/
ec135-test.xml
238 lines (190 loc) · 7.77 KB
/
ec135-test.xml
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<!-- official RD + x.xx m = yasim RD (reference datum) -->
<!-- FDM based also on information given in NASA-CR-3144; TR-1087-1-->
<airplane mass="3268">
<approach speed="47" aoa="16">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
</approach>
<cruise speed="137" alt="0">
<control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
</cruise>
<!--cyclicele control way: 21.8deg/ 215mm
cyclicail control way: 15deg/ 160mm-->
<rotor name="main" x="-2.75" y="0.0" z="1.55"
nx="0.087" ny="0" nz="1." fx="1" fy="0" fz="0" ccw="1"
maxcollective="16.25" mincollective="0.2"
mincyclicele="-9.6" maxcyclicele="12.2"
mincyclicail="-6.42" maxcyclicail="8.58"
diameter="10.2"
numblades="4"
weightperblade="65"
relbladecenter="0.5"
dynamic="0.75" rpm="395" phi0="45"
rellenflaphinge="0.09" delta3="0"
delta=".20"
pitch-a="10"
pitch-b="15"
flapmin="-13"
flapmax="13"
flap0="-5"
flap0factor="0"
notorque="0"
dragfactor="0.30"
translift-ve="13"
translift-maxfactor="1.55"
ground-effect-constant="0.15"
twist="-10.2"
taper="1"
chord="0.27"
number-of-segments="8"
number-of-parts="8"
rel-len-where-incidence-is-measured="0.7"
rel-len-blade-start="0.08"
airfoil-lift-coefficient="6.4"
airfoil-drag-coefficient0="0.0054"
airfoil-drag-coefficient1="0.086"
incidence-stall-zero-speed="16"
incidence-stall-half-sonic-speed="15.5"
lift-factor-stall="0.18"
stall-change-over="5.5"
drag-factor-stall="2.0"
cyclic-factor="0.8"
rotor-correction-factor="0.8"
downwashfactor="0.3"
>
<control-input axis="/controls/flight/aileron-trim" control="CYCLICAIL"/>
<control-input axis="/controls/flight/fcs/roll" control="CYCLICAIL"
src0="-1.0" src1="1.0"
dst0="-1.0" dst1="1.0"/>
<control-input axis="/controls/flight/elevator-trim" control="CYCLICELE"/>
<control-input axis="/controls/flight/fcs/pitch" control="CYCLICELE"
src0="-1.0" src1="1.0"
dst0="-1.0" dst1="1.0"/>
<control-input axis="/controls/engines/engine[0]/throttle" control="COLLECTIVE"
src0="0.0" src1="1.0"
dst0="1.0" dst1="-1"/>
</rotor>
<rotor name="tail" x="-8.855" y="-0.102" z="0.696"
nx="0.0" ny="-1" nz="0.0" fx="1" fy="0" fz="0" ccw="1"
maxcollective="34.2" mincollective="-16.8"
diameter="1" numblades="10" weightperblade="0.64" relbladecenter="0.7"
dynamic="1" rpm="3584" rellenflaphinge="0.0" delta3="0" translift="0" delta="0.5" twist="-7.0"
pitch-a="10"
pitch-b="15"
airfoil-lift-coefficient="6.4"
airfoil-drag-coefficient0="0.0053"
airfoil-drag-coefficient1="0.20"
notorque="0"
taper="1"
chord="0.05"
number-of-segments="8"
number-of-parts="8"
rel-len-blade-start="0.35"
incidence-stall-zero-speed="28"
incidence-stall-half-sonic-speed="27"
lift-factor-stall="0.18"
stall-change-over="5.5"
drag-factor-stall="8"
rotor-correction-factor="0.8"
downwashfactor="0.5"
>
<control-input axis="/controls/flight/fcs/yaw" control="COLLECTIVE" invert="true"
src0="-1.0" src1="1.0"
dst0="-1.0" dst1="1.0"/>
<control-input axis="/controls/flight/fcs/tail-rotor/throttle" control="COLLECTIVE"
src0="0.0" src1="1.0"
dst0=".00000000000000000065" dst1=".00000000000000000065"/>
</rotor>
<rotorgear
max-power-engine="926"
max-power-rotor-brake="100"
rotorgear-friction="1.4"
engine-prop-factor="0.005"
engine-accel-limit="100"
yasimdragfactor="60"
yasimliftfactor="12"
>
<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>
<cockpit x="-1.88" y=".33" z="0.6"/>
<!--set cz="2.5" to improve autorotation behavior and climbrate perfoamnce-->
<fuselage ax="0.201" ay="0" az="-.4" bx="-5.3" by="0" bz="-.07" cz="-2.5"
