Preliminary Performance Analysis of Satellite Formation Flying Testbed by Attitude Tracking Experiment

ABSTRACT Thispaperpresentspreliminaryperformanceanalysisofasatelliteformationflyingtestbed, which is under development by Astrodynamics and Control Laboratory,Department of Astronomy, Yonsei University. A model reference adaptive controller(MRAC)withafirst-orderreferencemodelischosentoenhancetheresponseofreactionwheel system which issubject to uncertainties caused by unmodelled dynamicsandmeasurementnoise.Inaddition,anon-lineparameterestimation(OPE)techniquebasedontheleastsquareiscombinedtoeliminatetheeffectofangularmeasurementnoisebyestimatingthemomentofinertia.BothnumericalsimulationsandhardwareexperimentswithMRACsupporttheeffectivenessandapplicabilityoftheadaptivecontrolscheme,whichmaintainsthetrackingerrorbelow0.25 o fortheentiretimespan.However,thehighfrequency control input generated in hardware experiment strongly suggests designmodificationstoreducetheeffectofdeadzone. 초 록 본 논문에서는 연세대학교 천문우주학과 우주비행제어연구실에서 개발 중인 인공위성 편대비행 테스트베드에 대한 예비 성능분석 결과를 제시하였다.동역학 모델에 포함되지 않은 동특성과 측정 잡음 등에 의한 불확실성의 영향을 받는 반작용 휠의 응답 성능을 향상시키기 위하여 간단한 1차 선형시스템을 기준 모델로 하는 적응제어기를 설계하였다.또한 자세 측정값에 잡음이 포함된 환경에서도 원활한 제어를 수행하기 위해 최소제곱법 기반의 실시간 파라미터 추정기법을 이용하여 관성모멘트를 추정하였다.수치 시뮬레이션과 하드웨어 실험을 통해 설계된 모델 기준 적응제어기의 적합성과 향후 적용가능성을 검토하였고,전 시간에 걸친 자세 추적오차가 0.25

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