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mv22.xml
376 lines (306 loc) · 22.8 KB
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mv22.xml
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<?xml version="1.0" encoding="UTF-8"?>
<!-- VMX-22 Version - 28.08.2010 -->
<!--
Sources:
[1] http://www.boeing.com/boeing/rotorcraft/military/v22/v22spec.page
[2] http://www.boeing.com/assets/pdf/rotorcraft/military/v22/docs/V-22_overview.pdf
[3] https://en.wikipedia.org/wiki/V-22#Specifications_.28MV-22B.29
[4] http://www.globalsecurity.org/military/systems/aircraft/v-22-specs.htm
[5] http://www.bellhelicopter.com/MungoBlobs/126/268/V-22%20Guidebook%202013_update_PREVIEW_LR2.pdf (conversion corridor, page 29)
[6] http://www.boeing.com/ospreynews/2011/issue_02/final_2011_2012_guidebook.pdf (performance, page 30)
[7] http://www.defensenews.com/article/20130916/DEFREG02/309160009/Rolls-Royce-Boosts-Power-V-22-Engines?odyssey=mod_sectionstories
[8] http://www.rolls-royce.com/defence/products/tactical_aircraft/ae_1107/
[9] http://www.globalsecurity.org/military/systems/aircraft/v-22-fuel.htm
[10] http://www.fas.org/man/dod-101/sys/ac/docs/99-033.pdf
[11] http://trace.tennessee.edu/cgi/viewcontent.cgi?article=3171&context=utk_gradthes
-->
<!--
Empty weight: 33140 lbs
-->
<airplane mass="33140" version="YASIM_VERSION_32">
<approach speed="85" aoa="6">
<control-setting axis="/sim/model/v22/tilt" value="90"/>
<control-setting axis="/sim/model/v22/wing/flap" value="0.5"/>
<control-setting axis="/controls/gear/gear-down" value="1.0"/>
<solve-weight idx="0" weight="180"/>
<solve-weight idx="1" weight="180"/>
</approach>
<!--
275 KTAS at sea level, 305 KTAS at 15000 ft
Sources:
- [3]
Original value VMX-22 speed = 275
-->
<cruise speed="305" alt="15000">
<control-setting axis="/sim/model/v22/tilt" value="90"/>
<control-setting axis="/sim/model/v22/wing/flap" value="0.0"/>
<control-setting axis="/controls/gear/gear-down" value="0.0"/>
<solve-weight idx="0" weight="180"/>
<solve-weight idx="1" weight="180"/>
</cruise>
<!-- main == right rotor D (name=main for mp-protocol)-->
<!-- tail == left rotor G (name=tail for mp-protocol)-->
<!-- mintiltpitch=" -180" maxtiltpitch="180" tiltcenterx="2.48" tiltcentery="-2.1" tiltcenterz="0.12" -->
<rotor name="main" x="1.57" y="-7.041" z="2.550" nx="0.0" ny="0" nz="1." fx="1" fy="0" fz="0" ccw="1"
maxcollective="180" mincollective="-180" mincyclicele="-90" maxcyclicele="90" mincyclicail="-90" maxcyclicail="90"
mintiltpitch="-180" maxtiltpitch="180" tiltcenterx="1.75" tiltcentery="-7.041" tiltcenterz="0.30"
mintiltroll="-90" maxtiltroll="90"
diameter="11.58" numblades="3" weightperblade="675" twist="-47.5" chord="0.81" rpm="397" relbladecenter="0.5" dynamic="1"
rellenflaphinge="0.13" delta3="-0.26" delta=".25" pitch-a="10" pitch-b="15" flapmin="-15" flapmax="15" flap0="-2" flap0factor="0"
notorque="0" dragfactor="0.30" translift-ve="20" translift-maxfactor="1.3" ground-effect-constant="0.1" taper="1"
number-of-segments="8" number-of-parts="8" rel-len-where-incidence-is-measured="0.6" rel-len-blade-start="0.16"
