Optimum yaw motion for satellites with a nadir-pointing payload
Abstract
This paper treats the case of a satellite powered by a plane solar array with a payload that needs to be pointed toward nadir at all times. First the formulas are derived for perfect alignment between solar generator and sun direction. These attitude conditions have been derived before but the coordinates chosen here permit a particularly simple presentation of the results. A simplified attitude scheme is then proposed which consists of replacing the ideal yaw angle profile by a square wave. The yaw angle is thus maintained constant for large parts of the orbit, which is a great advantage for certain applications.
- Publication:
-
Journal of Guidance Control Dynamics
- Pub Date:
- February 1983
- DOI:
- 10.2514/3.19801
- Bibcode:
- 1983JGCD....6...47K
- Keywords:
-
- Satellite Attitude Control;
- Satellite Orbits;
- Solar Arrays;
- Solar Electric Propulsion;
- Solar Position;
- Spacecraft Power Supplies;
- Control Theory;
- Satellite Configurations;
- Satellite Design;
- Solar Eclipses;
- Yaw;
- Astrodynamics