采用多敏感器相互校正的卫星入轨姿态计算方法

摘要

针对卫星与运载分离后,由于星上姿态测量敏感器未开机或不具备工作条件而无法获悉初始入轨姿态的问题,设计了采用多敏感器相互校正的入轨姿态计算方法.建立运动学方程,结合陀螺测量角速度信息和星敏感器首次测量有效姿态,采用信赖域方法进行非线性优化求解,由后向前反向推算姿态;提出一种由模拟太阳敏感器测量对日姿态到对地姿态转化的便捷方法,由模拟太阳敏感器测量对日信息,采用本体系太阳矢量与星敏感器测量信息建立联系,达到了利用太阳敏感器测量信息校正星敏感器推算姿态的目的,最终得到的星箭分离时卫星姿态信息能够与运载方信息吻合.将入轨后卫星真实姿态与地面模型仿真结果对比,验证了模型的正确性,为后续卫星设计和飞行程序设计与改进提供了重要依据.%After the satellite is separated from the upper stage, the initial attitude is not learned about since the attitude sensors are not valid for the measurement.In order to solve this problem, an initial attitude calculation method using multi sensors' intercalibration was designed.The kinematic equation was set firstly, and then the first available attitudes measured by star sensor as well as gyro's angular velocity were prepared.The nonlinear equation was solved by using the trust region algorithm;meanwhile the attitude was obtained from backward to forward;the analog sun vector detector's information was used to revise the deduction;a convenient method translating the attitude from the sun to the earth was put forward;sun vector was connected to star sensor's information.The deduction result is consistent with injection attitude of rocket.Simulation result on the ground was compared with the real attitude in orbit, validating the correctness of simulation model.The result provides support for the design of satellite and the procedure design and improvement of flight.