Optimal transfer orbits of spacecraft with high-thrust engines
Abstract
Approximation methods for obtaining optimal spacecraft transfer orbits in cases of high-thrust (chemical and nuclear-thermal) propulsion are discussed. A general theoretical approach to the problem of optimizing impulse transfer orbits is presented with application to spacecraft orbiting the moon or a planet and returning to earth. The theory of optimal maneuverability of spacecraft in thin layers of a central gravitational field is examined.
- Publication:
-
Moscow Izdatel Nauka
- Pub Date:
- 1976
- Bibcode:
- 1976MoIzN....R....I
- Keywords:
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- Earth-Moon Trajectories;
- High Thrust;
- Interplanetary Flight;
- Trajectory Optimization;
- Transfer Orbits;
- Chemical Propulsion;
- Circular Orbits;
- Gravitational Fields;
- Maneuverability;
- Nuclear Propulsion;
- Spacecraft Maneuvers;
- Astrodynamics