipto>
<min>-1</min>
<max> 1</max>
</clipto>
</summer>
<kinematic name="Pitch Trim Sum">
<input>fcs/pitch-trim-sum-cmd</input>
<traverse>
<setting>
<position>-1</position>
<time>0</time>
</setting>
<setting>
<position>1</position>
<time>0.829</time> <!-- from report about Norwegian Air LN-DYM. Rate is 50 deg/sec -->
</setting>
</traverse>
<output>fcs/pitch-trim-sum</output>
</kinematic>
<aerosurface_scale name="Elevator Control">
<input>fcs/pitch-trim-sum</input>
<range>
<min>-0.336</min>
<max> 0.3875</max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Elevator Normalized">
<input>fcs/elevator-pos-rad</input>
<domain>
<min>-0.336</min>
<max> 0.3875</max>
</domain>
<range>
<min>-1</min>
<max> 1</max>
</range>
<output>fcs/elevator-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Roll">
<summer name="Roll Trim Sum">
<input>/controls/flight/aileron-sum</input>
<input>fcs/roll-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max> 1</max>
</clipto>
</summer>
<fcs_function name="Left Aileron Control">
<function>
<table>
<independentVar>fcs/roll-trim-sum</independentVar>
<tableData>
-1 -0.3577924967
-0.9195402299 -0.3271881482
-0.8620689655 -0.3028076439
-0.8045977011 -0.2784271396
-0.7471264368 -0.2540448899
-0.6896551724 -0.2296643856
-0.632183908 -0.2078407886
-0.5747126437 -0.1861428554
-0.5172413793 -0.1644445731
-0.4597701149 -0.1427468143
-0.4022988506 -0.1210490556
-0.3448275862 -0.0993512969
-0.2873563218 -0.0792398679
-0.2298850575 -0.0591930161
-0.1724137931 -0.0391461643
-0.1149425287 -0.0198375868
-0.0574712644 -0.000818809
0 0.0181999444
0.0574712644 0.035044117
0.1149425287 0.0518179528
0.1724137931 0.0685919632
0.2298850575 0.085421126
0.2873563218 0.1023026486
0.3448275862 0.1191841713
0.4022988506 0.1345229974
0.4597701149 0.1495581363
0.5172413793 0.1645932751
0.5747126437 0.1796275413
0.632183908 0.1946635528
0.6896551724 0.209697819
0.7471264368 0.2231124196
0.8045977011 0.2363751766
0.8620689655 0.2496361882
0.9195402299 0.2628989452
1 0.2705260341
</tableData>
</table>
</function>
<output>fcs/left-aileron-pos-rad</output>
</fcs_function>
<fcs_function name="Right Aileron Control">
<function>
<table>
<independentVar>fcs/roll-trim-sum</independentVar>
<tableData>
-1 0.2705260341
-0.9195402299 0.2628989452
-0.8620689655 0.2496361882
-0.8045977011 0.2363751766
-0.7471264368 0.2231124196
-0.6896551724 0.209697819
-0.632183908 0.1946635528
-0.5747126437 0.1796275413
-0.5172413793 0.1645932751
-0.4597701149 0.1495581363
-0.4022988506 0.1345229974
-0.3448275862 0.1191841713
-0.2873563218 0.1023026486
-0.2298850575 0.085421126
-0.1724137931 0.0685919632
-0.1149425287 0.0518179528
-0.0574712644 0.035044117
0 0.0181999444
0.0574712644 -0.000818809
0.1149425287 -0.0198375868
0.1724137931 -0.0391461643
0.2298850575 -0.0591930161
0.2873563218 -0.0792398679
0.3448275862 -0.0993512969
0.4022988506 -0.1210490556
0.4597701149 -0.1427468143
0.5172413793 -0.1644445731
0.5747126437 -0.1861428554
0.632183908 -0.2078407886
0.6896551724 -0.2296643856
0.7471264368 -0.2540448899
0.8045977011 -0.2784271396
0.8620689655 -0.3028076439
0.9195402299 -0.3271881482
1 -0.3577924967
</tableData>
</table>
</function>
<output>fcs/right-aileron-pos-rad</output>
</fcs_function>
<aerosurface_scale name="Left aileron Normalized">
<input>fcs/left-aileron-pos-rad</input>
<domain>
<min>-0.3577924967</min>
<max> 0.2705260341</max>
</domain>
<range>
<min>-1</min>
<max> 1</max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="Right aileron Normalized">
<input>fcs/right-aileron-pos-rad</input>
<domain>
<min>-0.3577924967</min>
<max> 0.2705260341</max>
</domain>
<range>
<min>-1</min>
<max> 1</max>
</range>
<output>fcs/right-aileron-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Yaw">
<summer name="Rudder Command Sum">
<input>fcs/rudder-cmd-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max> 1</max>
</clipto>
</summer>
<!--Yaw damper-->
<washout_filter name="yaw-wf">
<input>velocities/r-aero-rad_sec</input>
<c1>4</c1>
</washout_filter>
<pure_gain name="Yaw Damper">
<input>fcs/yaw-wf</input>
<gain>5</gain>
</pure_gain>
<!--Slip stabilizer-->