airfoil-lift-coefficient="3.15" airfoil-drag-coefficient0="0.38" airfoil-drag-coefficient1="5.5" incidence-stall-zero-speed="65"
incidence-stall-half-sonic-speed="55.0" lift-factor-stall="0.45" stall-change-over="11" drag-factor-stall="4.0"
cyclic-factor="0.8" rotor-correction-factor="1.7" balance="1" downwashfactor="0.3" phi0="95">
<control-input axis="/sim/model/v22/tilt" control="TILTPITCH" src0="-180.0" src1="180.0" dst0="1.0" dst1="-1.0"/>
<control-input axis="/sim/model/v22/rotor/right/elevator" control="CYCLICELE" src0="-90.0" src1="90.0" dst0="-1.0" dst1="1.0"/>
<control-input axis="/sim/model/v22/rotor/right/aileron" control="CYCLICAIL" src0="-90.0" src1="90.0" dst0="-1.0" dst1="1.0"/>
<control-input axis="/sim/model/v22/rotor/right/collective" control="COLLECTIVE" src0="-180.0" src1="180.0" dst0="-1" dst1="1.0"/>
</rotor>
<!-- mintiltpitch=" -180" maxtiltpitch="180" tiltcenterx="2.48" tiltcentery="2.1" tiltcenterz="0.12" -->
<rotor name="tail" x="1.57" y="7.041" z="2.550" nx="0.0" ny="0" nz="1." fx="1" fy="0" fz="0" ccw="0"
maxcollective="180" mincollective="-180" mincyclicele="-90" maxcyclicele="90" mincyclicail="-90" maxcyclicail="90"
mintiltpitch="-180" maxtiltpitch="180" tiltcenterx="1.75" tiltcentery="7.041" tiltcenterz="0.30"
mintiltroll="-90" maxtiltroll="90"
diameter="11.58" numblades="3" weightperblade="675" twist="-47.5" chord="0.81" rpm="397" relbladecenter="0.5" dynamic="1"
rellenflaphinge="0.13" delta3="-0.26" delta=".25" pitch-a="10" pitch-b="15" flapmin="-15" flapmax="15" flap0="-2" flap0factor="0"
notorque="0" dragfactor="0.30" translift-ve="20" translift-maxfactor="1.3" ground-effect-constant="0.1" taper="1"
number-of-segments="8" number-of-parts="8" rel-len-where-incidence-is-measured="0.6" rel-len-blade-start="0.16"
airfoil-lift-coefficient="3.15" airfoil-drag-coefficient0="0.38" airfoil-drag-coefficient1="5.5" incidence-stall-zero-speed="65"
incidence-stall-half-sonic-speed="55.0" lift-factor-stall="0.45" stall-change-over="11" drag-factor-stall="4.0"
cyclic-factor="0.8" rotor-correction-factor="1.7" balance="1" downwashfactor="0.3" phi0="95">
<control-input axis="/sim/model/v22/tilt" control="TILTPITCH" src0="-180.0" src1="180.0" dst0="1.0" dst1="-1.0"/>
<control-input axis="/sim/model/v22/rotor/left/elevator" control="CYCLICELE" src0="-90.0" src1="90.0" dst0="-1.0" dst1="1.0"/>
<control-input axis="/sim/model/v22/rotor/left/aileron" control="CYCLICAIL" src0="-90.0" src1="90.0" dst0="-1.0" dst1="1.0"/>
<control-input axis="/sim/model/v22/rotor/left/collective" control="COLLECTIVE" src0="-180.0" src1="180.0" dst0="-1" dst1="1.0"/>
</rotor>
<!--
6150 SHP = 4586 kW
7195 SHP = 5365 kW (+ 17 %)
9066 SHP = 6761 kW (+ 26 %)
Sources:
- [7] (Mentions 17 % Block 3 and 10000 SHP for Block 4)
- [8] (The overview says 7000 SHP (13 % increase), but the
specification says 7650 SHP (24 %) and 9000 SHP (17 %), so
the second number (7650 SHP) seems too high to me)
Original value VMX-22 max-power-engine-real = 9172
Warning: I haven't modified max-power-engine and max-power-rotor-brake!
