TF-G1-yasim.xml
9.29 KB
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
<?xml version="1.0" encoding="UTF-8"?>
<!--
Normal rotor speed is 600 rpm with a Vmax of 1000 rpm,
and the blades have been tested up to 4000N static tensile strength,
with a maximum centrifugal load of five tons at 300 rpm in a 3-G pull-up maneuver.
Vne: 95 kts
Max Cruise: 80 kts
Economy Cruise: 70 kts
Best Climb: 52 kts
Rotor Diameter: 7 m
Rotorblade Chord:180 mm
Fuselage Length: 3.5 m
Height: 2.0 m
Wheel Track: 1.7 m
Propeller Diameter: 1.2 m
Rotor Disk Area: 38.5 sqm
Empty Weight: 167 kg
Gross Weight: 290 kg
Max Disc Loading: 7.5 kg/sqm
Max Power Loading: 3.9 kg/hp
Vne: 170 kmh
Max Cruise: 140 kmh
Economy Cruise: 120 kmh
Minimum Speed: 40 kmh
Max ROC: 3 m/s
Service Ceiling (estimated): 4000 m (13000 ft)
Takeoff Run 10 m
Landing Run: 5 m
Range: 250 km
-->
<airplane version="2018.1" mass-kg="3.2" mtow-kg="25">
<approach speed="20" aoa="0">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.60"/>
</approach>
<cruise speed="26" alt="0">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.75"/>
</cruise>
<rotor name="main"
x="-0.24" y="0.0" z="0.33"
nx="0" ny="0" nz="1"
fx="1" fy="0" fz="0" ccw="1"
maxcollective="3.5" mincollective="3.5"
maxcyclicele="0" mincyclicele="0"
maxcyclicail="0" mincyclicail="0"
diameter="2.1"
numblades="2"
weightperblade="1.1"
twist="0"
chord="0.05"
rpm="700"
tiltcenterx="-0.24" tiltcentery="0" tiltcenterz="0.30"
mintiltpitch=" 2"
maxtiltpitch="22"
mintiltroll="-2"
maxtiltroll=" 2"
relbladecenter="0.7"
dynamic="1"
sharedflaphinge="0"
rellenflaphinge="0.0"
delta3="1"
delta="0.8"
pitch-a="6.3"
pitch-b="6.3"
flapmin="-8"
flapmax="8"
flap0="-3"
flap0factor="0"
notorque="0"
translift-ve="15"
translift-maxfactor="1"
ground-effect-constant="0.2"
taper="1"
number-of-segments="8"
number-of-parts="8"
rel-len-where-incidence-is-measured="0.5"
rel-len-blade-start="0.125"
airfoil-lift-coefficient="6.8"
airfoil-drag-coefficient0="0.0075"
airfoil-drag-coefficient1="0.325"
airfoil-incidence-no-lift="0"
incidence-stall-zero-speed="15"
incidence-stall-half-sonic-speed="14.5"
lift-factor-stall="0.6"
stall-change-over="10"
drag-factor-stall="1.5"
cyclic-factor="0.8"
rotor-correction-factor="0.95"
downwashfactor="0.0"
balance="0.999995"
>
<control-input axis="/controls/flight/aileron-trim" control="TILTROLL" split="true" src0="-1.0" src1="1.0" dst0="1.0" dst1="-1.0"/>
<control-input axis="/controls/flight/aileron" control="TILTROLL" src0="-1.0" src1="1.0" dst0="1.0" dst1="-1.0"/>
<control-input axis="/controls/flight/elevator-trim" control="TILTPITCH" split="true" src0="-1.0" src1="1.0" dst0="1.0" dst1="-1.0"/>
<control-input axis="/controls/flight/elevator" control="TILTPITCH" src0="-1.0" src1="1.0" dst0="1.0" dst1="-1.0"/>
</rotor>
<rotorgear max-power-engine="0.750"
max-power-rotor-brake="0.050"
rotorgear-friction="0.0005"
engine-prop-factor="0.02"
engine-accel-limit="5"
yasimdragfactor="30"
yasimliftfactor="140"
>
<!-- ROTORGEARENGINEON is unable to handle proportional input (https://sourceforge.net/p/flightgear/flightgear/ci/next/tree/src/FDM/YASim/Rotor.cpp#l1533)-->
<control-input axis="/controls/engines/engine[0]/starter" control="ROTORGEARENGINEON"/>
<control-input axis="/controls/rotor/brake" control="ROTORBRAKE" src0="0.0" src1="1.0" dst0="0.0" dst1="1.0"/>
</rotorgear>
<!-- Thruster device which does not produce adjacent moments-->
<thruster x="0" y="0" z="0.03" vx="1" vy="0" vz="0" thrust="6.61">
<control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE" src0="-1" src1="1" dst0="-1" dst1="1"/>
</thruster>
<!--
<propeller x="0.02" y="0" z="0.03"
mass="0.05"
moment="0.05"
radius="0.203"
cruise-speed="70"
cruise-rpm="2800"
cruise-alt="2000"
cruise-power="1"
takeoff-power="2"
takeoff-rpm="3600"
contra="1"
>
<actionpt x="0" y="0" z="0.03"/>
<piston-engine eng-power="2" eng-rpm="3800" displacement="20" >
<control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"/>
<control-input axis="/controls/engines/engine[0]/starter" control="STARTER"/>
<control-input axis="/controls/engines/engine[0]/magnetos" control="MAGNETOS"/>
