Modular testbed for spinning spacecraft

Chanik, Abadi, Gao, Yang and Si, J (2016) Modular testbed for spinning spacecraft AIAA Journal of Spacecraft, and Rockets, 54 (1). pp. 90-100.

Preview	Text AIAA2016.pdf - Accepted version Manuscript Available under License : See the attached licence file. Download (564kB) | Preview
Preview	Text (licence) SRI_deposit_agreement.pdf Available under License : See the attached licence file. Download (33kB) | Preview

Abstract

The ground verification of a spacecraft control algorithm is commonly done via air bearing facility. Air bearing testbeds are frequently developed for testing a three-axis stabilized spacecraft control algorithm but hardly for a spin-stabilized spacecraft. A modular testbed for testing a spinning spacecraft has been developed at Surrey Space Centre initially for the real-time verification of a prolate spinner slew control algorithm. This testbed is made from commercial off-the-shelf components with a modular system design approach through rapid control prototyping using Matlab xPC Target and is extendable to other rapid control prototyping techniques. It is equipped with a novel low-cost monocular vision system for attitude determination with accuracy of 0.06 deg and angular velocity accuracy of 0.15  deg/s0.15  deg/s. For the current specification, a cold-gas propulsion system is fixed to the testbed with a two-degree-of-freedom thruster set that can deliver up to 0.25 N of thrust and an air bearing capability that gives three degrees of freedom with a maximum tilt angle of 30 deg. In this paper, the testbed implementation is described, and the test platform is verified.

Item Type:	Article
Subjects :	Surrey Space Centre
Divisions :	Faculty of Engineering and Physical Sciences > Electronic Engineering > Surrey Space Centre
Authors :	Name Email ORCID Chanik, Abadi a.azhar@surrey.ac.uk Gao, Yang Yang.Gao@surrey.ac.uk Si, J
Date :	3 October 2016
Identification Number :	10.2514/1.A33586
Copyright Disclaimer :	Copyright © 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Copies of this paper may be made for personal and internal use, on condition that the copier pay the per-copy fee to the Copyright Clearance Center (CCC). All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0022-4650 (print) or 1533-6794 (online) to initiate your request.
Depositing User :	Symplectic Elements
Date Deposited :	26 Oct 2016 10:34
Last Modified :	31 Oct 2017 18:51
URI:	http://epubs.surrey.ac.uk/id/eprint/812616

Actions (login required)

View Item

Downloads