MENU-TYPE DESIGN METHOD FOR GEO SATELLITE CONTROL SYSTEM BASED ON OPTIMIZED INFORMATION INTEGRATION

• Main Authors: HAN, Xiaodong, GUO, Tingrong, GONG, Jianjun, SUN, Baoxiang, CUI, Zhenjiang, ZHOU, Zhicheng, WEI, Qiang, CAO, Guixing
• Format: Patent
• Language: English; French; German
• Published: 26.06.2019
• Subjects: AIRCRAFT; AVIATION; COSMONAUTICS; GYROSCOPIC INSTRUMENTS; MEASURING; MEASURING DISTANCES, LEVELS OR BEARINGS; NAVIGATION; PERFORMING OPERATIONS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY; PHYSICS; SURVEYING; TESTING; TRANSPORTING; VEHICLES OR EQUIPMENT THEREFOR

A menu-type design method for a GEO satellite control system based on optimized information integration, comprising the following steps: configuring four long-life inertial attitude sensor gyroscopes arranged in pyramid fashion for a long-life GEO satellite control system; configuring various sensors required by a user in accordance with hardware menu-type design requirements; sequentially arranging three types of Kalman filters, which are: three inertial attitude sensor gyroscopes plus an optical attitude start sensor, three inertial attitude sensor gyroscopes plus an earth sensor as well as a sun sensor, and three inertial attitude sensor gyroscopes plus another type of sensor capable of measuring a three-axis attitude, respectively; if an FDIR module of satellite-borne computer application software detects a fault, the FDIR module automatically generates a corresponding alarm, and the currently selected Kalman filter performs automatic reduced-order filtering; the FDIR module implements automatic recombination if the fault is not eliminated within a set period of time. The method can improve the cost performance, carrier-to-interference ratio, and reliability of a satellite platform and can obviously shorten the developing cycle.