width="1.92" taper="0.95" midpoint="0.5" idrag="0"/>
<fuselage ax="-5.254" ay="0" az="0.445" bx="-9.7" by="0" bz=".51" cz="0.25" cx="3"
width="0.47" taper="0.9" midpoint="0.05" idrag="0.0"/>
<vstab x="-8.933" y="0" z="1.389"
taper=".5"
length="1.0"
chord="1.2"
sweep="15"
incidence="7">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<vstab x="-7.4" y="1.27" z=".12"
taper="1"
length=".65"
chord=".40"
incidence="7"
sweep="20">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<vstab x="-7.4" y="-1.27" z=".12"
taper="1"
length=".65"
chord=".40"
incidence="7"
sweep="20">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<hstab x="-7.4" y="0.05" z="0.43" taper="1.0" effectiveness="2.0" length="1.30" chord="0.36" sweep="0" incidence="30">
<stall aoa="0" width="0" peak="1.5"/>
</hstab>
<!-- left skid -->
<gear x="-0.96" y="+1.00" z="-1.65" skid="1" compression="0.1" spring="0.8" sfric="0.5" dfric="0.4"/>
<gear x="-3.6" y="+1.00" z="-1.51" skid="1" compression="0.1" spring="0.8" sfric="0.5" dfric="0.5"/>
<!-- right skid -->
<gear x="-0.96" y="-1.00" z="-1.65" skid="1" compression="0.1" spring="0.8" sfric="0.5" dfric="0.4"/>
<gear x="-3.6" y="-1.00" z="-1.51" skid="1" compression="0.1" spring="0.8" sfric="0.5" dfric="0.4"/>
<!-- tail skid -->
<gear x="-8.756" y="+0.00" z="-0.35" skid="1" compression="0.01" spring="0.1" sfric="1" dfric="1"/>
<gear x="-9.389" y="+0.00" z="-0.20" skid="1" compression="0.01" spring="0.1" sfric="1" dfric="1"/>
<tank x="-2.69" y="0" z="-.945" capacity="1006"/> <!-- main: 580 l (570 l usable) @ 6.682 ppg (H3EU.pdf) -->
<tank x="-3.467" y="0" z="-.945" capacity="163.7"/> <!-- supply: 93 l (usable?) -->
<!--<tank x="-1.74" y="0" z=".68" capacity="163.7"/> --><!-- supply: 93 l (usable?) -->
<ballast x="-4.00" y="+0.0" z="0.2" mass="600"/>
<ballast x="-4.4" y="+0.0" z="0.5" mass="300"/>
<ballast x=" -3.4" y="-2.25" z="0.9" mass="150"/>
<ballast x="-3.4" y="+2.25" z="0.9" mass="150"/>
<ballast x="-3.5" y="0" z="1.60" mass="200"/>
<ballast x="-3.5" y="0" z="-1.60" mass="200"/>
<ballast x="-0.4" y="+0.0" z="-0.8" mass="800"/>
<ballast x="1.40" y="0" z=".68" mass="-182"/>
<ballast x="-4.40" y="0" z=".68" mass="-182"/>
<weight x="-1.0" y="-.33" z="-0.599" mass-prop="/sim/weight[0]/weight-lb"/> <!-- pilot -->
<weight x="-1.0" y=".33" z="-0.599" mass-prop="/sim/weight[1]/weight-lb"/> <!-- co-pilot -->
<weight x="-1.68" y="-.33" z="-0.599" mass-prop="/sim/weight[2]/weight-lb"/> <!-- right passenger -->
<weight x="-1.68" y="0" z="-0.599" mass-prop="/sim/weight[3]/weight-lb"/> <!-- middle passenger -->
<weight x="-1.68" y=".33" z="-0.599" mass-prop="/sim/weight[4]/weight-lb"/> <!-- left passenger -->
<weight x="-3.5" y="0" z="-0.599" mass-prop="/sim/weight[5]/weight-lb"/> <!-- patient/load -->
<thruster x="-2.55" y="0.0" z="1.55" vx="1" vy="0" vz="0" thrust="1000">
<control-input axis="/rotors/main/vibration/longitudinal" src0="-1" src1="1" dst0="-1" dst1="1" control="THROTTLE"/>
</thruster>
<thruster x="-2.55" y="0.0" z="1.55" vx="0" vy="1" vz="0" thrust="1000">
<control-input axis="/rotors/main/vibration/lateral" src0="-1" src1="1" dst0="-1" dst1="1" control="THROTTLE"/>
</thruster>
<!-- residual thrust-->
<thruster x="-4.142" y="0.6" z="0.821" vx="-1" vy="0" vz="0" thrust="400">
<control-input axis="/engines/engine[0]/residualthrust" src0="0" src1="1" dst0="0" dst1="-1" control="THROTTLE"/>
</thruster>
<thruster x="-4.142" y="-0.6" z="0.821" vx="-1" vy="0" vz="0" thrust="400">
<control-input axis="/engines/engine[0]/residualthrust" src0="0" src1="1" dst0="0" dst1="-1" control="THROTTLE"/>
</thruster>
</airplane>