-->
<rotorgear max-power-engine="131720"
max-power-rotor-brake="4850"
rotorgear-friction="30"
engine-prop-factor="0.015"
engine-accel-limit="4"
yasimdragfactor="270"
yasimliftfactor="28">
<control-input axis="/controls/engines/engine[0]/magnetos" control="ROTORGEARENGINEON"/>
<control-input axis="/controls/rotor/brake" control="ROTORBRAKE" src0="0.0" src1="1.0" dst0="0.0" dst1="1.0"/>
<control-input axis="/controls/rotor/reltarget" control="ROTORRELTARGET"
src0="0.0" src1="2.0"
dst0="0.0" dst1="2.0"/>
<control-input axis="/controls/rotor/maxreltorque" control="ROTORENGINEMAXRELTORQUE"
src0="0.0" src1="2.0"
dst0="0.0" dst1="2.0"/>
</rotorgear>
<!-- fuselage -->
<cockpit x="-1.88" y=".33" z="0.6"/>
<!-- air refueling fuselage -->
<!-- main fuselage front-->
<fuselage ax="8.1" ay="0" az="-1.9" bx="5.8" by="0" bz="-1.4" width="2.2" taper="0.25" midpoint="1.0" cx="0.15" cy="0.15" cz="0.35" idrag="0"/>
<!-- main fuselage center -->
<fuselage ax="6.0" ay="0" az="-1.4" bx="-2.5" by="0" bz="-1.4" width="2.3" taper="0.95" midpoint="0.5" cx="0.35" cy="1.6" cz="0.35" idrag="0"/>
<!-- top fuselage -->
<fuselage ax="1.0" ay="0" az="-0.8" bx="-2.5" by="0" bz="-0.8" width="2.3" taper="0.40" midpoint="0.0" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="3.0" ay="0" az="-0.8" bx="1.00" by="0" bz="-0.8" width="2.3" taper="1.00" midpoint="0.5" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="4.0" ay="0" az="-0.8" bx="3.00" by="0" bz="-0.8" width="2.3" taper="0.40" midpoint="1.0" cx="0.15" cy="0.15" cz="0.35" idrag="0"/>
<!-- top fuselage right wingbase-->
<fuselage ax="3.2" ay="-0.2" az="-0.0" bx="2.20" by="-0.7" bz="0.0" width="0.5" taper="0.40" midpoint="1.0" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="2.2" ay="-0.7" az="-0.0" bx="0.00" by="-0.7" bz="0.0" width="0.5" taper="1.00" midpoint="0.5" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="0.0" ay="-0.7" az="-0.0" bx="-1.20" by="-0.2" bz="-0.2" width="0.5" taper="0.40" midpoint="0.0" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="3.2" ay="-0.5" az="-0.0" bx="2.20" by="-1.0" bz="0.0" width="0.5" taper="0.40" midpoint="1.0" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="2.2" ay="-1.0" az="-0.0" bx="0.00" by="-1.0" bz="0.0" width="0.5" taper="1.00" midpoint="0.5" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="0.0" ay="-1.0" az="-0.0" bx="-1.20" by="-0.4" bz="-0.2" width="0.5" taper="0.40" midpoint="0.0" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<!-- top fuselage left wingbase-->
<fuselage ax="3.2" ay="0.2" az="-0.0" bx="2.20" by="0.7" bz="0.0" width="0.5" taper="0.40" midpoint="1.0" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="2.2" ay="0.7" az="-0.0" bx="0.00" by="0.7" bz="0.0" width="0.5" taper="1.00" midpoint="0.5" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="0.0" ay="0.7" az="-0.0" bx="-1.20" by="0.2" bz="-0.2" width="0.5" taper="0.40" midpoint="0.0" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="3.2" ay="0.5" az="-0.0" bx="2.20" by="1.0" bz="0.0" width="0.5" taper="0.40" midpoint="1.0" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="2.2" ay="1.0" az="-0.0" bx="0.00" by="1.0" bz="0.0" width="0.5" taper="1.00" midpoint="0.5" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<fuselage ax="0.0" ay="1.0" az="-0.0" bx="-1.20" by="0.4" bz="-0.2" width="0.5" taper="0.40" midpoint="0.0" cx="0.015" cy="0.15" cz="0.35" idrag="0"/>
<!-- side fuselage right-->
