Skip to content

Commit

Permalink
Erick Hoffman Releases new FDM
Browse files Browse the repository at this point in the history
  • Loading branch information
@IAHM-COL
IAHM-COL committed Jun 7, 2016
1 parent ffae617 commit 963a5e9
Show file tree
Hide file tree
Showing 6 changed files with 1,163 additions and 614 deletions.
94 changes: 94 additions & 0 deletions Engines/PT6A.xml
View file
@@ -0,0 +1,94 @@
<?xml version="1.0"?>

<!--
File: PT6A.xml
Author: AeromatiC++ v 3.2.5
See: http://wiki.flightgear.org/JSBSim_Engines#FGTurboprop
Inputs:
name: PT6A
type: Turboprop Engine
power: 549.8 hp
inlet temperature: 725.0 degrees C
overall pressure ratio: 6.3:1
Outputs:
psfc: 0.641 lbs/hr/hp
engine weight: 298.2 lbs
engine length: 4.6 ft
engine diameter: 1.8 ft
-->

<turboprop_engine name="PT6A">
<milthrust unit="LBS"> 1231.6 </milthrust>
<idlen1> 60.0 </idlen1>
<maxn1> 100.0 </maxn1>
<maxpower unit="HP"> 549.8 </maxpower>
<psfc unit="LBS/HR/HP"> 0.641 </psfc>
<n1idle_max_delay> 1 </n1idle_max_delay>
<maxstartingtime> 20 </maxstartingtime>
<startern1> 20 </startern1>
<ielumaxtorque unit="FT*LB"> 1303.7 </ielumaxtorque>
<itt_delay> 0.05 </itt_delay>
<betarangeend> 64 </betarangeend>
<reversemaxpower> 60 </reversemaxpower>

<function name="EnginePowerVC">
<table>
<description> Engine power, function of airspeed and pressure </description>
<independentVar lookup="row">atmosphere/P-psf</independentVar>
<independentVar lookup="column">velocities/ve-kts</independentVar>
<tableData>
0 50 100 150 200 250
503 0.357 0.380 0.400 0.425 0.457 0.486
1048 0.586 0.589 0.600 0.621 0.650 0.686
1328 0.707 0.721 0.731 0.757 0.786 0.821
1496 0.779 0.786 0.808 0.821 0.857 0.900
1684 0.850 0.857 0.874 0.900 0.943 0.979
1896 0.914 0.929 0.946 0.971 1 1.057
2135 1 1.011 1.029 1.043 1.083 1.150
2213 1.029 1.043 1.057 1.079 1.114 1.171
</tableData>
</table>
</function>

<table name="EnginePowerRPM_N1" type="internal">
<description> Engine Power, function of RPM and N1 </description>
<tableData>
0 5 60 86 94 95 96 97 98 99 100 101
0.0 0.0 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
862.7 0.0 0.4 25.9 148.0 259.0 281.2 310.8 340.4 370.0 392.2 429.2 458.8
1291.7 0.0 0.4 22.2 170.2 296.0 318.2 347.8 373.7 407.0 436.6 473.6 503.2
1723.0 0.0 0.4 3.7 177.6 325.6 351.5 377.4 407.0 440.3 466.2 503.2 532.8
2154.4 0.0 0.1 0.1 166.5 333.0 366.3 388.5 418.1 451.4 481.0 518.0 551.3
2370.1 0.0 0.1 0.1 151.7 325.6 355.2 381.1 414.4 447.7 477.3 514.3 549.8
</tableData>
</table>

<table name="ITT_N1" type="internal">
<description> Inter-Turbine Temperature ITT [deg C] depending on N1 and engine run (0=off / 1=running) </description>
<tableData>
0 1
0 0 0
15 105.1 105.1
60 188.5 546.7
96 283.5 714.8
100 294.4 790.2
</tableData>
</table>

<table name="CombustionEfficiency_N1" type="internal">
<description>Dependency of fuel efficiency coefficient on N1 (and RPM)</description>
<tableData>
90 0.1221
91.2 0.2834
92.2 0.5336
93.4 0.7188
94.1 0.7741
95.2 0.8471
96.5 0.9001
100 1
</tableData>
</table>
</turboprop_engine>
143 changes: 143 additions & 0 deletions Engines/Propeller.xml
View file
@@ -0,0 +1,143 @@
<?xml version="1.0"?>

<!-- Generated by Aero-Matic v 3.2.5
See: http://wiki.flightgear.org/JSBSim_Thrusters#FGPropeller
Inputs:
horsepower: 549.81
max engine rpm: 37500
prop diameter (ft): 7.91667
prop chord (ft): 0.756031
pitch: variable at 45 inch
Outputs:
max prop rpm: 2370.06
gear ratio: 15.8224
Cp0: 0.0663477
Ct0: 0.15459
static thrust (lbs): 2253.1
-->

