Spin-Off Maneuvers of Flexible Satellite Using PD Based Constant-Amplitude Inputs

Parman Setyamartana; Radzuan B. Razali; Azman Zainuddin

doi:10.4028/www.scientific.net/AMM.465-466.337

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 465-466Spin-Off Maneuvers of Flexible Satellite Using PD...

Spin-Off Maneuvers of Flexible Satellite Using PD Based Constant-Amplitude Inputs

Abstract:

Spin-off maneuver of a flexible satellite using constant-amplitude thrusters is studied in this paper. The satellite consists of a rigid main body and two symmetrical solar panels. The panels are having structural flexibility and their motions are discretized following the finite element method. Under constant-amplitude thrusts, steady-state attitude angle oscillations may occur in large amplitude after the maneuvers. Since in operation the satellite should point to certain area on the earth precisely, these oscillations of course are not acceptable. To reduce the oscillations, proportional derivative (PD) based constant-amplitude input shaping logic is proposed to determine time locations of thruster switching. Then, under such inputs, spin-downs of the satellite are simulated numerically. Results of simulations indicate that the precise orientation of the satellite can be achieved.

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Periodical:

Applied Mechanics and Materials (Volumes 465-466)

Pages:

337-344

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.465-466.337

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Online since:

December 2013

Authors:

Parman Setyamartana, Radzuan B. Razali, Azman Zainuddin

Keywords:

Constant-Amplitude, Flexible Satellite, PD Control, Spin-Off Maneuver

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