<fuselage ax="3.0" ay="-0.75" az="-2.1" bx="1.0" by="-1.75" bz="-2.1" width="0.8" taper="1.0" midpoint="0.5" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="1.2" ay="-1.70" az="-2.1" bx="-1.5" by="-1.70" bz="-2.1" width="0.8" taper="1.0" midpoint="0.5" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="1.7" ay="-1.0" az="-2.1" bx="-1.5" by="-1.0" bz="-2.1" width="0.8" taper="1.0" midpoint="0.5" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="-1.3" ay="-1.70" az="-2.1" bx="-3.8" by="-0.70" bz="-1.6" width="0.8" taper="1.0" midpoint="0.5" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<!-- side fuselage left-->
<fuselage ax="3.0" ay="0.75" az="-2.1" bx="1.0" by="1.75" bz="-2.1" width="0.8" taper="1.0" midpoint="0.5" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="1.2" ay="1.70" az="-2.1" bx="-1.5" by="1.70" bz="-2.1" width="0.8" taper="1.0" midpoint="0.5" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="1.7" ay="1.0" az="-2.1" bx="-1.5" by="1.0" bz="-2.1" width="0.8" taper="1.0" midpoint="0.5" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="-1.3" ay="1.70" az="-2.1" bx="-3.8" by="0.70" bz="-1.6" width="0.8" taper="1.0" midpoint="0.5" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<!-- back fuselage -->
<fuselage ax="-2.3" ay="0" az="-1.4" bx="-5.0" by="-0.45" bz="-1.03" width="2.2" taper="0.55" midpoint="0.0" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="-2.3" ay="0" az="-1.4" bx="-5.0" by="0" bz="-1.03" width="2.2" taper="0.55" midpoint="0.0" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="-2.3" ay="0" az="-1.4" bx="-5.0" by="0.45" bz="-1.03" width="2.2" taper="0.55" midpoint="0.0" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="-4.8" ay="-0.45" az="-1.05" bx="-6.5" by="-0.75" bz="-0.5" width="1.3" taper="0.35" midpoint="0.0" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="-4.8" ay="0" az="-1.05" bx="-6.5" by="0" bz="-0.5" width="1.3" taper="0.35" midpoint="0.0" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="-4.8" ay="0.45" az="-1.05" bx="-6.5" by="0.75" bz="-0.5" width="1.3" taper="0.35" midpoint="0.0" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="-6.4" ay="-0.75" az="-0.51" bx="-7.7" by="-0.75" bz="-0.4" width="0.45" taper="0.35" midpoint="0.0" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="-6.4" ay="0" az="-0.51" bx="-7.7" by="0" bz="-0.4" width="0.45" taper="0.35" midpoint="0.0" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<fuselage ax="-6.4" ay="0.75" az="-0.51" bx="-7.7" by="0.75" bz="-0.4" width="0.45" taper="0.35" midpoint="0.0" cx="0.015" cy="1" cz="0.35" idrag="0"/>
<!-- left engine x="1.57" y="7.041" z="2.550"
<fuselage ax="1.57" ay="7.041" az="2.550" bx="1.77" by="7.041" bz="-1.83" width="1.2" taper="0.45" midpoint="0.5" cx="0.0" cy="0" cz="0.0" idrag="0"/>
<fuselage ax="2.20" ay="7.041" az="1.800" bx="2.20" by="7.041" bz="-1.83" width="1.0" taper="0.65" midpoint="0.5" cx="0.0" cy="0" cz="0.0" idrag="0"/>-->
<!-- right engine x="1.57" y="-7.041" z="2.550"
<fuselage ax="1.57" ay="-7.041" az="2.550" bx="1.77" by="-7.041" bz="-1.83" width="1.2" taper="0.45" midpoint="0.5" cx="0.0" cy="0" cz="0.0" idrag="0"/>
<fuselage ax="2.20" ay="-7.041" az="1.800" bx="2.20" by="-7.041" bz="-1.83" width="1.0" taper="0.65" midpoint="0.5" cx="0.0" cy="0" cz="0.0" idrag="0"/>-->
<!-- Main wing has a forward sweep of 6 degrees and a dihedral of
3.5 degrees according to [11].
Incidence and camber lowered to some guessed numbers to get a nose up
of 3 to 5 degrees during level flight.
