Halo-orbit formulation for the ISEE-3 mission
Abstract
The path to which the ISEE-3 satellite is to be controlled is a periodic solution to the three-dimensional equations for motion about the interior libration point of the sun-earth-satellite three-body system. These particular periodic 'halo' orbits are constructed using analytical and numerical methods. The third-order analytical solution is obtained by application of successive approximations in conjunction with a form of the Lindstedt-Poincare method. The ISEE-3 mission orbit is one member of a family of orbits which are locally approximated by the analytical development. This orbit is produced from standard differential corrections procedures using the third-order solution as the 'initial guess'.
- Publication:
-
American Institute of Aeronautics and Astronautics Conference
- Pub Date:
- June 1979
- Bibcode:
- 1979aiaa.confS....R
- Keywords:
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- International Sun Earth Explorer 3;
- Libration;
- Orbital Mechanics;
- Satellite Control;
- Satellite Guidance;
- Three Body Problem;
- Graphs (Charts);
- Linearization;
- Mathematical Models;
- Tables (Data);
- Astrodynamics