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ec135P2.xml
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ec135P2.xml
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<!--
This file is part of FlightGear, the free flight simulator
http://www.flightgear.org/
Copyright (C) 2009 Heiko Schulz, [email protected]
This program is free software; you can redistribute it and/or
modify it under the terms of the GNU General Public License as
published by the Free Software Foundation; either version 2 of the
License, or (at your option) any later version.
This program is distributed in the hope that it will be useful, but
WITHOUT ANY WARRANTY; without even the implied warranty of
MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
General Public License for more details.
-->
<!--EC135 P2
Max weight: 2835kg
Min weight: 1500kg (3307 lbs)
Empty weight: 3268 lbs (baseline: 3207lbs + margin )
Max Range: 450 nm
Length: 12.16m
width: 2.0m
width with hstab: 2.65m
Main Rotor diameter: 10.2m
Type: bearingless main rotor
Disc area: ?? sqm
Number of Blades: 4
Rotor speed: 395rpm
airfoil: DFVLR DM-H3 non-symmetrical -> Lift/drag curve needed
rellenflaphinge based on: http://www.uni-stuttgart.de/hkom/publikationen/themenheft/03/bansemir.pdf
Tail rotor diameter: 1m
Type: Fenestron (TM)
Number of Blades: 10
Rotor speed: 3584rpm
disc area: ?? sqm
airfoil: DFVLR DM-H4 non-symmetrical -> Lift/drag curve needed
A control input shows as reaction a typical curve. (image 12.1 in [1]) The gradient increase of the curve describes the Control Sensitivity.
t0.63 is a normed value to describe and compare the Control Sensitivity of helicopters. This describes the time until 63% of the max. (roll, nick, yaw)-rate
is reached per stick travel way. The unit of the sensitivity is 1/s inch.
According to Walter Bittner's Book Roll Control Sensitivity is 1,33 x higher (2.4 vs 1.8) compared with BO105.
That means the increase of the gradient is 1.33 steeper.
Bo105 has a t0.63 of about 0.13-0.14sec.
As said, the sensitivity depends on the travel way of the stick. The EC135 has 1.37 less way than the BO105. That would mean if both helis
would have the same stick travel way, the EC135 would have 3% less steep gradient of the curve. (1.33 /1.37 = 0.97). But as the EC135s t0,63 is 0,23
we get a much higher roll rate of about 120- 130deg per second!
Problem: for every helicopter in FGFS we would need own hardware with its own realistic travel way. Not possible right now, so there are three ways to deal with:
1.) assume that we have realistic hardware with correct travel ways dynamic="0.51" delta="0.18"
2.) assume that there is the same hardware used for the BO105- so change fdm values to higher max rollrate to give the same impression. dynamic="0.51" delta="0.125"
3.) increase sensitivity of the hardware via the way FGFS handles the hardware. (sensitivity x 1,37)
Fuel Capacity: 142.7 US gal = 540liters = 427kg
2 Pratt & Whitney PW 206 B2
max power: 557kw, power rating (MTOP): 747SHP
max continous: 543 kw, power rating (MCP): 728SHP
CoG from the Flight Manual:
Datum around 4200 mm forward of main rotor head center line.
CoG- between 4180mm and 4570mm from datum
Empty weight CoG at around 4500mm
Airspeed Limits Never Exceed Power on: 155 ktn
Maximum possible speed with maximum continous power: 14ktn
FDM based on datas from:
Flight Manual EC135 P2;
EC135 Training Manual;
NASA-CR-3144 (www.robertheffley.com/docs/Data/NASA%20CR-3144.pdf?); TR-1087-1;
various threads on pprune.org;
[1]http://www.springer.com/cda/content/document/cda_downloaddocument/9783540889717-c1.pdf?SGWID=0-0-45-693203-p173897906,
Dave's all the worlds fenestron
Type Certifications
EC 135 AMM
FDM still in the work as some more datas are missing but expected to come soon or later.
