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do328-110.xml
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do328-110.xml
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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Dornier 328-110" 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 0.95 </author>
<filecreationdate>2013-07-21</filecreationdate>
<version>$Revision: 1.15 $</version>
<description> Models a Dornier 328-110. </description>
</fileheader>
<!--
File: Dornier 328-1xx.xml
Inputs:
name: Dornier 328-1xx
type: multi-engine jet transport
max weight: 30843.54 lb
wing span: 68.8 ft
length: 69.8 ft
wing area: 430.6 sq-ft
gear type: tricycle
retractable?: yes
# engines: 2
engine type: turboprop
engine layout: wings
yaw damper? yes
Outputs:
wing loading: 71.63 lb/sq-ft
payload: 3339.3 lbs
CL-alpha: 4.9 per radian
CL-0: 0.24
CL-max: 1.4
CD-0: 0.025
K: 0.039
-->
<!--
SPECS:
Height: 7.24m
Length: 21.11
Wing span: 20.98
Cruise Speed 270 KIAS up to 20000ft
Maximum mach speed 0.59 from 20000 to 31000
MTAS= 335ktn
Landing gear speed 200 KIAS
Flap Design Speed:
12degrees = 200 KIAS = Takeoff/ Approach Climb
20 degrees = 180 KIAS = Landing/ Approach Climb
32 degrees = 160 KIAS = landing
Max level spd: 324 kts
Max TO weight: 30840 lbs
Empty weight: 19670lbs
Range: 1000nm
Service ceiling: 31000ft
Cat II certification
MTOW, flaps 12 degrees, no icing: v2= 133 (?) kt from: http://uk.answers.yahoo.com/question/index?qid=20070125034605AAc90Bd
MTOW, flaps 12 degrees, no icing: Vr= 114kt
12500 kg (27557.78lbs)flaps 12 degrees, no icing condition:V1/vr= 109kt, V2: 113kt from: http://www.skybrary.aero/bookshelf/books/1285.pdf
with ice condition (deice) around 20kt higher according to the source: V1/Vr= 128kt, V2= 129kt
Another possible setting, 11710kg, (25816.13lbs) flaps 12 degrees, V1= 112kt, Vr= 117kt from: http://www.flightglobal.com/pdfarchive/view/1995/1995%20-%203235.html
probaly with icing conditions, without it should/could be: V1= 92 Vr= 97kt ??
Or: 11758.47kg, (25922.98lbs) flaps 12 degrees,OAT = -1 Celsius (icing condition), V1= 112kt, Vr=117kt, V2= 119kt from: http://compair.aviationresearch.com/database_files/TheImage_41.pdf
So no icing it should/could be 92/97/99kt ??
Weight/Vspeeds expected to be linear- here it is not. if it would be linear, than Vr would be at 11700kg = 104kt
Stall speed @max weight clean: 113kt
" " " " flap 32 degrees: 91kt
More stall speeds: http://www.caa.co.uk/docs/1455/SRG_FLT_CFS_284_Issue1_27072006.pdf
Vref= 1,3* Vs (Stall speed landing config)
Approach speed Vref at 11000kg (24250.84lbs)flaps 32: ca. 101kt (condition?) from :http://www.flightglobal.com/news/articles/a-better-pace-setter-21159
http://www.flightglobal.com/pdfarchive/view/1995/1995%20-%203235.html
Approach speed Vref at 12400kg (27337.32lbs)icing condition: 124 kt (so no icing should be 104kt?): BFU Saarbruecken accident
Approach speed Vref at <10500kg (23148.53lbs)icing condition: 115 kt (so no icing should be 95kt?): BFU Bremen Accident
Weight/Vrefs are more or less linear here
Landing Distance MLW (1/0.6): 3524ft/1025m (Landing distance with safety margin)
Landing Distance MLW unfactored (what the aircraft demostrated without any safety margin): 2115ft/645m
-->
<metrics>
<wingarea unit="M2"> 40.000 </wingarea>
<wingspan unit="FT"> 68.8000 </wingspan>
<wing_incidence unit="DEG"> 1.50 </wing_incidence>
<chord unit="FT"> 9.0000 </chord>
<htailarea unit="FT2"> 81.6480 </htailarea>
<htailarm unit="FT"> 37.6141 </htailarm>
<vtailarea unit="FT2"> 104.8608 </vtailarea>
<vtailarm unit="FT"> 33.5977 </vtailarm>
<location name="AERORP" unit="IN">
<x> -86.5 </x>
<y> 0.00 </y>
<z> 84.0</z>
</location>
<location name="EYEPOINT" unit="IN">
<x>317.764 </x>
<y> 28.39 </y>
<z> 95.68 </z>
</location>
<location name="VRP" unit="IN">
<x>0</x>
<y>0</y>
<z>0</z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 74023 </ixx>
