Strain actuated solar-arrays for precision pointing of spacecraft

Oscar Alvarez-Salazar, Jack Aldrich, Nuno Filipe, James Allison, Soon-Jo Chung

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Next generation telescopes for space exploration are being planned with unprecedented levels of pointing and wavefront stability as science enabling capabilities - i.e., sub-milli-arcsecond class pointing, and pico-meter class RMS wave-front error). Current methodologies for attaining these levels of stability are approaching the limit of what is possible with the use of isolation, intensive and risky structural dynamic tailoring, exquisite broad-band Attitude Control System (ACS) sensors and actuators, and ultra-precise fast steering mirrors commanded to compensate for pointing errors through feedback of camera measurements. This paper explores the benefits of using Strain Actuated Solar Arrays (SASA) - currently under Research at the Jet Propulsion Laboratory and the University of Illinois Urbana Champagne - in new ACS architectures for applications requiring very tight precision pointing of a SC and on-board instrumentation. A strain actuated solar array has the following characteristics: (1) Strain actuation and sensing is distributed throughout the SA panels to obtain control authority and observability over the strain state of the SA-enabling SA jitter control. (2) Large motion (up to 10 degrees or relative motion) strain based mechanisms are used in between SA panels and in between the SC and the solar array-enables SC slewing and limited momentum management. (3) The mechanical (i.e., stiffness and configuration) and inertia/mass properties of the SA have been designed to optimize its ability to control its vibrations and the vibration and attitude of the host SC. This paper discusses ACS architectures that use the above SASA system while avoiding the use of the Reaction Wheel Actuator (RWA) during key science observation periods. The RWA being the dominant source of pointing jitter and wave front jitter in a telescope based observatory; hence, not flying RWAs amounts to not flying the main source of jitter! At least two architectures based on the SASA system are studied - one is an earth orbiter, the other is assumed to be in an L2 orbit. Simulation results for one of these cases are discussed along with what developments are needed going forward to enable the use of this technology.

Original languageEnglish (US)
Title of host publicationGuidance, Navigation, and Control 2016
EditorsDavid A. Chart
PublisherUnivelt Inc.
Pages929-944
Number of pages16
ISBN (Print)9780877036319
StatePublished - Jan 1 2016
Event39th Annual AAS Rocky Mountain Section Guidance and Control Conference, 2016 - Breckenridge, United States
Duration: Feb 5 2016Feb 10 2016

Publication series

NameAdvances in the Astronautical Sciences
Volume157
ISSN (Print)0065-3438

Other

Other39th Annual AAS Rocky Mountain Section Guidance and Control Conference, 2016
CountryUnited States
CityBreckenridge
Period2/5/162/10/16

ASJC Scopus subject areas

  • Aerospace Engineering
  • Space and Planetary Science

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  • Cite this

    Alvarez-Salazar, O., Aldrich, J., Filipe, N., Allison, J., & Chung, S-J. (2016). Strain actuated solar-arrays for precision pointing of spacecraft. In D. A. Chart (Ed.), Guidance, Navigation, and Control 2016 (pp. 929-944). (Advances in the Astronautical Sciences; Vol. 157). Univelt Inc..