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Journal of Applied Sciences
  Year: 2012 | Volume: 12 | Issue: 24 | Page No.: 2519-2526
DOI: 10.3923/jas.2012.2519.2526
 
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Attitude Maneuvers of CTS-like Spacecraft Using PD based Constant-Amplitude Inputs

Setyamartana Parman, Bambang Ari-Wahjoedi, Edward Halawa and Affiani Machmudah

Abstract:
Attitude maneuvers of a Communication Technology Satellite (CTS)-like spacecraft using constant-amplitude thrusters is of great importance. The spacecraft consists of a rigid main body and two symmetrical solar panels. When the panels are large, they cannot be treated as rigid bodies anymore. They are supposed to behave structural flexibility. To discrete their motion, the finite element method is followed. Under constant-amplitude thrusts, steady-state attitude angle oscillations may occur in large amplitude after the maneuvers. Since, the spacecraft should point to the earth precisely, these oscillations must be reduced into small permissible values. To reduce residual attitude angle oscillations, Proportional Derivative (PD) based constant-amplitude input shaping logic is proposed to determine time locations of thruster switching. Then, under such inputs, attitude maneuvers of the spacecraft are simulated numerically. Results of simulations show that the precise orientation of the satellite can be achieved.
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How to cite this article:

Setyamartana Parman, Bambang Ari-Wahjoedi, Edward Halawa and Affiani Machmudah, 2012. Attitude Maneuvers of CTS-like Spacecraft Using PD based Constant-Amplitude Inputs. Journal of Applied Sciences, 12: 2519-2526.

DOI: 10.3923/jas.2012.2519.2526

URL: https://scialert.net/abstract/?doi=jas.2012.2519.2526

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