-->
<airplane mass="3207" version="YASIM_VERSION_32">
<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>
<!--cyclicail should be the way round?
-->
<rotor name="main" x="-2.973" y="0.0" z="1.751"
nx="0.087" ny="0" nz="1." fx="1" fy="0" fz="0" ccw="1"
maxcollective="17.3" mincollective="0.0"
mincyclicele="-7.8" maxcyclicele="14"
mincyclicail="-6.6" maxcyclicail="7.9"
diameter="10.2"
numblades="4"
weightperblade="83.7"
relbladecenter="0.5"
dynamic="0.51" rpm="395" phi0="45"
rellenflaphinge="0.09" delta3="0"
delta="0.18"
pitch-a="10"
pitch-b="15"
flapmin="-13"
flapmax="13"
flap0="-5"
flap0factor="0"
notorque="0"
dragfactor="0.30"
translift-ve="20"
translift-maxfactor="1.55"
ground-effect-constant="0.1"
twist="-10.2"
taper="1"
chord="0.30"
number-of-segments="8"
number-of-parts="8"
rel-len-where-incidence-is-measured="0.7"
rel-len-blade-start="0.29"
airfoil-incidence-no-lift="-0.1"
airfoil-lift-coefficient="4.55"
airfoil-drag-coefficient0="0.0074"
airfoil-drag-coefficient1="0.15"
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="1.1"
rotor-correction-factor="0.9"
downwashfactor="1.0"
>
<!--lst values: 1.35;0.1;-0.3;3.80;0.0074;0.04; to-do: play with lift-coeff and translift-factor-->
<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"/>
<!--without SAS-system
<control-input axis="/controls/flight/aileron-trim" control="CYCLICAIL"/>
<control-input axis="/controls/flight/aileron" 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/elevator" 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="-1.0"/>-->
</rotor>
<!--flapmin/max guessed from a real fenestron with 1-3degrees-->
<rotor name="tail" x="-8.844" y="-0.07" z="0.873"
nx="0.00" ny="-1" nz="0.00" fx="1" fy="0" fz="0" ccw="1"
maxcollective="34.2" mincollective="-16.8"
diameter="1" numblades="10" weightperblade="0.64" relbladecenter="0.5"
dynamic="1.4" rpm="3584" rellenflaphinge="0.35" delta3="0" translift="0" delta="0.5" twist="-7.0"
pitch-a="10"
pitch-b="15"
flapmin="-2.0"
flapmax="2.0"
flap0="0"
airfoil-lift-coefficient="5.1"
airfoil-drag-coefficient0="0.0074"
airfoil-drag-coefficient1="0.9"
notorque="0"
taper="1"
chord="0.05"
number-of-segments="5"
number-of-parts="4"
rel-len-blade-start="0.35"
airfoil-incidence-no-lift="-0.3"
incidence-stall-zero-speed="34"
incidence-stall-half-sonic-speed="33"
lift-factor-stall="0.18"
stall-change-over="5.5"
drag-factor-stall="8"
rotor-correction-factor="0.8"
downwashfactor="1.0"
>
<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" invert="true"
src0="0.0" src1="1.0"
dst0="0.0" dst1="1.0"/>
<!--without SAS-System
<control-input axis="/controls/flight/rudder-trim" control="COLLECTIVE" invert="true"/>
<control-input axis="/controls/flight/rudder" control="COLLECTIVE" invert="true"
src0="-1.0" src1="1.0"
dst0="-1.0" dst1="1.0"/>
-->
</rotor>
<rotorgear
max-power-engine="1218"
max-power-rotor-brake="100"
rotorgear-friction="5.2"
engine-prop-factor="0.015"
engine-accel-limit="100"
yasimdragfactor="22.5"
yasimliftfactor="25"
>
<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"/>
<fuselage ax="0.201" ay="0" az="-.162" bx="-5.3" by="0" bz="0.17" cx="3.0" cz="0.2"
width="1.92" taper="0.95" midpoint="0.5" idrag="0"/>
<fuselage ax="-5.262" ay="0" az="0.698" bx="-9.78" by="0" bz=".757" cz="0.25" cx="2.5"
