forked from HHS81/ec135
-
Notifications
You must be signed in to change notification settings - Fork 0
/
ec135P2.xml
528 lines (433 loc) · 21.9 KB
/
ec135P2.xml
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
86
87
88
89
90
91
92
93
94
95
96
97
98
99
100
101
102
103
104
105
106
107
108
109
110
111
112
113
114
115
116
117
118
119
120
121
122
123
124
125
126
127
128
129
130
131
132
133
134
135
136
137
138
139
140
141
142
143
144
145
146
147
148
149
150
151
152
153
154
155
156
157
158
159
160
161
162
163
164
165
166
167
168
169
170
171
172
173
174
175
176
177
178
179
180
181
182
183
184
185
186
187
188
189
190
191
192
193
194
195
196
197
198
199
200
201
202
203
204
205
206
207
208
209
210
211
212
213
214
215
216
217
218
219
220
221
222
223
224
225
226
227
228
229
230
231
232
233
234
235
236
237
238
239
240
241
242
243
244
245
246
247
248
249
250
251
252
253
254
255
256
257
258
259
260
261
262
263
264
265
266
267
268
269
270
271
272
273
274
275
276
277
278
279
280
281
282
283
284
285
286
287
288
289
290
291
292
293
294
295
296
297
298
299
300
301
302
303
304
305
306
307
308
309
310
311
312
313
314
315
316
317
318
319
320
321
322
323
324
325
326
327
328
329
330
331
332
333
334
335
336
337
338
339
340
341
342
343
344
345
346
347
348
349
350
351
352
353
354
355
356
357
358
359
360
361
362
363
364
365
366
367
368
369
370
371
372
373
374
375
376
377
378
379
380
381
382
383
384
385
386
387
388
389
390
391
392
393
394
395
396
397
398
399
400
401
402
403
404
405
406
407
408
409
410
411
412
413
414
415
416
417
418
419
420
421
422
423
424
425
426
427
428
429
430
431
432
433
434
435
436
437
438
439
440
441
442
443
444
445
446
447
448
449
450
451
452
453
454
455
456
457
458
459
460
461
462
463
464
465
466
467
468
469
470
471
472
473
474
475
476
477
478
479
480
481
482
483
484
485
486
487
488
489
490
491
492
493
494
495
496
497
498
499
500
501
502
503
504
505
506
507
508
509
510
511
512
513
514
515
516
517
518
519
520
521
522
523
524
525
526
527
528
<!--
This file is part of FlightGear, the free flight simulator
http://www.flightgear.org/
Copyright (C) 2009 Heiko Schulz, Heiko.H.Schulz@gmx.net
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>