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CU-Boulder ASEN 3200 - Orbit Mechanics Quiz 1

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ASEN 3200 Orbit Mechanics/Attitude Dynamics & controlOrbit Mechanics Quiz 1Name _______________________________________ASEN 3200 Orbit Mechanics/Attitude Dynamics & controlOrbit Mechanics Quiz 1Jan 25, 2001These are equations you may need for this quiz:    2a p23 23e2p p2 312a 1 er , r a 1 e , r a 1 e1 e cosvE , GM 398600 KM s2a 2 raR 6378KM, P 2 , h rxv, h r v cos2Ehe 1 , M n(t t ) (t t ) E esin Ea1 e Etan tan2 1 e 2                            1. (40%) The perigee altitude of an Earth satellite is 2422 km and its eccentricity is 0.2Find:a. Semimajor axisb. apogee altitudec. the orbit energyd. the velocity at apogee[OVER]2. (20%) Compute the time to go from apogee to perigee for an Earth satellite witha=8000km, e=0.4, and =30.3. (20%) the position and velocity vectors of an Earth satellite in Earth Centered Inertial (ECI) are: (Hint – Draw a sketch)r i j DUr k DU TU 2 2101. /a. The orbit inclination is ___________b. The right ascension of the ascending node is ____________c. The angular momentum vector is___________4. (20%) Fill in the elements of the transformation matricesLNMMMMMMOQPPPPPPLNMMMMMMOQPPPPPPLNMMMMMMOQPPPPPPLNMMMMMMOQPPPPPPLNMMMMMMOQPPPPPPLNMMMMMMOQPPPPPPXYZXYZXYZXYZX XYYZ,


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CU-Boulder ASEN 3200 - Orbit Mechanics Quiz 1

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