The original paper is in English. Non-English content has been machine-translated and may contain typographical errors or mistranslations. ex. Some numerals are expressed as "XNUMX".
Copyrights notice
The original paper is in English. Non-English content has been machine-translated and may contain typographical errors or mistranslations. Copyrights notice
본 연구의 주요 목적은 유연한 우주선의 자세 제어를 위한 시뮬레이션과 지상 기반 실험을 입증하는 것입니다. 전형적인 우주선 구조는 강체와 크고 유연한 태양 전지판인 유연한 부속 장치, 무게를 줄이기 위해 가벼운 재료로 제작된 포물선 안테나로 구성됩니다. 따라서 이러한 부속물은 외부 힘의 자극에 의해 구조적 진동을 유발하기 때문에 자세 제어에 큰 문제가 있습니다. 유연한 팔을 갖춘 단일 축 회전 시뮬레이터는 작동으로 온-오프 공기 추진기와 반응 휠을 사용하여 구성됩니다. 시뮬레이터에는 또한 동시 스러스터 및 DC 서보 모터 작동을 통한 페이로드 포인팅 기능이 장착되어 있습니다. 유연한 우주선 자세 제어 실험은 반응 바퀴만을 사용하여 수행됩니다. 반응 휠을 사용하여 퍼지-PID 컨트롤러의 성능은 단일 축 회전 시뮬레이터에 대한 시뮬레이션 및 실험 결과를 통해 설명됩니다.
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부
Jong-Oh PARK, Young-Do IM, "An Attitude Control of Flexible Spacecraft Using Fuzzy-PID Controller" in IEICE TRANSACTIONS on Fundamentals,
vol. E92-A, no. 4, pp. 1237-1241, April 2009, doi: 10.1587/transfun.E92.A.1237.
Abstract: This primary objective of this study is to demonstrate simulation and ground-based experiment for the attitude control of flexible spacecraft. A typical spacecraft structure consists of the rigid body and flexible appendages which are large flexible solar panels, parabolic antennas built from light materials in order to reduce their weight. Therefore the attitude control has a big problem because these appendages induce structural vibration under the excitation of external forces. A single-axis rotational simulator with a flexible arm is constructed with on-off air thrusters and reaction wheel as actuation. The simulator is also equipped with payload pointing capability by simultaneous thruster and DC servo motor actuation. The experiment of flexible spacecraft attitude control is performed using only the reaction wheel. Using the reaction wheel the performance of the fuzzy-PID controller is illustrated by simulation and experimental results for a single-axis rotational simulator.
URL: https://global.ieice.org/en_transactions/fundamentals/10.1587/transfun.E92.A.1237/_p
부
@ARTICLE{e92-a_4_1237,
author={Jong-Oh PARK, Young-Do IM, },
journal={IEICE TRANSACTIONS on Fundamentals},
title={An Attitude Control of Flexible Spacecraft Using Fuzzy-PID Controller},
year={2009},
volume={E92-A},
number={4},
pages={1237-1241},
abstract={This primary objective of this study is to demonstrate simulation and ground-based experiment for the attitude control of flexible spacecraft. A typical spacecraft structure consists of the rigid body and flexible appendages which are large flexible solar panels, parabolic antennas built from light materials in order to reduce their weight. Therefore the attitude control has a big problem because these appendages induce structural vibration under the excitation of external forces. A single-axis rotational simulator with a flexible arm is constructed with on-off air thrusters and reaction wheel as actuation. The simulator is also equipped with payload pointing capability by simultaneous thruster and DC servo motor actuation. The experiment of flexible spacecraft attitude control is performed using only the reaction wheel. Using the reaction wheel the performance of the fuzzy-PID controller is illustrated by simulation and experimental results for a single-axis rotational simulator.},
keywords={},
doi={10.1587/transfun.E92.A.1237},
ISSN={1745-1337},
month={April},}
부
TY - JOUR
TI - An Attitude Control of Flexible Spacecraft Using Fuzzy-PID Controller
T2 - IEICE TRANSACTIONS on Fundamentals
SP - 1237
EP - 1241
AU - Jong-Oh PARK
AU - Young-Do IM
PY - 2009
DO - 10.1587/transfun.E92.A.1237
JO - IEICE TRANSACTIONS on Fundamentals
SN - 1745-1337
VL - E92-A
IS - 4
JA - IEICE TRANSACTIONS on Fundamentals
Y1 - April 2009
AB - This primary objective of this study is to demonstrate simulation and ground-based experiment for the attitude control of flexible spacecraft. A typical spacecraft structure consists of the rigid body and flexible appendages which are large flexible solar panels, parabolic antennas built from light materials in order to reduce their weight. Therefore the attitude control has a big problem because these appendages induce structural vibration under the excitation of external forces. A single-axis rotational simulator with a flexible arm is constructed with on-off air thrusters and reaction wheel as actuation. The simulator is also equipped with payload pointing capability by simultaneous thruster and DC servo motor actuation. The experiment of flexible spacecraft attitude control is performed using only the reaction wheel. Using the reaction wheel the performance of the fuzzy-PID controller is illustrated by simulation and experimental results for a single-axis rotational simulator.
ER -