Relative to a non-rotating Earth-centred Cartesian coordinate system, the position and velocity vectors of a spacecraft

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Relative to a non-rotating Earth-centred Cartesian coordinate system, the position and velocity vectors of a spacecraft

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Relative To A Non Rotating Earth Centred Cartesian Coordinate System The Position And Velocity Vectors Of A Spacecraft 1
Relative To A Non Rotating Earth Centred Cartesian Coordinate System The Position And Velocity Vectors Of A Spacecraft 1 (65.2 KiB) Viewed 46 times
Relative to a non-rotating Earth-centred Cartesian coordinate system, the position and velocity vectors of a spacecraft are r = 21,522i - 17,573j + 21,522k (km) v = 1801i + 1100j +1801k (m/s) Calculate: (b) the orbit eccentricity; [4 Marks] (c) the orbit semi-major axis, its perigee and apogee radii, the orbit period; [3 Marks] (d) position of the orbit perigee in the non-rotating Earth-centred Cartesian coordinate system; [2 marks] (e) current true anomaly of the spacecraft, 0. Examine whether this angle is less or greater than 180°. [2 marks]
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