Results in orbital evolution of objects in the geosynchronous regionThe orbital evolution of objects at or near geosynchronous orbit (GEO) has been simulated to investigate possible hazards to working geosynchronous satellites. Orbits of both large satellites and small particles have been simulated, subject to perturbations by nonspherical geopotential terms, lunar and solar gravity, and solar radiation pressure. Large satellites in initially circular orbits show an expected cycle of inclination change driven by lunar and solar gravity, but very little altitude change. They thus have little chance of colliding with objects at other altitudes. However, if such a satellite is disrupted, debris can reach thousands of kilometers above or below the initial satellite altitude. Small particles in GEO experience two cycles driven by solar radiation: an expected eccentricity cycle and an inclination cycle not expected. Particles generated by GEO insertion stage solid rocket motors typically hit the earth or escape promptly; a small fraction appear to remain in persistent orbits.
Document ID
19900045001
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Friesen, Larry Jay (Lockheed Engineering and Sciences Co. Houston, TX, United States)
Jackson, Albert A., IV (Lockheed Engineering and Sciences Co. Houston, TX, United States)
Zook, Herbert A. (Lockheed Engineering and Sciences Co. Houston, TX, United States)
Kessler, Donald J. (NASA Johnson Space Center Houston, TX, United States)