Minimization of Perturbative Effects on a High Eccentricity, Highly Inclined 24-Hour Satellite Orbit
Abstract
A study was performed to analyse and minimize the effects of the perturbative forces on a 24-hour satellite orbit having an eccentricity of 0.6 and an inclination of 60 degrees by selection of an optimum launch date. The computer model used includes the perturbations due to the oblate earth as described by the zonal, tesseral and sectorial harmonic series through sixth order, the solar and lunar third-body forces, and the solar radiation pressure on a vehicle whose area-to-mass ratio is 10 ft squared/slug. The orbit was computed for one year following launch with oribital parameter variations presented as functions of the launch date during 1970. The results of the study indicate that the total required impulse is significantly dependent on the launch date and oscillatory behavior of the orbital parameters due to the lunar-cycle.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1973
- Accession Number
- AD0769964
Entities
People
- Allen L. Thede
Organizations
- Air Force Institute of Technology