width="0.47" taper="0.9" midpoint="0.05" idrag="0.0"/>
<!-- fin-->
<vstab x="-8.604" y="0" z="0.962"
taper=".6"
effectiveness="0.5"
length="1.7"
chord="1.3"
sweep="20"
incidence="5">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<!--bumper-->
<vstab x="-8.8928" y="0" z="0.538"
dihedral="-90"
taper=".5"
effectiveness="0.5"
length="0.65"
chord="1.3"
sweep="15"
incidence="-5">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<vstab x="-7.481" y="1.27" z=".672"
taper="0.7"
effectiveness="0.5"
length=".26"
chord=".50"
incidence="4"
sweep="22">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<vstab x="-7.481" y="1.27" z=".672"
taper="0.7"
effectiveness="0.5"
length="-.52"
chord=".50"
incidence="4"
sweep="-30">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<vstab x="-7.481" y="-1.27" z=".672"
taper="0.7"
effectiveness="0.5"
length=".26"
chord=".50"
incidence="4"
sweep="22">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<vstab x="-7.481" y="-1.27" z=".672"
taper="0.7"
effectiveness="0.5"
length="-.52"
chord=".50"
incidence="4"
sweep="-30">
<stall aoa="24" width="10" peak="1.5"/>
</vstab>
<!--changed incidence to -5, former -7-->
<hstab x="-7.44" y="0.05" z="0.715"
taper="1.0"
dihedral="0"
length="1.30"
chord="0.36"
sweep="0"
incidence="-5">
<stall aoa="27" width="0" peak="1.5"/>
</hstab>
<!-- left lowskid -->
<gear x="-1.09" y="+1.00" z="-1.348" skid="1" compression="0.1" spring="1.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<gear x="-3.792" y="+1.00" z="-1.201" skid="1" compression="0.1" spring="1.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<!-- right lowskid -->
<gear x="-1.09" y="-1.00" z="-1.348" skid="1" compression="0.1" spring="1.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<gear x="-3.792" y="-1.00" z="-1.201" skid="1" compression="0.1" spring="1.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<!-- left lowskid with floats-->
<gear x="-1.09" y="+1.00" z="-1.348" skid="1" compression="0.1" spring="1.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<gear x="-3.792" y="+1.00" z="-1.201" skid="1" compression="0.1" spring="1.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<gear x="-5.186" y="+1.00" z="-0.862" skid="1" compression="0.1" spring="1.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<control-input axis="/sim/model/ec135/longskid_floats" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[2]/position-norm"/>
<control-speed control="EXTEND" transition-time="0.1"/>
<!-- right lowskid with floast-->
<gear x="-1.09" y="-1.00" z="-1.348" skid="1" compression="0.1" spring="1.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<gear x="-3.792" y="-1.00" z="-1.201" skid="1" compression="0.1" spring="1.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<gear x="-5.186" y="-1.00" z="-0.862" skid="1" compression="0.1" spring="1.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<control-input axis="/sim/model/ec135/longskid_floats" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[3]/position-norm"/>
<control-speed control="EXTEND" transition-time="0.1"/>
<!-- left midskid -->
