Battery charge control with temperature compensated voltage limit
Abstract
Battery charge control for orbiting spacecraft with mission durations from three to ten years, is a critical design feature that is discussed. Starting in 1974, the General Electric Space Systems Division designed, manufactured and tested battery systems for six different space programs. Three of these are geosynchronous missions, two are medium altitude missions and one is a near-earth mission. All six power subsystems contain nickel cadmium batteries which are charged using a temperature compensated voltage limit. This charging method was found to be successful in extending the life of nickel cadmium batteries in all three types of earth orbits. Test data and flight data are presented for each type of orbit.
- Publication:
-
The 1982 Goddard Space Flight Center Battery Workshop
- Pub Date:
- August 1983
- Bibcode:
- 1983batt.work..259T
- Keywords:
-
- Current Regulators;
- Electric Charge;
- Electric Potential;
- Nickel Cadmium Batteries;
- Spacecraft Power Supplies;
- Temperature Compensation;
- Design Analysis;
- Earth Orbits;
- Life (Durability);
- Performance Tests;
- Temperature Effects;
- Electronics and Electrical Engineering