<iyy unit="SLUG*FT2"> 91146 </iyy>
<izz unit="SLUG*FT2"> 162013 </izz>
<emptywt unit="LBS" > 19670 </emptywt>
<location name="CG" unit="IN">
<x> -76.5 </x>
<y> 0.00 </y>
<z> 84.0 </z>
</location>
<pointmass name="Payload">
<description> 3339 LBS + full (7834 LBS) fuel should bring model up to entered max weight</description>
<weight unit="LBS">0</weight>
<location name="POINTMASS" unit="IN">
<x> -91.45 </x>
<y> 0.00 </y>
<z> 62.98 </z>
</location>
</pointmass>
<pointmass name="Crew">
<description> Crew</description>
<weight unit="LBS"> 371 </weight>
<location name="POINTMASS" unit="IN">
<x> -312.27 </x>
<y> 0.00 </y>
<z> 62.98 </z>
</location>
</pointmass>
<pointmass name="Cargo">
<description> Cargo</description>
<weight unit="LBS">0 </weight>
<location name="POINTMASS" unit="IN">
<x> 149.89</x>
<y> 0.00 </y>
<z> 73.37 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<!--structure by Michael Soitanen, coefficients by Heiko Schulz-->
<location unit="IN">
<x> -343.49 </x>
<y> 0.00 </y>
<z> -11.74 </z>
</location>
<static_friction> 0.80 </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
0.65 600
1.3 45500
1.31 49000
</tableData>
</table>
</product>
<ifthen>
<ge>
<property> gear/unit[0]/compression-velocity-fps </property>
<value> 0.0 </value>
</ge>
<product>
<value> -1100 </value>
<property> gear/unit[0]/compression-velocity-fps </property>
</product>
<product>
<value> -2600 </value>
<property> gear/unit[0]/compression-velocity-fps </property>
</product>
</ifthen>
</sum>
</function>
</strut_force>
<max_steer unit="DEG"> 10 </max_steer>
<brake_group> NONE </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<!--structure by Michael Soitanen, coefficients by Heiko Schulz-->
<location unit="IN">
<x> -54.044 </x>
<y> -63.39 </y>
<z> -9.11 </z>
</location>
<static_friction>0.8</static_friction>
<dynamic_friction> 0.5 </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
1.30 50500
1.31 65000
</tableData>
</table>
</product>
<ifthen>
<ge>
<property> gear/unit[1]/compression-velocity-fps </property>
<value> 0.0 </value>
</ge>
<product>
<value> -2500 </value>
<property> gear/unit[1]/compression-velocity-fps </property>
</product>
<product>
<value> -3900</value>
<property> gear/unit[1]/compression-velocity-fps </property>
</product>
</ifthen>
</sum>
</function>
</strut_force>
<max_steer unit="DEG">0</max_steer>
<brake_group>LEFT</brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MAIN">
<!--structure by Michael Soitanen, coefficients by Heiko Schulz-->
<location unit="IN">
<x> -54.044 </x>
<y> 63.39 </y>
<z> -9.11 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction>0.5 </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
1.30 50500
1.31 65000
</tableData>
</table>
</product>
<ifthen>
<ge>
<property> gear/unit[2]/compression-velocity-fps </property>
<value> 0.0 </value>
</ge>
<product>
<value> -2500</value>
<property> gear/unit[2]/compression-velocity-fps </property>
</product>
<product>
<value> -3900 </value>
<property> gear/unit[2]/compression-velocity-fps </property>
</product>
</ifthen>
</sum>
</function>
</strut_force>
<max_steer unit="DEG">0</max_steer>
<brake_group>RIGHT</brake_group>
<retractable>1</retractable>
</contact>
<!-- to prevent from sinking in to deep
<contact type="BOGEY" name="NOSE2">
<location unit="IN">
<x> -343.49 </x>
<y> 0.00 </y>
<z> -1.74 </z>
</location>
<static_friction> 0.00 </static_friction>
<dynamic_friction> 0.00 </dynamic_friction>
<rolling_friction> 0.0 </rolling_friction>
<spring_coeff unit="LBS/FT"> 0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 000 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC">0000</damping_coeff_rebound>
<max_steer unit="DEG"> 5.00 </max_steer>
<brake_group>NONE</brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN2">
<location unit="IN">
<x> -54.044 </x>
<y> -71.88 </y>
<z> -1.8 </z>
</location>
<static_friction> 0.0</static_friction>
