Lunar-Solar Effects on the 60,000 Nautical Mile SOLRAD-HI Satellite.

Abstract

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)

Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1971
Accession Number
AD0724639

Entities

People

  • Robert Mueller

Organizations

  • Naval Surface Warfare Center Dahlgren Division

Tags

Communities of Interest

  • Space

DTIC Thesaurus Topics

  • Altitude
  • Artificial Satellites
  • Eccentricity
  • Grids
  • High Altitude
  • Longitude
  • Nautical

Readers

  • Mathematics or Statistics
  • Space Exploration and Orbital Mechanics.

Technology Areas

  • Space
  • Space - Orbital Debris