Attitude Control Simulation for Equator-S using Object Oriented Modeling

Abstract

This paper describes efforts for simulation of the Equator-S spacecraft for mission analysis and preparation. Simulation modeling is performed within the object oriented modeling environment Dymola. This allows the modeling of the satellite dynymics on its most transparent level in form of physical objects, and the modeling of the control algorithm in form of basic control block objects. From the object model of the controlled Equators- S a simulation code is automatically generated for simulating a spin axis erection maneuver using the Shigehara algorithm. Such a maneuver is necessary to ensure constant power supply by solar cells for the rotating satellite independently from the position of sun.