<dynamic_friction> 0.00 </dynamic_friction>
<rolling_friction> 0.0 </rolling_friction>
<spring_coeff unit="LBS/FT"> 0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 0 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC">000</damping_coeff_rebound>
<max_steer unit="DEG">0</max_steer>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MAIN2">
<location unit="IN">
<x> -54.044 </x>
<y> 71.88 </y>
<z> -1.8 </z>
</location>
<static_friction> 0.0 </static_friction>
<dynamic_friction> 0.00 </dynamic_friction>
<rolling_friction> 0.0 </rolling_friction>
<spring_coeff unit="LBS/FT"> 0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 0</damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC">00</damping_coeff_rebound>
<max_steer unit="DEG">0</max_steer>
<retractable>1</retractable>
</contact>-->
<contact type="STRUCTURE" name="LEFT_WING">
<location unit="IN">
<x> 44.82 </x>
<y> -414.98 </y>
<z>119.76 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_WING">
<location unit="IN">
<x> 44.82 </x>
<y> 414.98 </y>
<z>119.76 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="LEFT_FIN">
<location unit="IN">
<x> 252.588 </x>
<y>-16.07 </y>
<z>45.64</z>
</location>
<static_friction> 0.8</static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC">1000</damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_FIN">
<location unit="IN">
<x> 252.588 </x>
<y>16.07 </y>
<z>45.64</z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="TAIL">
<location unit="IN">
<x> 401.92 </x>
<y>0</y>
<z>90.588</z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC">1000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="NOSE">
<location unit="IN">
<x> -414.19</x>
<y>0</y>
<z>43.84</z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 10000</damping_coeff>
</contact>
<contact type="STRUCTURE" name="BELLY_FORWARD">
<location unit="IN">
<x> -390.8</x>
<y>0</y>
<z>30.07</z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="BELLY_AFT_LEFT">
<location unit="IN">
<x> -44.9</x>
<y>-28.78</y>
<z>12.94</z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="BELLY_AFT_RIGHT">
<location unit="IN">
<x> -44.9</x>
<y>28.78</y>
<z>12.94</z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000</spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
</contact>
</ground_reactions>
<propulsion>
<engine file="PW119BR">
<location unit="IN">
<x>-143.17 </x>
<y> -139 </y>
<z>114.823 </z>
</location>
<orient unit="DEG">
<pitch> 1.50 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<feed>3</feed>
<feed>4</feed>
<feed>5</feed>
<thruster file="hartzell2">
<sense>1</sense>
<location unit="IN">
<x>-200.35 </x>
<y> -139 </y>
<z>114.823 </z>
</location>
<orient unit="DEG">
<pitch>1.50 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<engine file="PW119BL">
<location unit="IN">
<x>-143.17 </x>
<y> 139 </y>
<z>114.823 </z>
</location>
<orient unit="DEG">
<pitch> 1.50 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<feed>3</feed>
<feed>4</feed>
<feed>5</feed>
<thruster file="hartzell2">
<sense>1</sense>
<location unit="IN">
<x>-200.35 </x>
<y> 139 </y>
<z>114.823 </z>
</location>
<orient unit="DEG">
<pitch> 1.50 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<!--http://328.eu/wp-content/uploads/2013/04/easa-tcds-do328.pdf-->
<tank type="FUEL" number="0"><!--feeder tank-->
<location unit="M">
<x>-2.0 </x>
<y>-7.634 </y>
<z> 3.1 </z>
</location>
<priority>1</priority>
<capacity unit="LBS"> 187.4 </capacity>
<contents unit="LBS"> 187.4 </contents>
<density unit="LBS/GAL"> 6.643 </density>
</tank>
<tank type="FUEL" number="1">
<location unit="M">
<x>-2.0 </x>
<y>-5.0 </y>
<z> 3.2 </z>
</location>
<priority>1</priority>
<capacity unit="LBS"> 1395.5 </capacity>
<contents unit="LBS"> 1395.5 </contents>
<density unit="LBS/GAL"> 6.643 </density>
</tank>
<tank type="FUEL" number="2">
<location unit="M">
<x>-2.0 </x>
<y>-2.2 </y>
