Thanks. So for STS 75. I can get the TLE file and load that using the scn editor and then pick the time?
The altitude depends on the semi-major axis that is computed from the TLE data you based. Here's the formula to get the SMA directly from the TLENot sure how to get the different alt. This should be the orbit to launch Eureca.
STS-46
1 22064U 92 49 A 92215.26859953 .00013412 00000-0 25599-3 0 45
2 22064 28.4698 338.7713 0008891 295.2501 190.9110 [B]15.46403423[/B] 20
1 22064U 92 49 A 92215.64583333 .00013459 00000-0 25599-3 0 55
2 22064 28.4712 336.1282 0007242 311.3562 119.2459 15.46519912 320
-30.000 =orbit(425,437,28.45,-1)
Thanks. So what should I set the guidance for?The shuttle is too heavy to launch itself in a perfectly circular orbit about 400 km in altitude. The initial flight profile of every shuttle launch has its perigee somewhere between 90-110 km to allow the external tank fall into the Pacific or Indian Oceans, and the apogee is always somewhere between 220-250 km depending on the mission.
Therefore, the circularization and raising of the shuttle's orbit is always achieved manually through 1 or 2 OMS burns
Before STS-38:Thanks. So what should I set the guidance for?
-30.000 =orbit(104,228,inclination,-1)
-30.000 =orbit(104,apogee,inclination,-1)
-30.000 =orbit(104,apogee,inclination,-1)
360=inverse()
-30.000 =orbit(104,apogee,inclination,-1)
the apogee is 425