Jon S. Berndt
2010-01-14
$Revision: 1.5 $
Rough model of the DIRECT Jupiter-246
Lunar Crew Launch Vehicle Configuration.
FOR EDUCATIONAL PURPOSES ONLY.
This model is not sanctioned by nor is it a work of the DIRECT Launcher
team.
This model was created using publicly available data, publicly available
technical reports, textbooks, and guesses. It contains no proprietary or
restricted data. If this model has been validated at all, it would be
only to the extent that it seems to "fly right", and that it possibly
complies with published, publicly known, performance data (maximum speed,
endurance, etc.). Thus, this model is meant for educational and entertainment
purposes only.
This simulation model is not endorsed by the manufacturer. This model is not
to be sold.
255
18
300
1500
0
0
0
0
0
0
0
0
185000
2770.0
-225.0
0.0
185000
2770.0
225.0
0.0
119479
2556.0
0.0
0.0
7000
3500.0
0.0
165.0
7000
3500.0
0.0
55.0
7000
3500.0
0.0
-55.0
7000
3500.0
0.0
-165.0
8748
1600.0
0.0
0.0
21117
1176.0
0.0
0.0
610
78.0
0.0
8.0
610
78.0
6.928
4.0
610
78.0
6.928
-4.0
610
78.0
0.0
-8.0
610
78.0
-6.928
-4.0
610
78.0
-6.928
4.0
26000
700.0
0.0
0.0
20000
400.0
0.0
0.0
16000
120.0
0.0
0.0
12571
1176.0
0.0
0.0
2676
-225
0
0
3500
-225
0
2676
-225
0
6.0
124.0
2.0
1114092
1114092
2676
225
0
1
3500
225
0
2676
225
0
6.0
124.0
2.0
1114092
1114092
3500
0
165
2
3
3500
0
165
3500
0
55
2
3
3500
0
55
3500
0
-55
2
3
3500
0
-55
3500
0
-165
2
3
3500
0
-165
1956
0
0
2076
0
0
1389500
1389500
2520
0
0
3300
0
0
231571
231571
78.0
0.0
8.0
4
5
78.0
0.0
8.0
78.0
6.928
4.0
4
5
78.0
6.928
4.0
78.0
6.928
-4.0
4
5
78.0
6.928
-4.0
78.0
0.0
-8.0
4
5
78.0
0.0
-8.0
78.0
-6.928
-4.0
4
5
78.0
-6.928
-4.0
78.0
-6.928
4.0
4
5
78.0
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4.0
1250
0
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1356
0
0
331674
331674
1476
0
0
1596
0
0
55279
55279
Drag_minimum
aero/qbar-psf
metrics/Sw-sqft
velocities/mach
0.0000 0.0610
0.1000 0.0610
0.5000 0.0610
0.7000 0.0620
0.8000 0.0650
0.9000 0.0680
0.9900 0.0900
1.0000 0.0900
1.0100 0.0900
1.1000 0.1300
1.2000 0.1200
1.3000 0.1100
1.4000 0.1000
1.5000 0.0930
2.0000 0.0800
3.0000 0.0620
4.0000 0.0480
5.0000 0.0400
6.0000 0.0380
7.0000 0.0370
8.0000 0.0370
9.0000` 0.0370
Side force due to beta
aero/qbar-psf
metrics/Sw-sqft
aero/beta-rad
velocities/mach
0.0000 -4.5000
0.4000 -3.8000
0.6000 -3.6000
1.0500 -4.5000
1.4000 -4.0000
2.8000 -2.5000
6.0000 -1.1000
9.0000 -1.0000
Lift force due to alpha
aero/qbar-psf
metrics/Sw-sqft
aero/alpha-rad
velocities/mach
0.0000 4.5000
0.4000 3.8000
0.6000 3.6000
1.0500 4.5000
1.4000 4.0000
2.8000 2.5000
6.0000 1.1000
9.0000 1.0000