[특허]Apparatus and method for autonomous satellite attitude sensing

Apparatus and method for autonomous satellite attitude sensing 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G06F-165/00
출원번호	US-0139935 (1993-10-20)
발명자 / 주소	Johnson William M. (Sudbury MA) Musoff Howard (Brookline MA)
출원인 / 주소	The Charles Stark Draper Laboratory, Inc. (Cambridge MA 02)
인용정보	피인용 횟수 : 66 인용 특허 : 0

초록 ▼

An attitude sensing system utilizing simplified techniques and apparatus includes a Kalman filter which receives signals from an inertial measurement unit, a GPS receiver, and an integrated optical assembly. The output vector of the filter includes estimates of attitude misalignments and estimates of gyro drifts corresponding to the axes of the inertial measurement unit. The optical assembly includes a sensor array providing signals to the filter representing detection of the Earth\s horizon or the center of the Sun. More particularly, a local vertical vector, computed from fore and aft detections of the Earth\s horizon, is used in combination with GPS received signals to initially determine attitude by means of gyrocompassing. This attitude information is thereafter maintained by the inertial measurement unit and azimuth error resulting from drift of the inertial measurement unit and the initial gyrocompassing error is corrected by detections of the Earth\s horizon and the Sun. The integrated optical assembly, used to detect the locations of both the Sun and Earth relative to the satellite, eliminates a need for separate apparatus dedicated to each sensing function. Moreover, the GPS receiver eliminates the need for ground tracking apparatus by providing the satellite ephemerides (including orbital pitch rate used in gyrocompassing) for use by the filter, rendering the attitude sensing system substantially autonomous. Additionally, the GPS receiver, in combination with the Sun and Earth detections, eliminates the need for a complex star tracker by providing an accurate inertial frame of reference.

대표청구항 ▼

An attitude sensing system for a spacecraft comprising: a satellite receiver for providing a receiver output signal in response to satellite generated signals; an inertial measurement unit for providing a direction cosine matrix representing the attitude of said spacecraft in inertial space with respect to a yaw axis, a pitch axis, and a roll axis defining a frame of reference of said system; an optical assembly providing an optical assembly output signal, said optical assembly including a sensor array for providing a representation of an image focused on said sensor array; and a digital filter, responsive to said receiver output signal, said direction cosine matrix, and said optical assembly output signal, for providing an output vector for correcting the attitude of said spacecraft.

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Apparatus and method for autonomous satellite attitude sensing 원문보기

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Apparatus and method for autonomous satellite attitude sensing 원문보기

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