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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Vector sum of Combined maneuvers α 28.5 deg = V plane 794.102 m s = V plane 2V a sin α 2 := Plane Change Δ V 2 V f V a := V f V a 1.462 10 3 × m s = V f 3.075 10 3 × m s = Deltavee2 V a 1.613 10 3 × m s = V p V i 2.412 10 3 × m s = c Deltavee1 V a 1.613 10 3 × m s = V a 2 μ r a μ a := apogee velocity V p 1.011 10 4 × m s = V p 2 μ r p μ a := perigee veloctiy Transfer orbit a 2.445 10 4 × km = a r a r p + 2 := V f 3.075 10 3 × m s = V f μ r a := Final circular orbit velocity
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Problem 3 1 m s 1 watt c 1.001 kg .8 11.895 yr = 1 m s 1 watt c 1.001 kg .8 3.754 10 8 × sec = d 1 watt c 1.001 kg .8 2.664 10 9 × m s 2 = c 1watt c 3.333 10 9 × N = b c g 3.059 10 7 × s = a c 300000
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MAE155A_AstroMidTerm - Test 2010 note you may have...

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