Orbit manoeuvres with finite thrust - A study and presentation of results
Abstract
The results of a numerical examination of orbital maneuvers using a hypergolic propellant at low thrust levels are presented. The study is confined to coplanar, Hohmann transfers with the thrust occurring only at periapsis or apoapsis. The transfers are from circular to elliptic, circular to hyperbolic, elliptic to elliptic, and elliptic to hyperbolic orbits at varying thrust increments and decrements. Numerical techniques are formulated to define the operative control laws during thrusting, using the Pontryagin Maximum Principle, and are written in FORTRAN. Two periapsis burns were analyzed as examples, one from circular to elliptic and one from circular to hyperbolic orbits. The technique is recommended as a means to establishing a data base for hypergolic propellant economy during orbit changes, and can be adapted to multiburn maneuvers.
- Publication:
-
ESA Journal
- Pub Date:
- 1982
- Bibcode:
- 1982ESAJ....6..291I
- Keywords:
-
- Elliptical Orbits;
- Hypergolic Rocket Propellants;
- Optimal Control;
- Orbit Calculation;
- Orbital Maneuvers;
- Transfer Orbits;
- Circular Orbits;
- Eccentric Orbits;
- Equations Of Motion;
- Gravitational Fields;
- Hyperbolic Trajectories;
- Optimization;
- Astrodynamics