Automatic mass balancing of a spacecraft three-axis simulator: analysis and experimentation
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Authors
Chesi, Simone
Gong, Qi
Pellegrini, Veronica
Cristi, Roberto
Romano, Marcello
Subjects
Advisors
Date of Issue
2014
Date
January-February 2014
Publisher
AIAA
Language
Abstract
Spacecraft three-axis simulators provide frictionless and, ideally, torque-free hardware simulation platforms that are crucial for validating spacecraft attitude determination and control strategies. To reduce the gravitational torque, the distance between the simulator center of mass and the center of rotation needs to be minimized. This work proposes an automatic mass balancing system for spacecraft simulators, which uses only the three sliding masses during the balancing process, without need of further actuators. The proposed method is based on an adaptive nonlinear feedback control that aims to move, in real time, the center of mass toward the spacecraft simulator’s center of rotation. The stability of the feedback system and the convergence of the estimated unknown parameter (the distance between the center of mass and the center of rotation) are analyzed through Lyapunov stability theory. The proposed method is experimentally validated using the CubeSat Three-Axis Simulator at the Spacecraft Robotics Laboratory of the Naval Postgraduate School.
Type
Article
Description
The article of record as published may be found at http://dx.doi.org/10.2514/1.60380
Series/Report No
Department
Electrical Engineering/Mechanical & Aerospace Engineering
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
10 p.
Citation
Journal of guidance, control and dynamics, Vol. 37, No. 1, January–February 2014, p. 197-206
Distribution Statement
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.