Abstract
This paper presents a new experimental research and development platform for satellite attitude determination and control systems (ADCS). It is designed to easily accommodate any major component of a satellite ADCS. The platform provides a near-zero gravity condition using a Ball-and-Socket air bearing table that provides unconstrained satellite rotational motion. The pressurized air flow is passed through five micro-scale air holes carefully placed inside the socket to provide the required air gap between the socket and the ball. The platform provides full freedom of spin in the yaw axis but roll and pitch motions are constrained to angles of less than +/- 30 degrees. A special counter balance mechanism has been designed for a wide range of payloads that can be mounted on it. The satellite with its counter balance structure is attached to the ball and is carefully placed on the air cushion using a special mechanism. A dedicated UHF/VHF RF link is designed to allow for remote command and control of payloads under testing. All payloads will be connected to the RF system via a CAN bus.
The paper discusses the detailed description of the testing platform and the challenges related to its commissioning and operation. In addition, it presents research projects that could be carried out using the platform including applying advanced robust control theory, system identification, validity tests and sensors integration and calibration in future satellite ADCSs. In particular, a multi-filters multi-sensors estimator is presented for the multiple MEMS gyros array system.