Sword7
Member
Folks,
I found two memos (in download section) about state vector to orbital elements conversion or via through google. I was able implemented them into my program. I tried it with object above earth with zero velocity and circular velocity (v = sqrt(GM/r)). I got interesting results of conversion.
With zero velocity, it fell down to earth like skydiving and it is parabolic orbit (e = 1). Its perigee is at earth core like on Orbiter MFD when you are on ground. With circular velocity, it resulted perfect circular orbit. I calculated state vector into speed - 17,150 mph at 400 km AGL. (mph = v.norm() * 3600 * 0.62)
https://www.rene-schwarz.com/web/Home
I found two memos (in download section) about state vector to orbital elements conversion or via through google. I was able implemented them into my program. I tried it with object above earth with zero velocity and circular velocity (v = sqrt(GM/r)). I got interesting results of conversion.
With zero velocity, it fell down to earth like skydiving and it is parabolic orbit (e = 1). Its perigee is at earth core like on Orbiter MFD when you are on ground. With circular velocity, it resulted perfect circular orbit. I calculated state vector into speed - 17,150 mph at 400 km AGL. (mph = v.norm() * 3600 * 0.62)
https://www.rene-schwarz.com/web/Home