<z> 3.2 </z>
</location>
<priority>1</priority>
<capacity unit="LBS"> 2182.6 </capacity>
<contents unit="LBS"> 2182.6 </contents>
<density unit="LBS/GAL"> 6.643 </density>
</tank>
<tank type="FUEL" number="3">
<location unit="M">
<x>-2.0 </x>
<y> 2.2 </y>
<z> 3.2 </z>
</location>
<priority>1</priority>
<capacity unit="LBS"> 2182.6 </capacity>
<contents unit="LBS"> 2182.6 </contents>
<density unit="LBS/GAL"> 6.643 </density>
</tank>
<tank type="FUEL" number="4">
<location unit="M">
<x>-2.0 </x>
<y> 5.0 </y>
<z> 3.2 </z>
</location>
<priority>1</priority>
<capacity unit="LBS"> 1395.5 </capacity>
<contents unit="LBS"> 1395.5 </contents>
<density unit="LBS/GAL"> 6.643 </density>
</tank>
<tank type="FUEL" number="5"><!--feeder tank-->
<location unit="M">
<x>-2.0 </x>
<y> 7.634 </y>
<z> 3.1 </z>
</location>
<priority>1</priority>
<capacity unit="LBS"> 187.4 </capacity>
<contents unit="LBS"> 187.4 </contents>
<density unit="LBS/GAL"> 6.643 </density>
</tank>
</propulsion>
<flight_control name="FCS: Dornier 328-110">
<channel name = "aeromechanical">
<switch name="/controls/gear/tiller-disabled">
<default value="0"/>
<test logic="AND" value="1">
/controls/gear/tiller-enabled == 0
</test>
</switch>
<fcs_function name="Nose Wheel Steering 0">
<function name="fcs/steer-nose-deg[0]">
<description>Steering command for nose gear</description>
<sum>
<product>
<table>
<independentVar lookup="row">/controls/gear/tiller-cmd-norm</independentVar>
<independentVar lookup="column">/controls/flight/rudder</independentVar>
<tableData>
-1 0 1
-1 -61 -61 -61
0 -10 0 10
1 61 61 61
</tableData>
</table>
<property>/controls/gear/tiller-enabled</property>
</product>
<product>
<product>
<property>/controls/flight/rudder</property>
<value>61</value>
</product>
<property>/controls/gear/tiller-disabled</property>
</product>
</sum>
</function>
</fcs_function>
<fcs_function name="propulsion/engine[0]/trq-percent">
<function>
<description>Indicated TRQ in percent</description>
<product>
<property>propulsion/engine/EIP/state</property>
<max>
<value>0</value>
<product>
<property>propulsion/engine/power-hp</property>
<value>60</value>
<pow>
<max>
<property>propulsion/engine/propeller-rpm</property>
<value>10</value>
</max>
<value>-1</value>
</pow>
</product>
</max>
</product>
</function>
</fcs_function>
<fcs_function name="propulsion/engine[1]/trq-percent">
<function>
<description>Indicated TRQ in percent</description>
<product>
<property>propulsion/engine/EIP/state</property>
<max>
<value>0</value>
<product>
<property>propulsion/engine[1]/power-hp</property>
<value>60</value>
<pow>
<max>
<property>propulsion/engine[1]/propeller-rpm</property>
<value>10</value>
</max>
<value>-1</value>
</pow>
</product>
</max>
</product>
</function>
</fcs_function>
<!-- need %Cg in chord for moments [Xcg - Xref)/100]
<summer name="cg-x-offset-chord-in">
<input> inertia/cg-x-in</input>
<input> -metrics/aero-rp-x-in</input>
<output>inertia/cg-x-offset-chord-in</output>
</summer>
<pure_gain name="cg-x-chord-percent">
<description>Percent offset of the CoP from the CG</description>
<input>inertia/cg-x-offset-chord-in</input>
<gain> -0.01</gain>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
<output> inertia/cg-x-mac-percent </output>
</pure_gain>-->
<!-- simulate rotational friction -->
<actuator name="Gear Nose Actuator">
<input>fcs/steer-nose-deg[0]</input>
<rate_limit>61</rate_limit>
<output>fcs/steer-pos-deg[0]</output>
</actuator>
</channel>
<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>
<gain>0.01745</gain>
<range>
<min> -25 </min>
<max> 30 </max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
</channel>
<channel name="Roll">
<summer name="Roll Trim Sum">
<input>fcs/aileron-cmd-norm</input>
<input>fcs/roll-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
<aerosurface_scale name="Left Aileron Control">
<input>fcs/roll-trim-sum</input>
<gain>0.01745</gain>