<control-input axis="/controls/engines/engine[0]/mixture" control="MIXTURE"/>
</piston-engine>
</propeller>
-->
<!-- main fuselage -->
<fuselage ax="0" ay="0" az="0" bx="-0.62" by="0" bz="0" width="0.2" taper="0" midpoint="0.25"/>
<!-- main tube -->
<fuselage ax="0" ay="0" az="0" bx="-0.92" by="0" bz="0" width="0.03" taper="1" midpoint="0.6"/>
<!-- gear tubes -->
<!--
<fuselage ax="-0.06838" ay="-0.15" az="-0.02754" bx="-0.06838" by="0.15" bz="-0.02754" width="0.03" taper="0" midpoint="0.5"/>
<fuselage ax="-0.41636" ay="-0.15" az="-0.02754" bx="-0.41636" by="0.15" bz="-0.02754" width="0.03" taper="0" midpoint="0.5"/>
-->
<hstab x="-0.91" y="0.0" z="0"
taper="1"
length="0.15"
chord="0.15"
sweep="0"
dihedral = "0"
>
<stall aoa="14" width="4" peak="1.5"/>
</hstab>
<vstab x="-0.91" y="0.15" z="-0.055"
chord="0.25"
length="0.15"
taper="1"
sweep="0"
incidence="0" >
<stall aoa="16" width="4" peak="1.5"/>
<flap0 start="0" end="1" lift="1.2" drag="0.8"/>
<control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/>
<control-input axis="/controls/flight/rudder-trim" control="FLAP0" invert="true"/>
<control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm" min="1" max="-1"/>
</vstab>
<vstab x="-0.91" y="-0.15" z="-0.055"
chord="0.25"
length="0.15"
taper="1"
sweep="0"
incidence="0" >
<stall aoa="16" width="4" peak="1.5"/>
<flap0 start="0" end="1" lift="1.2" drag="0.8"/>
<control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/>
<control-input axis="/controls/flight/rudder-trim" control="FLAP0" invert="true"/>
<control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm" min="1" max="-1"/>
</vstab>
<gear x="-0.06471" y="0.0" z="-0.205" compression="0.051">
<control-input axis="/controls/flight/rudder" control="STEER" square="false" src0="-1.0" src1="1.0" dst0="-0.3" dst1="0.3"/>
<control-input axis="/controls/gear/brake-right" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
</gear>
<gear x="-0.34368" y="0.25" z="-0.205" compression="0.051">
<control-input axis="/controls/gear/brake-right" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
</gear>
<gear x="-0.34368" y="-0.25" z="-0.205" compression="0.051">
<control-input axis="/controls/gear/brake-left" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
</gear>
<!-- tail gear -->
<gear x="-1.12" y="0.000" z="-0.09"
compression="0.08"
ignored-by-solver="1" >
</gear>
<!-- fuel tank for moddeled engine-->
<tank x="-0.1" y="0.0" z="-0.05" capacity="0.2"/>
<!-- rotor head ballast -->
<ballast x="-0.24" y="0.0" z="0.33" mass-kg="0.5"/>
<!-- gear weights and balasts -->
<!--
<weight x="-0.06471" y="0.225" z="-0.2" mass-prop="/sim/weight[0]/weight-kg"/>
<weight x="-0.06471" y="-0.225" z="-0.2" mass-prop="/sim/weight[1]/weight-kg"/>
<weight x="-0.34368" y="0.225" z="-0.2" mass-prop="/sim/weight[2]/weight-kg"/>
<weight x="-0.34368" y="-0.225" z="-0.2" mass-prop="/sim/weight[2]/weight-kg"/>
-->
<ballast x="-0.06471" y="0" z="-0.2" mass-kg="0.3"/>
<ballast x="-0.34368" y="0.225" z="-0.2" mass-kg="0.15"/>
<ballast x="-0.34368" y="-0.225" z="-0.2" mass-kg="0.15"/>
<!-- engine balast -->
<ballast x="0.0" y="0.0" z="0.02" mass-kg="0.7"/>
<!-- accumulator balasts -->
<ballast x="-0.15" y="0.1" z="0.0" mass-kg="0.25"/>
<ballast x="-0.15" y="-0.1" z="0.0" mass-kg="0.25"/>
<!-- tail balasts -->
<ballast x="-0.98" y="0.15" z="0.00" mass-kg="0.26"/>
<ballast x="-0.98" y="-0.15" z="0.00" mass-kg="0.26"/>
<!-- hitch -->
<hitch name="winch" x="0.0" y="0.0" z="0.0">
<tow length="50" weight-per-meter="0.0035" elastic-constant="40000" break-force="10000"/>
<!-- 3mm paracord-->
<winch max-tow-length="1000" min-tow-length="1" initial-tow-length="1000" max-winch-speed="20" power="2" max-force="80"/>
<control-input axis="/controls/winch/place" control="PLACEWINCH"/>
</hitch>
<hitch name="aerotow" x="0.0" y="0.0" z="0.0" force-is-calculated-by-other="0">
<tow length="60" weight-per-meter="0.0035" elastic-constant="9000" break-force="100" mp-auto-connect-period="0.0"/>
<winch max-tow-length="1000" min-tow-length="60" initial-tow-length="60"/>
<control-input axis="/controls/aerotow/find-aircraft" control="FINDAITOW"/>
</hitch>
</airplane>