<gear x="-1.09" y="+1.00" z="-1.448" skid="1" compression="0.1" spring="2.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<control-input axis="/sim/model/ec135/midskid" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[4]/position-norm"/>
<control-speed control="EXTEND" transition-time="0.1"/>
<gear x="-3.792" y="+1.00" z="-1.301" skid="1" compression="0.1" spring="2.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<control-input axis="/sim/model/ec135/midskid" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[5]/position-norm"/>
<control-speed control="EXTEND" transition-time="0.1"/>
<!-- right midskid -->
<gear x="-1.09" y="-1.00" z="-1.448" skid="1" compression="0.1" spring="2.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<control-input axis="/sim/model/ec135/midskid" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[6]/position-norm"/>
<control-speed control="EXTEND" transition-time="0.1"/>
<gear x="-3.792" y="-1.00" z="-1.301" skid="1" compression="0.1" spring="2.5" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<control-input axis="/sim/model/ec135/midskid" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[7]/position-norm"/>
<control-speed control="EXTEND" transition-time="0.1"/>
<!-- left highskid -->
<gear x="-1.09" y="+1.00" z="-1.648" skid="1" compression="0.1" spring="3.7" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<control-input axis="/sim/model/ec135/highskid" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[8]/position-norm"/>
<control-speed control="EXTEND" transition-time="0.3"/>
<gear x="-3.792" y="+1.00" z="-1.501" skid="1" compression="0.1" spring="3.7" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<control-input axis="/sim/model/ec135/highskid" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[9]/position-norm"/>
<control-speed control="EXTEND" transition-time="0.3"/>
<!-- right highskid -->
<gear x="-1.09" y="-1.00" z="-1.648" skid="1" compression="0.1" spring="3.7" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<control-input axis="/sim/model/ec135/highskid" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[10]/position-norm"/>
<control-speed control="EXTEND" transition-time="0.3"/>
<gear x="-3.792" y="-1.00" z="-1.501" skid="1" compression="0.1" spring="3.7" damp="1.70" sfric="0.6" dfric="0.8" stiction="1"/>
<control-input axis="/sim/model/ec135/highskid" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[110]/position-norm"/>
<control-speed control="EXTEND" transition-time="0.3"/>
<!-- main: 474.5kg -->
<tank x="-2.69" y="0" z="-.945" capacity="1046"/>
<!-- Rsupply: 44.5kg (usable?) -->
<tank x="-3.467" y="0.16" z="-.945" capacity="98.12257"/>
<!-- Lsupply: 49.0kg (usable?) -->
<tank x="-1.74" y="-0.16" z=".68" capacity="108.045"/>
<!--CoG: -3.198, 0.0, 1.047
<ballast x="-4.15" y="+0.0" z="2.038" mass="588"/>
<ballast x="-4.55" y="+0.0" z="2.038" mass="294"/>
<ballast x=" -3.55" y="-1.95" z="1.738" mass="147"/>
<ballast x="-3.55" y="+1.95" z="1.738" mass="147"/>
<ballast x="-3.65" y="0" z="2.315" mass="196"/>
<ballast x="-3.65" y="0" z="2.368" mass="196"/>
<ballast x="-0.55" y="+0.0" z="1.038" mass="785"/>
<ballast x="0.35" y="0" z="2.518" mass="-178"/>
<ballast x="-3.65" y="0" z="2.518" mass="-178"/>
-->
<!-- ballast CoG: -3.198, 0.0, 0.328 ; Tensors: 1874, 6516, 6156
