ZERO-G EMULATING TESTBED FOR SPACECRAFT CONTROL SYSTEM

摘要

The present invention provides an emulation system having a control systemthat allows thetesting of a satellite control system with all of its hardware in place, i.e.fully integrated. Theemulation methodology is applicable to the case of either a rigid spacecraftor a flexiblespacecraft, provided that the spacecraft's sensors and actuators are stowed tothe rigid partof spacecraft in the case of a flexible spacecraft. Practically, the lattercondition is notrestrictive, as the actuators and sensors are usually placed rigidly in thesatellite bus, whilethe satellite solar panels constitute the flexible elements. The controlsystem is used to tunethe mass properties and dynamic behaviour of a rigid ground-spacecraft in a 1-Genvironment to those of a flight-spacecraft in 0-G. A six-axis force/momentsensor is placedat an interface of the ground-spacecraft and a manipulator. Signals receivedfrom theforce/moment sensor, and in some cases signals relating to the position andvelocity ofmanipulator joints, are received into the control system.