<switch name="accelerations/Ny-switched">
<default value="0.0"/>
<test logic="AND" value="accelerations/Ny">
aero/h_b-mac-ft GE 1
/b737/controls/flight/yaw-damper NE 0
</test>
</switch>
<pid name="fcs/yaw-slip">
<input>accelerations/Ny-switched</input>
<kp> -0.1 </kp>
<ki> 0.05 </ki>
<kd> 0.0 </kd>
<clipto>
<min>-0.12</min>
<max>0.12</max>
</clipto>
<!--<output>fcs/yaw-slip-out</output> possible for debug -->
</pid>
<summer name="Yaw Damper Sum">
<input>fcs/yaw-damper</input>
<input>fcs/yaw-slip</input>
<clipto>
<min>-0.12</min>
<max> 0.12</max>
</clipto>
</summer>
<switch name="Yaw Damper Final">
<default value="0.0"/>
<test value="fcs/yaw-damper-sum">
/b737/controls/flight/yaw-damper ne 0
</test>
</switch>
<summer name="Rudder Sum Cmd">
<input>fcs/rudder-command-sum</input>
<input>fcs/yaw-damper-final</input>
<clipto>
<min>-1</min>
<max> 1</max>
</clipto>
</summer>
<kinematic name="Rudder Sum">
<input>fcs/rudder-sum-cmd</input>
<traverse>
<setting>
<position>-1</position>
<time>0</time>
</setting>
<setting>
<position>1</position>
<time>0.909</time> <!-- from reports about problems with jammed rudder -->
</setting>
</traverse>
<output>fcs/rudder-sum</output>
</kinematic>
<aerosurface_scale name="Rudder Control"> <!-- -30...+30 degrees range -->
<input>fcs/rudder-sum</input>
<range>
<min>-0.523</min>
<max> 0.523</max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Rudder Normalized">
<input>fcs/rudder-pos-rad</input>
<domain>
<min>-0.523</min>
<max> 0.523</max>
</domain>
<range>
<min>-1</min>
<max> 1</max>
</range>
<output>fcs/rudder-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Flaps">
<kinematic name="Flaps Control">
<input>fcs/flap-cmd-norm</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>0.125</position>
<time>13</time>
</setting>
<setting>
<position>0.25</position>
<time>3</time>
</setting>
<setting>
<position>0.375</position>
<time>4</time>
</setting>
<setting>
<position>0.5</position>
<time>2</time>
</setting>
<setting>
<position>0.625</position>
<time>3</time>
</setting>
<setting>
<position>0.75</position>
<time>2</time>
</setting>
<setting>
<position>0.875</position>
<time>5</time>
</setting>
<setting>
<position>1</position>
<time>5</time>
</setting>
</traverse>
<output>fcs/flap-pos-norm</output>
</kinematic>
</channel>
<channel name="Landing Gear">
<kinematic name="Gear Control">
<input>gear/gear-cmd-norm</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>1</position>
<time>5</time>
</setting>
</traverse>
<output>gear/gear-pos-norm</output>
</kinematic>
</channel>
<channel name="Flight Spoilers">
<!-- operated by the speedbrake handle and roll control -->
<fcs_function name="Outboard spoiler command low">
<function>
<table>
<independentVar>fcs/roll-trim-sum</independentVar>
<tableData>
-0.966 -33.0184
-0.954 -32.5422
-0.839 -25.816
-0.69 -17.9607
-0.483 -10.0735
-0.23 -3.08542
-0.172 -0.734767
-0.161 -0.262478
-0.149 0
0.149 0
0.161 0.262478
0.172 0.734767
0.23 3.08542
0.483 10.0735
0.69 17.9607
0.839 25.816
0.954 32.5422
0.966 33.0184
</tableData>
</table>
</function>
<output>fcs/spoilers-outb-cmd-low</output>
</fcs_function>
<fcs_function name="Outboard spoiler command high">
<function>
<table>
<independentVar>fcs/roll-trim-sum</independentVar>
<tableData>
-0.908 -33.0184
-0.897 -33
-0.885 -32.7384
-0.874 -32.3305
-0.828 -29.3878
-0.69 -21.2068
-0.494 -12.3579
-0.322 -6.87439
-0.207 -3.93022
-0.126 -0
0.126 0
0.207 3.93022
0.322 6.87439
0.494 12.3579
0.69 21.2068
0.828 29.3878
0.874 32.3305
0.885 32.7384
0.897 33
0.908 33.0184
</tableData>
</table>
</function>
<output>fcs/spoilers-outb-cmd-high</output>
</fcs_function>
<pure_gain name="fcs/spoilers-outb-rollpos">
<input>fcs/spoilers-outb-rollpos</input>
<gain>1</gain>
<clipto>
<min>fcs/spoilers-outb-cmd-low</min>
<max>fcs/spoilers-outb-cmd-high</max>
</clipto>
<output>fcs/spoilers-outb-rollpos</output>
</pure_gain>
<fcs_function name="fcs/spoilers-23-pos">
<function>
<sum>
<product>
<property>fcs/spoilers-outb-rollpos</property>
<value>-1</value>
</product>
<table>
<independentVar>/controls/flight/speedbrake-output</independentVar>