bo105weight= 2868 vs 3207;
xx: 1363.380 x 1.041 (x 1.265) x 1.16 = (2082.64) 1646.363
yy: 3977.918 x 1.041 x 1.157 x 1.16= 5557.73
zz: 3959.745 x 1.041 x 1.157 x 1.256= 5990.2
-->
<ballast x="-0.050" y="+0.0" z=" 0.528" mass="534.5"/>
<ballast x="-6.346" y="+0.0" z=" 0.528" mass="534.5"/>
<ballast x="-3.198" y="1.33" z=" 0.528" mass="534.5"/>
<ballast x="-3.198" y="-1.33" z=" 0.528" mass="534.5"/>
<ballast x="-3.198" y="+0.0" z="1.8438" mass="534.5"/>
<ballast x="-3.198" y="+0.0" z="-0.782" mass="534.5"/>
<weight x="-1.196" y="-.33" z="-0.275" mass-prop="/sim/weight[0]/weight-lb"/> <!-- pilot -->
<weight x="-1.196" y=".33" z="-0.275" mass-prop="/sim/weight[1]/weight-lb"/> <!-- co-pilot -->
<weight x="-2.073" y="-.33" z="-0.275" mass-prop="/sim/weight[2]/weight-lb"/> <!-- right passenger -->
<weight x="-2.073" y="0" z="-0.275" mass-prop="/sim/weight[3]/weight-lb"/> <!-- middle passenger -->
<weight x="-2.073" y=".33" z="-0.275" mass-prop="/sim/weight[4]/weight-lb"/> <!-- left passenger -->
<weight x="-3.5" y="0" z="-0.275" mass-prop="/sim/weight[5]/weight-lb"/> <!-- patient/load -->
<!--weight by the additional things like emergency floats, skibox, FLIR...To DO: add the missing things-->
<weight x="-3.198" y="0.0" z="-0.078" size="0.0" mass-prop="/sim/model/ec135/external/HEMS/weight-lb"/>
<weight x="-3.198" y="0.0" z="-0.078" size="0.0" mass-prop="/sim/model/ec135/external/VIP/weight-lb"/>
<weight x="-3.198" y="0.0" z="-0.078" size="0.0" mass-prop="/sim/model/ec135/external/Utility/weight-lb"/>
<weight x="0.138" y="0.0" z="-0.096" size="0.2" mass-prop="/sim/model/ec135/external/BigRadom/weight-lb"/>
<weight x="0.138" y="0.0" z="-0.096" size="0.1" mass-prop="/sim/model/ec135/external/smallradom/weight-lb"/>
<weight x="0.249" y="0.0" z="-0.337" size="0.2" mass-prop="/sim/model/ec135/external/searchlight_front/weight-lb"/>
<weight x="-0.538" y="0.924" z="-0.837" size="0.2" mass-prop="/sim/model/ec135/external/searchlight_left/weight-lb"/>
<weight x="-0.571" y="-1.096" z="-0.984" size="0.5" mass-prop="/sim/model/ec135/external/FLIR/weight-lb"/>
<weight x="0.031" y="-0.397" z="-0.772" size="0.4" mass-prop="/sim/model/ec135/external/mirror/weight-lb"/>
<weight x="-1.244" y="0.0" z="1.009" size="0.1" mass-prop="/sim/model/ec135/external/wirecutter_up/weight-lb"/>
<weight x="-0.212" y="0.0" z="-0.518" size="0.1" mass-prop="/sim/model/ec135/external/wirecutter_down/weight-lb"/>
<weight x="-2.197" y="0.0" z="1.052" size="0.2" mass-prop="/sim/model/ec135/external/sandfilter/weight-lb"/>
<weight x="-3.9367" y="0.0" z="1.060" size="0.0" mass-prop="/sim/model/ec135/external/IBF/weight-lb"/>
<weight x="-2.180" y="0.6" z="0.625" size="0.2" mass-prop="/sim/model/ec135/external/winch/weight-lb"/>
<weight x="-0.755" y="0.316" z="-0.694" size="0.0" mass-prop="/sim/model/ec135/external/SLLightL/weight-lb"/>
<weight x="-0.755" y="-0.316" z="-0.694" size="0.0" mass-prop="/sim/model/ec135/external/SLLightR/weight-lb"/>
<weight x="-1.368" y="-0.311" z="-0.956" size="0.1" mass-prop="/sim/model/ec135/external/loudspeaker/weight-lb"/>
<weight x="-1.368" y="0.357" z="-1.034" size="0.1" mass-prop="/sim/model/ec135/external/hellas/weight-lb"/>
