基于卫星和星敏感器的冗余激光惯组在轨标定

采用高精度卫星导航速度、位置信息以及星敏感器提供的姿态信息设计十表冗余捷联惯组的标定模型,包含陀螺和加速度计的零次项和标度因数,对卫星和星敏感器辅助的冗余激光陀螺捷联惯组进行实时在轨标定.利用标准Kalman滤波和Sage-Husa自适应滤波作为估计算法,对十表冗余捷联惯组参数进行在线估计.数值仿真结果表明:参数标定精度均在7％以内,是一种实时的在轨标定方法,满足误差补偿要求.冗余惯组在轨标定方法为航天器高精度定姿和定轨提供了一种理论参考.

On Orbit Calibration Method for Redundant Inertial Measurement Units by Satellite and Star Sensors

We proposed a real time on orbit calibration method for redundant laser gyro inertial measurement units.High precision speed and location information from satellite navigation and attitude information from star sensors are used to design the calibration model with ten inertial instruments (five gyros and five accelerometers), including gyros bias and accelerometers bias and scale factor.Standard Kalman filter and Sage Husa adaptive filter are applied as the estimation algorithm and inertial instruments redundant strapdown inertial measurement unit parameters are estimated on line.The results of numerical simulation show that parameters calibration precision is within 7%.It is a kind of real time on orbit calibration method, which satisfies the requirements of error compensation.A theoretical reference for high precision spacecraft position and attitude determination method is proposed by redundant inertial measurement unit on orbit calibration