<range>
<min>-25</min>
<max>28</max>
</range>
<output>fcs/left-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Left Aileron Norm">
<input>fcs/roll-trim-sum</input>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron Control">
<input>-fcs/roll-trim-sum</input>
<gain>0.01745</gain>
<range>
<min>-25</min>
<max>28</max>
</range>
<output>fcs/right-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron Norm">
<input>-fcs/roll-trim-sum</input>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/right-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="Left Spoileron Control">
<input>fcs/roll-trim-sum</input>
<gain>0.01745</gain>
<range>
<min>-58</min>
<max>0</max>
</range>
<output>fcs/left-spoileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Left Spoileron Norm">
<input>fcs/roll-trim-sum</input>
<range>
<min>-1</min>
<max>0</max>
</range>
<output>fcs/left-spoileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="Right Spoileron Control">
<input>-fcs/roll-trim-sum</input>
<gain>0.01745</gain>
<range>
<min>-58</min>
<max>0</max>
</range>
<output>fcs/right-spoileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Right Spoileron Norm">
<input>-fcs/roll-trim-sum</input>
<range>
<min>-1</min>
<max>0</max>
</range>
<output>fcs/right-spoileron-pos-norm</output>
</aerosurface_scale>
</channel>
<property value="1">fcs/yaw-damper-enable</property>
<channel name="Yaw">
<scheduled_gain name="Yaw Damper Rate">
<input>velocities/r-aero-rad_sec</input>
<table>
<independentVar lookup="row">velocities/ve-kts</independentVar>
<tableData>
30 0.00
60 2.00
</tableData>
</table>
<gain>fcs/yaw-damper-enable</gain>
</scheduled_gain>
<summer name="Rudder Sum">
<input>fcs/rudder-command-sum</input>
<input>fcs/yaw-damper-rate</input>
<clipto>
<min> -1.0 </min>
<max> 1.0 </max>
</clipto>
</summer>
<aerosurface_scale name="Rudder Control">
<input>fcs/rudder-sum</input>
<domain>
<min> -1.0 </min>
<max> 1.0</max>
</domain>
<range>
<min> -0.349 </min>
<max> 0.4188 </max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="rudder normalization">
<input>fcs/rudder-pos-rad</input>
<domain>
<min> -0.349 </min>
<max> 0.4188 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/rudder-pos-norm</output>
</aerosurface_scale>
<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>
</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>0.375</position>
<time>4</time>
</setting>
<setting>
<position>0.625</position>
<time>4</time>
</setting>
<setting>
<position>1</position>
<time>4</time>
</setting>
</traverse>
<output>fcs/flap-pos-norm</output>
</kinematic>
<aerosurface_scale name="Flap Position Normalizer">
<input>fcs/flap-pos-norm</input>
<domain>
<min>0</min>
<max>1</max>
</domain>
<range>
<min>0</min>
<max>32</max>
</range>
<output>fcs/flap-pos-deg</output>
</aerosurface_scale>
</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> 13</time>
</setting>
</traverse>
<output>gear/gear-pos-norm</output>
</kinematic>
</channel>
<channel name="Groundspoiler">
<kinematic name="Groundspoiler Control">
<input>fcs/spoiler-cmd-norm</input>
<traverse>
<setting>
<position> 0 </position>
<time> 0 </time>
</setting>
<setting>
<position> 1 </position>
<time> 0.75 </time>
</setting>
</traverse>
<output>fcs/groundspoiler-pos-norm</output>
</kinematic>
</channel>
<channel name="alpha-wing-rad-to-deg">
<pure_gain name="wing-incidence-deg">
<input>aero/alpha-wing-rad</input>
<gain>57.29578</gain>
<output>aero/alpha-wing-deg</output>
</pure_gain>
</channel>
<property>fcs/aeromatic</property>
<property>propulsion/engine[0]/torque-lbs</property>
<property>propulsion/engine/EIP/state</property>
</flight_control>
<aerodynamics>
<function name="aero/function/kCDge">
<description>Change_in_drag_due_to_ground_effect</description>
<product>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 0.0480
0.1000 0.5150
0.1500 0.6290
0.2000 0.7090
0.3000 0.8150