Lunar-Solar Effects on the 60,000 Nautical Mile SOLRAD-HI Satellite.
NAVAL WEAPONS LAB DAHLGREN VA
Pagination or Media Count:
Limitations on launch conditions are found which yield acceptable orbits for high altitude satellites planned for the SOLRAD-HI system. Lunar-solar effects and mission constraints result in the conclusion that for a three satellite system with a three year lifetime, the semimajor axes should lie between 60,000 and 70,000 n.m., the eccentricities less than 0.02, the inclinations between 6.5 and 7.0 degrees, and the longitude of the ascending node between -70 and 90 degrees. If the overlap time can be reduced from 30 minutes, larger inclinations can be allowed, and a longer operational lifetime will result. Author
- Spacecraft Trajectories and Reentry