Accession Number : AD1053058

Title :   Flexible Multi-Body Spacecraft Simulator: Design, Construction, and Experiments

Descriptive Note : Technical Report

Corporate Author : Naval Postgraduate School Monterey United States

Personal Author(s) : Atwood,Adam L

Full Text :

Report Date : 01 Dec 2017

Pagination or Media Count : 99

Abstract : The aim of this thesis was to develop and construct a flexible multi-body spacecraft simulator for use in testing optimal control-based slew and maneuver designs. The simulator is modified from an earlier prototype, which had a flexible arm and actuated robotic arm on an aluminum plate atop an air bearing. The new simulator features enhanced capabilities, with an improved passive flexible appendage, a commercial-off-the-shelf (COTS) robotic arm, a reaction wheel momentum control system, a wireless flight control system, and a battery-powered electrical distribution system. The COTS robotic arm was modified to function with either flexible or rigid joints, and was used as a basis for initial experimentation. The simulators purpose is to test agile cooperative maneuvers designed using optimal control theory. A specific maneuver was developed and tested for the robotic arm in its flexible joint configuration. It is shown experimentally that maneuver time could be reduced by 50% as compared to a baseline (standard) maneuver, and that the optimal control-based solution significantly reduced post maneuver vibrations.

Descriptors :   artificial satellites , spacecraft , simulators , flight control systems , physical properties , momentum , moment of inertia , gas bearings , dc motors , steady state , space systems , software prototyping , mathematical models , bearings , VIBRATION , robotics

Subject Categories : Unmanned Spacecraft
      Computer Programming and Software

Distribution Statement : APPROVED FOR PUBLIC RELEASE