MAE155A_AstroMidTerm

MAE155A_AstroMidTerm - Test 2010 note you may have...

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V i 7.697 10 3 × m s = V i μ r p := Initial circular orbit velocity α 28.5 deg = r p 6.728 10 3 × km = r a 4.216 10 4 × km = b Parameters of transfer orbit P 1.526 hr = P 2 π μ r p 3 := a Orbit period r p 350 km R e + := Perigee Radius r a 4.216 10 4 × km = r a R geo := Apogee radius Hohmann tansfer R geo 42164 km := α 28.5 deg := ETR inclination 1 Same as above, with plane change μ 398600 km 3 sec 2 := R e 6378.14 km := Hohmann transfer pg 79 Geosynch mission design pg 102 Test 2010 note you may have interpreted the problem differently and used a proper method and therefore come with a different answer so you still get most of the points.
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