<weight x="-2.5218" y="0.0" z="-1.123" size="0.1" mass-prop="/sim/model/ec135/external/snowboard_lowskid/weight-lb"/>
<weight x="-0.801" y="0.0" z="-1.161" size="0.1" mass-prop="/sim/model/ec135/external/wirecutter_skid/weight-lb"/>
<weight x="-3.004" y="0.0" z="-1.055" size="0.1" mass-prop="/sim/model/ec135/external/longskid_floats/weight-lb"/>
<weight x="-2.339" y="0.0" z="-1.114" size="0.1" mass-prop="/sim/model/ec135/external/midskid/weight-lb"/>
<weight x="-2.5218" y="0.0" z="-1.123" size="0.1" mass-prop="/sim/model/ec135/external/snowboard_midskid/weight-lb"/>
<weight x="-0.801" y="0.0" z="-1.161" size="0.1" mass-prop="/sim/model/ec135/external/wirecutter_midskid/weight-lb"/>
<weight x="-2.339" y="0.0" z="-1.223" size="0.1" mass-prop="/sim/model/ec135/external/highskid/weight-lb"/>
<weight x="-2.521" y="0.0" z="-1.309" size="0.1" mass-prop="/sim/model/ec135/external/snowboard_highskid/weight-lb"/>
<weight x="-0.801" y="0.0" z="-1.413" size="0.1" mass-prop="/sim/model/ec135/external/wirecutter_highskid/weight-lb"/>
<weight x="-2.481" y="0.0" z="-0.852" size="0.0" mass-prop="/sim/model/ec135/external/multifunctioncarrier/weight-lb"/>
<weight x="-2.418" y="0.0" z="-0.901" size="0.0" mass-prop="/sim/model/ec135/external/DoubleCargoHook/weight-lb"/>
<weight x="-4.767" y="-0.052" z="-0.164" size="0.0" mass-prop="/sim/model/ec135/external/buckle/weight-lb"/>
<thruster x="-2.973" y="0.0" z="1.751" 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="-2.973" y="0.0" z="1.751" 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 turbine a 155 pounds(calculated from MTU DB 720) maybe much less in reality for PW206-->
<thruster x="-4.406" y="0.6" z="0.978" vx="-1" vy="0" vz="0" thrust="155">
<control-input axis="/engines/engine[0]/residualthrust" src0="0" src1="1" dst0="0" dst1="-1" control="THROTTLE"/>
</thruster>
<thruster x="-4.406" y="-0.6" z="0.978" vx="-1" vy="0" vz="0" thrust="155">
<control-input axis="/engines/engine[1]/residualthrust" src0="0" src1="1" dst0="0" dst1="-1" control="THROTTLE"/>
</thruster>
<!-- downwash effect of the residual thrust turbine a 155 pounds to the stab-->
<thruster x="-7.3" y="0.6" z="0.615" vx="-1" vy="0" vz="-0.122" thrust="155">
<control-input axis="/engines/engine[0]/residualthrust" src0="0" src1="1" dst0="0" dst1="-1" control="THROTTLE"/>
</thruster>
<thruster x="-7.3" y="-0.6" z="0.615" vx="-1" vy="0" vz="-0.122" thrust="155">
<control-input axis="/engines/engine[1]/residualthrust" src0="0" src1="1" dst0="0" dst1="-1" control="THROTTLE"/>
</thruster>
<hitch name="winch" x="-2.481" y="0" z="-0.852">
<tow length="15" weight-per-meter="0.1" elastic-constant="40000" break-force="10000"/>
<!-- 4.5mm steel wire-->
<winch max-tow-length="15" min-tow-length="1" initial-tow-length="2500" max-winch-speed="1.5" power="150" max-force="6000" />
<control-input axis="/controls/winch/place" control="PLACEWINCH"/>
</hitch>
<hitch name="aerotow" x="-2.481" y="0" z="-0.852" force-is-calculated-by-other="0">
<tow length="15" weight-per-meter="0.1" elastic-constant="40000" break-force="10000" mp-auto-connect-period="0.0"/>
<winch max-tow-length="15" min-tow-length="15" initial-tow-length="2500"/>
<control-input axis="/controls/aerotow/find-aircraft" control="FINDAITOW"/>
</hitch>
</airplane>