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A-10-yasim.xml
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A-10-yasim.xml
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<!-- A-10 yasim config. This is a hack and not an authentic
representation of the aircraft. Having said that, the
numbers, where I could find them, roughly match those of
the original aircraft.
Lee Elliott.
-->
<!--
Aircraft mass comprises pilot, oxygen, unusable fuel & oil, gun and
six pylons. The solve weight used in the approach and cruise
configurations represent a full ammunition load (1350 x 2lbs)
-->
<airplane mass="24959">
<!-- Approach configuration -->
<approach speed="120" aoa="8" fuel="0.2">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.5"/>
<control-setting axis="/controls/engines/engine[1]/throttle" value="0.5"/>
<control-setting axis="/controls/flight/flaps" value="1.0"/>
<control-setting axis="/controls/flight/spoilers" value="0.5"/>
<control-setting axis="/controls/gear/gear-down" value="1.0"/>
<solve-weight idx="0" weight="2700"/>
</approach>
<!-- Cruise configuration -->
<cruise speed="380" alt="15000" fuel="0.8">
<control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
<control-setting axis="/controls/engines/engine[1]/throttle" value="1.0"/>
<control-setting axis="/controls/flight/flaps" value="0.0"/>
<control-setting axis="/controls/flight/spoilers" value="0.0"/>
<control-setting axis="/controls/gear/gear-down" value="0.0"/>
<solve-weight idx="0" weight="2700"/>
</cruise>
<cockpit x="-3.25" y="0.0" z="1.2"/>
<fuselage ax="0" ay="0" az="0" bx="-16.16" by="0" bz="0"
width="1.4" taper="0.9"/>
<!-- Left Engine -->
<fuselage ax="-9.44" ay="1.50" az="1.3" bx="-12.73" by="1.50" bz="1.18"
width="1.5"/>
<!-- Right Engine -->
<fuselage ax="-9.44" ay="-1.50" az="1.3" bx="-12.73" by="-1.50" bz="1.18"
width="1.5"/>
<wing x="-8.32" y="0.63" z="0.0" taper="0.7" incidence="-0.8"
length="8.31" chord="3.23" sweep="0.0" dihedral="3.0"
camber="0.0" twist="-1">
<stall aoa="15" width="6" peak="1.3"/>
<flap0 start="0.04" end="0.51" lift="1.3" drag="1.3"/>
<flap1 start="0.54" end="0.86" lift="1.6" drag="1.3"/>
<spoiler start="0.54" end="0.86" lift="0.6" drag="10.0"/>
<control-input axis="/controls/flight/flaps" control="FLAP0"/>
<control-input axis="/controls/flight/aileron" control="FLAP1" split="true"/>
<control-input axis="/controls/flight/aileron-trim" control="FLAP1" split="true"/>
<control-input axis="/controls/flight/spoilers" control="SPOILER"/>
<control-output control="FLAP0" side="left"
prop="/surface-positions/left-flap-pos-norm"/>
<control-output control="FLAP0" side="right"
prop="/surface-positions/right-flap-pos-norm"/>
<control-output control="FLAP0" prop="/surface-positions/flap-pos-norm"/>
<control-output control="FLAP1" side="left"
prop="/surface-positions/left-aileron-pos-norm"/>
<control-output control="FLAP1" side="right"
prop="/surface-positions/right-aileron-pos-norm"/>
<control-output control="FLAP1" prop="/surface-positions/aileron-pos-norm"/>
<control-output control="SPOILER" side="left"
prop="/surface-positions/left-spoiler-pos-norm"/>
<control-output control="SPOILER" side="right"
prop="/surface-positions/right-spoiler-pos-norm"/>
<control-output control="SPOILER" prop="/surface-positions/spoiler-pos-norm"/>
<control-speed control="FLAP0" transition-time="15"/>
<control-speed control="FLAP1" transition-time="0.5"/>
<control-speed control="SPOILER" transition-time="1.0"/>
</wing>
<hstab x="-14.88" y="0.42" z="0.41" taper="0.0" effectiveness="2"
length="2.38" chord="1.95" sweep="0.0" dihedral="0.0"
