CAJ | 학술논문

为提升空间非合作编队任务中卫星态势感知能力和工程冗余度,结合姿态和两星相对位置的耦合信息,提出了一种无角度测量信息的姿态与相对轨道一体化滤波算法.滤波器系统方程取惯性系下的误差四元数姿态和卫星轨道系下相对运动表述,通过扩展卡尔曼滤波实现对卫星姿态指向、陀螺零偏、相对位置速度的联合有效估计.针对跟飞和绕飞两种典型卫星编队模式和不同相对运动构型尺度下该滤波器的局部可观测性进行了比较与分析.地面仿真实验表明,相对导航位置误差0.3 m,相对速度估计误差10-4 m/s,卫星姿态估计误差0.05°,陀螺零偏估计误差10-4(°)/s,满足编队卫星任务需求.
위제승공간비합작편대임무중위성태세감지능력화공정용여도,결합자태화량성상대위치적우합신식,제출료일충무각도측량신식적자태여상대궤도일체화려파산법.려파기계통방정취관성계하적오차사원수자태화위성궤도계하상대운동표술,통과확전잡이만려파실현대위성자태지향、타라령편、상대위치속도적연합유효고계.침대근비화요비량충전형위성편대모식화불동상대운동구형척도하해려파기적국부가관측성진행료비교여분석.지면방진실험표명,상대도항위치오차0.3 m,상대속도고계오차10-4 m/s,위성자태고계오차0.05°,타라령편고계오차10-4(°)/s,만족편대위성임무수구.
To enhance the attitude perception of the satellites and engineering redundancy in the space non-cooperative mission, a filtering algorithm based on the integration of attitude and relative orbit while without acknowledging angle information was presented which combined with the attitude and the coupling information of the two satellites' relative position. The error quaternion-based attitude equation under inertial frame and the relative motion equation under satellite orbit frame were used as the filter's system equation, and the joint efficient estimation of satellite attitude stability, zero bias of gyros and relative position and velocity was realized by using extended Kalman filtering(EKF). Comparison and analysis were made on two classical satellite formation models (leader-follower and fly-around) and the filter's local observability in different structure and scale in relative motion. The effectiveness of the algorithm is validated by some simulation experiments. Simulation results show that the relative position estimation error and velocity estimation error were 0.3 m and 10-4 m/s respectively, the attitude determination error was 0.05° and the gyro bias estimation error was 10-4 (°)/s, which satisfy the mission requirements for satellite formation.