Analytic Model for Low Earth Orbit Satellite Solar Power
John Petrus Grey, I. R. Mann, Michael D. Fleischauer, D.G. Elliott
Abstract
An analytic model for calculating the instantaneous and average orbital power available to a satellite in a circular low Earth orbit is presented. By accounting for the effects of angle of solar incidence and eclipsing, for both stabilized and tumbling satellites, this model allows for fast, simple, accurate calculations of available power without the use of complex, often expensive, numerical simulation software. In addition, this method provides the value of maximum and minimum solar power available.
Topics & Concepts
SatelliteOrbit (dynamics)Aerospace engineeringGeocentric orbitPower (physics)PhysicsRemote sensingComputer scienceEngineeringGeologyQuantum mechanicssolar cell performance optimizationSpacecraft Design and TechnologySpacecraft Dynamics and Control