Session
Technical Session II: Small Satellites - Subsystems
Abstract
During the last 25 years APL has designed and built more than 50 small spacecraft, many being unique designs. The Power Systems of these spacecraft take many forms but almost all use a solar cell array and a Nickel-Cadmium battery. An overview of seven spacecraft power systems is presented. Four of the spacecraft are gravity gradient stabilized in a near-polar Low Earth Orbit (LEO). The remaining three spacecraft are spin stabilized, two with near-equatorial orbits. Both dissipative and nondissipative charge control systems are represented and the solar array configurations, all consisting of deployable panels, are described. Power system performance parameters are given for each system including weight, power generation, solar cell area utilization and power system efficiency. The array generation capabilities range from 34 to 280 Watts. Power system efficiencies are on the order of 60 to 80% and experiments use from 20 to 63% of the available spacecraft power. Power generation per array weight is approximately 5 Watts/Kilogram and available power per system weight is 1-3 Watts/Kilogram for the spacecraft surveyed.
A Survey of Recent APL Spacecraft Power Systems
During the last 25 years APL has designed and built more than 50 small spacecraft, many being unique designs. The Power Systems of these spacecraft take many forms but almost all use a solar cell array and a Nickel-Cadmium battery. An overview of seven spacecraft power systems is presented. Four of the spacecraft are gravity gradient stabilized in a near-polar Low Earth Orbit (LEO). The remaining three spacecraft are spin stabilized, two with near-equatorial orbits. Both dissipative and nondissipative charge control systems are represented and the solar array configurations, all consisting of deployable panels, are described. Power system performance parameters are given for each system including weight, power generation, solar cell area utilization and power system efficiency. The array generation capabilities range from 34 to 280 Watts. Power system efficiencies are on the order of 60 to 80% and experiments use from 20 to 63% of the available spacecraft power. Power generation per array weight is approximately 5 Watts/Kilogram and available power per system weight is 1-3 Watts/Kilogram for the spacecraft surveyed.
