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为满足深空探测器的精确定姿需求,提出了一种惯性测量单元(IMU)辅助的X射线脉冲星定姿方法。该方法用IMU的速率陀螺来估计航天器短时姿态,观测两颗或多颗脉冲星的X射线辐射信号,将拟合得到的观测矢量作为滤波器信息输入,利用这两种测姿手段在时间和空间上的互补特性,提供一种全天候、抗干扰性强的定姿方法。仿真结果表明,相比于EKF,基于UKF的俯仰、横滚和偏航三姿态角的测量精度可提高21.9%、21.1%和31.7%;与仅使用脉冲星或IMU的定姿方法相比,组合定姿方法的俯仰角估计精度分别提高了32.5%和77.6%。
In order to meet the precise attitude requirements of deep space probes, an inertial measurement unit (IMU) -assisted x-ray pulsar attitude determination method is proposed. The method uses the velocity gyro of IMU to estimate the short-term attitude of the spacecraft, observes the X-ray radiation signals of two or more pulsars, inputs the fitted observation vector as filter information, and utilizes the two attitude measurement methods in Time and space complementary features to provide a weather-based, anti-interference and strong positioning methods. The simulation results show that the accuracy of pitch, roll and yaw attitude measurement based on UKF can be increased by 21.9%, 21.1% and 31.7% compared with EKF. Compared with the pose method using only pulsar or IMU, The accuracy of pitch angle estimation of combined pose method is increased by 32.5% and 77.6% respectively.