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Co-Design of Strain-Actuated Solar Arrays for Spacecraft Precision Pointing and Jitter Reduction

Chilan, Christian M. and Herber, Daniel R. and Nakka, Yashwanth Kumar and Chung, Soon-Jo and Allison, James T. and Aldrich, Jack B. and Alvarez-Salazar, Oscar S. (2017) Co-Design of Strain-Actuated Solar Arrays for Spacecraft Precision Pointing and Jitter Reduction. AIAA Journal, 55 (9). pp. 3180-3195. ISSN 0001-1452. doi:10.2514/1.J055748.

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This work presents a novel spacecraft attitude control architecture using strain-actuated solar arrays that does not require the use of conventional attitude control hardware. A strain-actuated solar array enables attitude slewing maneuvers and precision pointing (image acquisition) stares, while simultaneously suppressing structural vibrations. Distributed piezoelectric actuators help achieve higher precision, higher bandwidth, and quieter operation than reaction wheels. To understand the design tradeoffs for this architecture, a framework for the integrated design of distributed structural geometry and distributed control is presented. The physical properties of the array are modeled and designed with respect to a piecewise linear distributed thickness profile. The distributed control is a voltage profile across the array modeled as a spatially continuous function. The dynamics of the system are modeled using a coupled ordinary differential equation–partial differential equation system using extended generalizations for hybrid coordinate systems. The combined physical and control system design, or co-design problem is investigated to understand the optimal performance of the system. Single-axis slew maneuvers of 7.2 milliradians or 1485 arcsec are achieved for a representative spacecraft model without increasing array mass or reducing array planform area. From additional tradeoff studies, a design criteria is revealed for the array structure and control strategy based on the optimal design tradeoff between large array inertia and fast structural dynamics. Moreover, the fundamental limits on strain-actuated solar arrays slew angle magnitude are demonstrated using an intuitive pseudorigid body dynamic model.

Item Type:Article
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URLURL TypeDescription ItemConference Paper
Nakka, Yashwanth Kumar0000-0001-7897-3644
Chung, Soon-Jo0000-0002-6657-3907
Additional Information:© 2017 by the American Institute of Aeronautics and Astronautics, Inc. The U.S. Government has a royalty‐free license to exercise all rights under the copyright claimed herein for Governmental purposes. Presented as Paper 2016-0162 at the 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, San Diego, CA, 4–8 January 2016; received 11 October 2016; revision received 24 February 2017; accepted for publication 10 May 2017; published online 11 August 2017. Government sponsorship is acknowledged. The research was carried out, in part, at the Jet Propulsion Laboratory, California Institute of Technology under a contract with the National Aeronautics and Space Administration. The authors acknowledge help from Giri Subramanian and Kevin Lohan during the initial phases of the project.
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Issue or Number:9
Record Number:CaltechAUTHORS:20170523-113653804
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Official Citation:Christian M. Chilan, Daniel R. Herber, Yashwanth Kumar Nakka, Soon-Jo Chung, James T. Allison, Jack B. Aldrich, and Oscar S. Alvarez-Salazar. "Co-Design of Strain-Actuated Solar Arrays for Spacecraft Precision Pointing and Jitter Reduction", AIAA Journal, Vol. 55, No. 9 (2017), pp. 3180-3195.
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:77660
Deposited By: George Porter
Deposited On:23 May 2017 19:31
Last Modified:15 Nov 2021 17:32

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