<propeller version="1.01" name="prop">
<ixx> 6.01793 </ixx>
<diameter unit="IN"> 95 </diameter>
<numblades> 4 </numblades>
<gearratio> 15.8224 </gearratio>
<cp_factor> 1.00 </cp_factor>
<ct_factor> 1.00 </ct_factor>
<minpitch> 12 </minpitch>
<maxpitch> 45 </maxpitch>
<minrpm> 2014.55 </minrpm>
<maxrpm> 2370.06 </maxrpm>

<!-- thrust coefficient as a function of advance ratio and blade angle -->
<table name="C_THRUST" type="internal">
<tableData>
-15 0 15 30 45 60
0.00 0.0499 0.1140 0.1781 0.2421 0.3062 0.3702
0.05 0.0438 0.1076 0.1712 0.2345 0.2975 0.3604
0.10 0.0378 0.1014 0.1645 0.2272 0.2894 0.3511
0.15 0.0319 0.0954 0.1582 0.2202 0.2816 0.3423
0.20 0.0260 0.0895 0.1520 0.2136 0.2743 0.3340
0.25 0.0202 0.0838 0.1461 0.2073 0.2673 0.3261
0.30 0.0144 0.0781 0.1404 0.2013 0.2607 0.3187
0.35 0.0086 0.0726 0.1349 0.1955 0.2544 0.3117
0.40 0.0029 0.0672 0.1296 0.1900 0.2485 0.3051
0.45 -0.0029 0.0618 0.1244 0.1847 0.2428 0.2988
0.50 -0.0087 0.0565 0.1193 0.1796 0.2375 0.2929
0.55 -0.0146 0.0513 0.1144 0.1747 0.2323 0.2872
0.60 -0.0204 0.0461 0.1095 0.1700 0.2275 0.2819
0.65 -0.0263 0.0409 0.1048 0.1655 0.2228 0.2769
0.70 -0.0323 0.0357 0.1002 0.1611 0.2184 0.2721
0.75 -0.0383 0.0306 0.0957 0.1569 0.2142 0.2676
0.80 -0.0444 0.0255 0.0912 0.1528 0.2101 0.2633
0.85 -0.0506 0.0203 0.0868 0.1488 0.2063 0.2593
0.90 -0.0569 0.0152 0.0825 0.1449 0.2026 0.2554
0.95 -0.0633 0.0100 0.0782 0.1412 0.1990 0.2517
1.00 -0.0697 0.0049 0.0739 0.1375 0.1956 0.2482
1.05 -0.0763 -0.0004 0.0697 0.1340 0.1924 0.2449
1.10 -0.0830 -0.0056 0.0655 0.1305 0.1892 0.2418
1.15 -0.0897 -0.0109 0.0614 0.1271 0.1862 0.2388
1.20 -0.0966 -0.0162 0.0572 0.1237 0.1833 0.2359
1.25 -0.1036 -0.0216 0.0531 0.1205 0.1805 0.2332
1.30 -0.1108 -0.0270 0.0490 0.1173 0.1778 0.2306
1.35 -0.1180 -0.0325 0.0449 0.1141 0.1752 0.2282
1.40 -0.1254 -0.0381 0.0407 0.1110 0.1727 0.2258
1.50 -0.1406 -0.0494 0.0325 0.1049 0.1679 0.2214
1.60 -0.1564 -0.0609 0.0242 0.0989 0.1633 0.2174
1.70 -0.1727 -0.0728 0.0158 0.0930 0.1590 0.2137
1.80 -0.1896 -0.0850 0.0073 0.0873 0.1549 0.2103
1.90 -0.2071 -0.0975 -0.0013 0.0815 0.1510 0.2071
2.00 -0.2251 -0.1104 -0.0100 0.0759 0.1473 0.2042
2.10 -0.2439 -0.1236 -0.0189 0.0702 0.1437 0.2015
2.20 -0.2632 -0.1371 -0.0279 0.0645 0.1402 0.1990
2.30 -0.2831 -0.1511 -0.0371 0.0589 0.1368 0.1967
2.40 -0.3037 -0.1654 -0.0464 0.0532 0.1335 0.1945
</tableData>
</table>

