Selection of orbital parameters for a satellite with a gyroaerodynamic attitude stabilization system
Abstract
A method of providing ballistic launch data for satellites employing aerodynamic moments for attitude stabilization is developed. In this method, the parameters of the initial orbit are selected shortly before launching on the basis of short-range atmospheric density predictions at the altitude of the satellite orbit and predictions of the wind conditions along the booster trajectory. The effectiveness of the method is demonstrated by the accuracy of the actual orbits of the Cosmos 149 and 320 satellites.
- Publication:
-
Space Arrow: Optical studies of the atmosphere
- Pub Date:
- 1974
- Bibcode:
- 1974saos.book..106B
- Keywords:
-
- Ballistic Trajectories;
- Orbital Elements;
- Satellite Attitude Control;
- Spacecraft Launching;
- Aerodynamic Forces;
- Atmospheric Density;
- Cosmos Satellites;
- Astrodynamics