camber="-0.0">
<stall aoa="15" width="3" peak="1.3"/>
<flap0 start="0" end="1" lift="1.8" drag="1.7"/>
<control-input axis="sim/model/A-10/controls/flight/sas-elevator" control="FLAP0"
square="true"/>
<control-input axis="/controls/flight/elevator-trim" control="FLAP0"/>
<control-output control="FLAP0" side="left"
prop="surface-positions/left-elevator-pos-norm"/>
<control-output control="FLAP0" side="right"
prop="surface-positions/right-elevator-pos-norm"/>
<control-output control="FLAP0" prop="surface-positions/elevator-pos-norm"/>
<control-speed control="FLAP0" transition-time="0.2"/>
</hstab>
<vstab x="-14.88" y="2.85" z="0.0" taper="0.6" effectiveness="2"
length="2.8" chord="2.14" sweep="0.0">
<stall aoa="16" width="5" peak="1.5"/>
<flap0 start="0" end="1" lift="1.5" drag="1.5"/>
<control-input axis="/controls/flight/rudder" control="FLAP0"
square="true" invert="true"/>
<control-input axis="/controls/flight/rudder-trim" control="FLAP0"
invert="true"/>
<control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"/>
<control-speed control="FLAP0" transition-time="0.5"/>
</vstab>
<vstab x="-14.88" y="-2.85" z="0.0" taper="0.6" effectiveness="2"
length="2.8" chord="2.14" sweep="0.0">
<stall aoa="16" width="5" peak="1.5"/>
<flap0 start="0" end="1" lift="1.5" drag="1.5"/>
<control-input axis="/controls/flight/rudder" control="FLAP0"
square="true" invert="true"/>
<control-input axis="/controls/flight/rudder-trim" control="FLAP0"
invert="true"/>
<control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"/>
<control-speed control="FLAP0" transition-time="0.5"/>
</vstab>
<!-- 2 x GE TF34-100 -->
<!-- GE TF34-100 characteristics:
thrust (at sea level): 9065 lbs (40422 N)
weight: 1,458 lbs
fuel consumption: 0.363 lbs per pound of thrust
bypass ratio: 6.42
pressure ratio: 21
fan/core thrust ratio: 0.85
spool time (idle to 100%): 10 sec
fan airflow: 338 lb/sec
fan airflow speed: 223.6 m/s (=> 434.64 kt) ( Vo(m/s)-Vi(m/s)=Thrust(N)/Dm(Kg/s) => (40422*0.85)/(338/2.2) , at takeoff we consider Ve = 0)
fan speed: 7,365 rpm
compressor airflow: 47 lb/sec
compressor airflow speed: 283.8 m/s (=> 551.7 kt)
compressor speed: 17,900 rpm
exhaust gas temperature: 813 °C
-->
<jet x="-10.8" y="1.5" z="1.27" mass="1440" thrust="18000" spool-time="8" tsfc="0.394" n1-idle="20" n1-max="100" n2-idle="56" n2-max="102" epr="2.0" exhaust-speed="2500.0" egt="1086" rotate="9">
<actionpt x="-12.5" y="1.5" z="1.15"/>
<control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"/>
</jet>
<jet x="-10.8" y="-1.5" z="1.27" mass="1440" thrust="18000" spool-time="8" tsfc="0.394" n1-idle="20" n1-max="100" n2-idle="56" n2-max="102" exhaust-speed="2500.0" epr="2.0" egt="1086" rotate="9">
<actionpt x="-12.5" y="-1.5" z="1.15"/>
<control-input axis="/controls/engines/engine[1]/throttle" control="THROTTLE"/>
</jet>
<!-- Internal tanks -->
<tank x="-8.3" y="2.0" z="0.0" jet="true" capacity="2089.92"/><!-- ppg=6.72, real tank capacity : 311 gallons -> 311*6.72 = 2089.92 lbs -->
<tank x="-8.8" y="0.0" z="0.63" jet="true" capacity="3433.92"/><!-- real tank capacity: 511 gallons -> 511*6.72 = 3433.92 lbs -->
<tank x="-7.2" y="0.0" z="0.63" jet="true" capacity="3433.92"/>
<tank x="-8.3" y="-2.0" z="0.0" jet="true" capacity="2089.92"/>
<!-- Ferry Tanks -->
<tank x="-7.6" y="1.29" z="-0.86" jet="true" capacity="4032"/> <!-- 600*6.72 = 4032 -->
<tank x="-7.6" y="0" z="-0.86" jet="true" capacity="4032"/>
<tank x="-7.6" y="-1.29" z="-0.86" jet="true" capacity="4032"/>
<!-- Undercarriage -->
<!-- nose -->
<gear x="-2.85" y="0.4" z="-2.33" compression="0.30" spring="0.25" damp="1.4">