<!-- power coefficient as a function of advance ratio and blade angle -->
<table name="C_POWER" type="internal">
<tableData>
-15 0 15 30 45 60
0.00 0.0067 0.0317 0.0792 0.1492 0.2418 0.3568
0.05 0.0077 0.0344 0.0835 0.1551 0.2492 0.3658
0.10 0.0084 0.0366 0.0873 0.1605 0.2563 0.3745
0.15 0.0085 0.0384 0.0907 0.1657 0.2631 0.3832
0.20 0.0083 0.0397 0.0938 0.1705 0.2698 0.3916
0.25 0.0075 0.0407 0.0965 0.1750 0.2762 0.3999
0.30 0.0063 0.0412 0.0989 0.1793 0.2824 0.4082
0.35 0.0047 0.0414 0.1009 0.1832 0.2884 0.4163
0.40 0.0025 0.0411 0.1026 0.1870 0.2942 0.4244
0.45 -0.0000 0.0404 0.1039 0.1904 0.3000 0.4325
0.50 -0.0031 0.0394 0.1050 0.1937 0.3055 0.4405
0.55 -0.0066 0.0379 0.1057 0.1967 0.3110 0.4485
0.60 -0.0106 0.0360 0.1061 0.1995 0.3163 0.4565
0.65 -0.0151 0.0337 0.1061 0.2021 0.3215 0.4646
0.70 -0.0201 0.0310 0.1059 0.2044 0.3267 0.4726
0.75 -0.0256 0.0279 0.1053 0.2066 0.3317 0.4807
0.80 -0.0315 0.0244 0.1044 0.2085 0.3366 0.4889
0.85 -0.0380 0.0204 0.1032 0.2102 0.3415 0.4971
0.90 -0.0451 0.0161 0.1017 0.2117 0.3463 0.5053
0.95 -0.0526 0.0112 0.0998 0.2131 0.3510 0.5136
1.00 -0.0607 0.0060 0.0976 0.2142 0.3556 0.5220
1.05 -0.0694 0.0003 0.0951 0.2151 0.3602 0.5304
1.10 -0.0786 -0.0059 0.0923 0.2158 0.3647 0.5389
1.15 -0.0884 -0.0125 0.0891 0.2162 0.3691 0.5475
1.20 -0.0987 -0.0195 0.0855 0.2165 0.3734 0.5562
1.25 -0.1097 -0.0271 0.0817 0.2166 0.3777 0.5649
1.30 -0.1212 -0.0351 0.0775 0.2164 0.3818 0.5737
1.35 -0.1334 -0.0436 0.0729 0.2161 0.3860 0.5826
1.40 -0.1461 -0.0526 0.0680 0.2155 0.3900 0.5915
1.50 -0.1735 -0.0720 0.0570 0.2136 0.3979 0.6097
1.60 -0.2034 -0.0935 0.0446 0.2109 0.4054 0.6281
1.70 -0.2359 -0.1171 0.0306 0.2072 0.4126 0.6469
1.80 -0.2711 -0.1428 0.0151 0.2025 0.4195 0.6660
1.90 -0.3090 -0.1706 -0.0019 0.1969 0.4260 0.6853
2.00 -0.3497 -0.2006 -0.0206 0.1903 0.4321 0.7049
2.10 -0.3932 -0.2329 -0.0410 0.1826 0.4379 0.7248
2.20 -0.4396 -0.2675 -0.0630 0.1739 0.4432 0.7449
2.30 -0.4889 -0.3044 -0.0867 0.1641 0.4481 0.7652
2.40 -0.5412 -0.3436 -0.1122 0.1532 0.4525 0.7858
</tableData>
</table>

<!-- thrust effects of helical tip Mach -->
<table name="CT_MACH" type="internal">
<tableData>
0.85 1.0
1.05 0.8
</tableData>
</table>

<!-- power-required effects of helical tip Mach -->
<table name="CP_MACH" type="internal">
<tableData>
0.85 1.0
1.05 1.8
2.00 1.4
</tableData>
</table>

</propeller>
124 changes: 124 additions & 0 deletions Systems/Conventional Controls.xml
View file
@@ -0,0 +1,124 @@
<?xml version="1.0"?>
<system name="Conventional Controls">
<channel name="Pitch">
<summer name="Pitch Trim Sum">
<input>fcs/elevator-cmd-norm</input>
<input>fcs/pitch-trim-cmd-norm</input>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
</summer>

<aerosurface_scale name="Elevator Control">
<input>fcs/pitch-trim-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>

<aerosurface_scale name="Elevator Normalization">
<input>fcs/elevator-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/elevator-pos-norm</output>
</aerosurface_scale>
</channel>

<channel name="Roll">
<summer name="Roll Trim Sum">
<input>fcs/aileron-cmd-norm</input>
<input>fcs/roll-trim-cmd-norm</input>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
</summer>

<aerosurface_scale name="Left Aileron Control">
<input>fcs/roll-trim-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/left-aileron-pos-rad</output>
</aerosurface_scale>

<aerosurface_scale name="Right Aileron Control">
<input>-fcs/roll-trim-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/right-aileron-pos-rad</output>
</aerosurface_scale>

<aerosurface_scale name="Left Aileron Normalization">
<input>fcs/left-aileron-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>

<aerosurface_scale name="Right Aileron Normalization">
<input>fcs/right-aileron-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/right-aileron-pos-norm</output>
</aerosurface_scale>
</channel>

<channel name="Yaw">
<summer name="Rudder Command Sum">
<input>fcs/rudder-cmd-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
</summer>

<aerosurface_scale name="Rudder Control">
<input>fcs/rudder-command-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>

<aerosurface_scale name="Rudder Normalization">
<input>fcs/rudder-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/rudder-pos-norm</output>
</aerosurface_scale>
</channel>

</system>

0 comments on commit 963a5e9

Please sign in to comment.