Problem of programing trajectory of satellite to obtain maximum orbit altitude investigated; optimum trajectory obtained by making tangent of angle psi between thrust vector and horizontal, linear function of time; explicit expressions for velocity and altitude given for particular case of constant thrust and mass flow rate.
On powered flight trajectory of earth satellite
Jet Propulsion
Jet Propulsion ; 27 , n 6
1957
3 pages
Article (Journal)
English
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On the Powered Flight Trajectory of an Earth Satellite
NTIS | 1956
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Engineering Index Backfile | 1957
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