<control-input axis="/controls/flight/rudder" control="STEER" square="true"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-speed control="EXTEND" transition-time="7"/>
<control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
</gear>
<!-- left main -->
<gear x="-8.3" y="2.5" z="-2.37" compression="0.4" spring="0.25" damp="1.4">
<control-input axis="/controls/gear/brake-left" control="BRAKE"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-speed control="EXTEND" transition-time="7"/>
<control-output control="EXTEND" prop="gear/gear[1]/position-norm"/>
</gear>
<!-- right main -->
<!--<gear x="-8.3" y="-2.5" z="-2.22" retract-time="6" compression="0.7" spring="1.6" damp="1.4">-->
<gear x="-8.3" y="-2.5" z="-2.37" compression="0.4" spring="0.25" damp="1.4">
<control-input axis="/controls/gear/brake-right" control="BRAKE"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-speed control="EXTEND" transition-time="7"/>
<control-output control="EXTEND" prop="gear/gear[2]/position-norm"/>
</gear>
<!-- Ballast -->
<ballast x="-3.16" y="0" z="0.78" mass="1200" /><!-- Titanium bathtub (for the mass see: http://www.plane-crazy.net/links/a10.htm) -->
<ballast x="-1.71" y="0.183" z="-0.823" mass="620"/><!-- GAU-8 barrel (length: 2800mm + 620mm) -->
<ballast x="-4.91" y="0" z="0" mass="2310"/><!-- GAU-8 feed system + ammunition drum + aluminium alloy cases + plastic driving bands -->
<ballast x="-6.1" y="0" z="0.0" mass="1000"/> <!-- avionics -->
<ballast x="-4" y="0" z="0.0" mass="2500"/> <!-- CG trim trim -->
<!--
GAU-8/A characteristics:
Magazine capacity: 1,350 max (1,174 is the normal load)
Rate of fire: 3900 RPM
Barrel length: 2.80 m
Total length: 6.4 m (from the muzzle to the rearmost point of the ammunition system)
Barrel weight: 620 lb
Total weight: 4,029 lb (complete weapon + ammunition load)
Recoil force: 10,000 lb
Ammo types:
PGU-14/B API: Armor Piercing Incendiary (with depleted uranium)
projectile weight: 425 grams
velocity: 3250 ft/sec
PGU-13/B HEI: High Explosive Incendiary
projectile weight: 360 grams
velocity: 3425 ft/sec
Note: The standard ammunition mixture for anti-armor use is a four-to-one mix of PGU-14/B and PGU-13/B rounds.
-->
<weight x="-4.91" y="0" z="0.0" size="0" mass-prop="yasim/weights/ammunition-weight-lbs"/>
<!-- Stations, weight is dynamicly configured while choosing the weapons,
drag should be too, but it's not possible yet in YASim-->
<weight x="-7.56" y="5.90" z="0.00"
size="0.25"
mass-prop="sim/weight[0]/weight-lb"/><!-- #1 extern L-->
<weight x="-7.56" y="4.83" z="-0.22"
size="0.25"
mass-prop="sim/weight[1]/weight-lb"/>
<weight x="-7.56" y="3.62" z="-0.37"
size="0.25"
mass-prop="sim/weight[2]/weight-lb"/>
<weight x="-7.56" y="1.69" z="-0.44"
size="0.25"
mass-prop="sim/weight[3]/weight-lb"/>
<weight x="-7.56" y="0.56" z="-0.44"
size="0.25"
mass-prop="sim/weight[4]/weight-lb"/><!--fuse L-->
<weight x="-7.56" y="0.00" z="-0.44"
size="0.25"
mass-prop="sim/weight[5]/weight-lb"/><!--center-->
<weight x="-7.56" y="-0.56" z="-0.44"
size="0.25"
mass-prop="sim/weight[6]/weight-lb"/><!--fuse R-->
<weight x="-7.56" y="-1.69" z="-0.44"
size="0.25"
mass-prop="sim/weight[7]/weight-lb"/>
<weight x="-7.56" y="-3.62" z="-0.37"
size="0.25"
mass-prop="sim/weight[8]/weight-lb"/>
<weight x="-7.56" y="-4.83" z="-0.22"
size="0.25"
mass-prop="sim/weight[9]/weight-lb"/>
<weight x="-7.56" y="-5.9" z="0.00"
size="0.25"
mass-prop="sim/weight[10]/weight-lb"/><!-- #11 extern R-->
<weight x="-7.56" y="-5.9" z="0.00"
size="0.25"
mass-prop="sim/weight[11]/weight-lb"/><!-- #11 extern R-->
</airplane>