Original value VMX-22 incidence = 3.5 and camber = 0.2
-->
<wing x="0.90" y="0.4" z="0.30" chord="2.65" chord_real="2.65" taper="1.0" length_real="6.1" length="6.1" dihedral="3.5" incidence="0.5" camber="0.15" sweep="-6">
<stall width="8" aoa="35" peak="1.5"/>
<flap0 drag="1.6" end="0.5" lift="2" start="0.02"/>
<flap1 drag="1.6" end="0.97" lift="2" start="0.5"/>
<control-input control="FLAP0" axis="/sim/model/v22/wing/flap"/>
<control-input control="FLAP1" axis="/sim/model/v22/wing/flap"/>
<control-input control="FLAP1" split="true" axis="sim/model/v22/wing/aileron"/>
<control-output prop="/surface-positions/flap-pos-norm" control="FLAP0"/>
<control-output prop="/surface-positions/left-aileron-pos-norm" side="left" control="FLAP1"/>
<control-output prop="/surface-positions/right-aileron-pos-norm" side="right" control="FLAP1"/>
</wing>
<!--
<wing x="1.91" y="0.6" z="0.39" chord="2.35" chord_real="2.35" taper="1.0" length_real="5.4" length="5.4" dihedral="3" incidence="3.5" camber="0.2" sweep="-8">
-->
<!-- Vertical wing - rudder -->
<vstab x="-7.90" y="2.52" z="-1.39" taper="0.4" length="3.20" chord="2.72" sweep="15" incidence="0">
<stall aoa="16" width="4" peak="1.5"/>
<flap0 drag="1.2" end="1" lift="1.4" start="0.4"/>
<control-input control="FLAP0" axis="/sim/model/v22/wing/rudder" invert="true"/>
<control-output prop="/surface-positions/rudder-pos-norm" control="FLAP0" min="1" max="-1"/>
</vstab>
<vstab x="-7.90" y="-2.52" z="-1.39" taper="0.4" length="3.20" chord="2.72" sweep="15" incidence="0">
<stall aoa="16" width="4" peak="1.5"/>
<flap0 drag="1.2" end="1" lift="1.4" start="0.4"/>
<control-input control="FLAP0" axis="/sim/model/v22/wing/rudder" invert="true"/>
<control-output prop="/surface-positions/rudder-pos-norm" control="FLAP0" min="1" max="-1"/>
</vstab>
<mstab x="-8.40" y="0.0" z="-0.45" taper="1.0" length="2.50" chord="2.30" sweep="0" incidence="-0.5">
<stall aoa="16" width="4" peak="1.5"/>
<flap0 drag="1.2" end="1" lift="1.9" start="0"/>
<control-input control="FLAP0" axis="/sim/model/v22/wing/elevator"/>
<control-output prop="/surface-positions/elevator-pos-norm" control="FLAP0"/>
</mstab>
<!-- Front gear -->
<gear x="7.105" y="0" z="-3.212" compression="0.4" spring="0.65" damp="0.4">
<control-input axis="/controls/gear/brake-right" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-left" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
<control-input axis="/controls/flight/rudder" control="STEER" square="true" src0="-1.0" src1="1.0" dst0="-1.0" dst1="1.0"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-speed control="EXTEND" transition-time="5"/>
<control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
</gear>
<!-- Left gear -->
<gear x="-1.118" y="2.101" z="-3.258" compression="0.4" spring="0.65" damp="0.4">
<control-input axis="/controls/gear/brake-left" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-speed control="EXTEND" transition-time="5.1"/>
<control-output control="EXTEND" prop="/gear/gear[1]/position-norm"/>
</gear>
<!-- Right gear -->
<gear x="-1.118" y="-2.101" z="-3.258" compression="0.4" spring="0.65" damp="0.4">
<control-input axis="/controls/gear/brake-right" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-speed control="EXTEND" transition-time="5.2"/>
<control-output control="EXTEND" prop="/gear/gear[2]/position-norm"/>
</gear>
<!-- CRASH LANDING FX - left skid -->
<gear x=" 6.00" y="+1.00" z="-2.50" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<gear x="-2.4" y="+1.00" z="-2.50" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<!-- CRASH LANDING FX - left skid -->
<gear x=" 6.00" y="-1.00" z="-2.50" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<gear x="-2.4" y="-1.00" z="-2.50" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<!-- CRASH FX - right ruder skid -->
<gear x="-7.50" y="+2.50" z="-1.38" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<gear x="-9.00" y="+2.50" z="-1.32" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<!-- CRASH FX - left ruder skid -->
<gear x="-7.50" y="-2.50" z="-1.38" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<gear x="-9.00" y="-2.50" z="-1.32" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<!-- CRASH FX - right engine skid ax="1.57" ay="7.041" az="2.550" -->
<gear x=" 2.52" y="-7.441" z="-1.87" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<gear x=" 1.40" y="-7.241" z="-1.87" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<!-- CRASH FX - left engine skid ax="1.57" ay="7.041" az="2.550" -->
<gear x=" 2.52" y="+7.441" z="-1.87" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<gear x=" 1.40" y="+7.241" z="-1.87" skid="1" compression="0.10" spring="0.8" sfric="0.7" dfric="0.6" ignored-by-solver="1"/>
<!-- Forward sponson tanks
2x 478 gal or 2x 3250 lbs
-->
<tank x="1.6" y="+1.4" z="-2.1" jet="true" capacity="3250"/>
<tank x="1.6" y="-1.4" z="-2.1" jet="true" capacity="3250"/>
<!-- Wing feeder tanks
2x 88 gal or 2x 600 lbs
Maximum capacity is 640 lbs, but required to stay at 600 lbs.
