Engineering, 21.11.2019 04:31, bigboy43

At time t0 (relative to perigee passage), a spacecraft has the following orbital parameters: % e = 1.5; perigee altitude = 300 km; i = 35 °; ω = 130 °; and ω = 115 °.% calculate r and v at perigee relative to a) the perifocal reference% frame. b) the geocentric equatorial frame.

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At time t0 (relative to perigee passage), a spacecraft has the following orbital parameters: % e = 1...