-->
<tank x="1.9" y="+5.8" z="0.3" jet="true" capacity="600"/>
<tank x="1.9" y="-5.8" z="0.3" jet="true" capacity="600"/>
<!-- Note: CV-22B has additionally: Wing auxilliary tanks
2x 296 gal (8 * 74) or 2015 lbs (8 * 504)
MV-22B does not have these!
-->
<!-- Aft sponson tank
1x 305 gal or 1x 2075 lbs
-->
<tank x="-1.9" y="-1.4" z="-2.1" jet="true" capacity="2075"/>
<!-- Optional MATS tanks
480 gal or 3264 lbs each ([3], [5] and [6])
or 800 gal or 5450 lbs [9]
or 4000 lbs [10]
Not sure about the y and z coordinates of the two forward
tanks. For now I'm assuming the two tanks are on top of
each other.
-->
<tank x="1.2" y="0" z="-1.5" jet="true" capacity="2350"/>
<tank x="1.2" y="0" z="-0.6" jet="true" capacity="2350"/>
<tank x="0.0" y="0" z="-1.5" jet="true" capacity="2200"/>
<!--
If we assume CV-22B has two additional wing auxilliary tanks ([9], [10]), we get for MV-22B:
2*478 + 2*88 + 1*305 = 1437 gal (instead of the 1721 gal mentioned by [5] and [6])
If we instead assume CV-22B has just the one additional sponson (aft) tank,
we get for MV-22B:
2*478 + 2*88 + 2*296 = 1724 gal (close to what [5] and [6] say)
and for the CV-22B:
2*478 + 2*88 + 2*296 + 1*305 = 2029 gal (close to what [3], [5], and [6] say)
-->
<!--
Ballast corection CG x: 1.530
Original value VMX-22 CG: x:1.519
-->
<ballast x="8" y="0" z="0" mass="8500"/>
<!-- Engine weight: 971 lbs, add some lbs for hydraulics and ... -->
<ballast x="1.91" yr="6" y="7" z="0.39" mass="1000"/>
<ballast x="1.91" yr="-6" y="-7" z="0.39" mass="1000"/>
<!-- Gear weight: 230 lbs, add some lbs for hydraulics and ... -->
<ballast x="7.10" yr="0" y="0.0" z="-2.20" mass="180"/>
<ballast x="-1.10" yr="6" y="2.1" z="-2.40" mass="230"/>
<ballast x="-1.10" yr="-6" y="-2.1" z="-2.40" mass="230"/>
<!-- Pilot -->
<weight x="6.0" y="0.60" z="-1.3" mass-prop="/sim/weight[0]/weight-lb"/>
<!-- Co-pilot -->
<weight x="6.0" y="-0.60" z="-1.3" mass-prop="/sim/weight[1]/weight-lb"/>
<!-- Cabin crew -->
<weight x="4.2" y="-0.60" z="-1.5" mass-prop="/sim/weight[2]/weight-lb"/>
<!-- Load -->
<weight x="0.20" y="0" z="-1.9" mass-prop="/sim/weight[3]/weight-lb"/>
<!-- Pushback -->
<thruster x="7.105" y="0" z="-3.212" vx="1" vy="0" vz="0" thrust="5200">
<control-input axis="/sim/model/pushback/target-speed-fps" control="THROTTLE" src0="-1" src1="1" dst0="-1" dst1="1"/>
</thruster>
<!-- Hitch -->
<hitch name="aerotow" x="-3.1" y="0.0" z="-2.525" force-is-calculated-by-other="1">
<tow length="30" weight-per-meter="0.035" elastic-constant="9000" break-force="80000" mp-auto-connect-period="1.0"/>
</hitch>
</airplane>