The invention provides a micro-thrust high-precision on-orbit estimation method. The micro-thrust high-precision on-orbit estimation method comprises the following steps: selecting the same arc section of two adjacent circles of a satellite for testing; in the first circle of test arc section, the thruster is not started, the angular speed of the satellite, the rotating speed of the momentum wheel and the moment of the magnetic torquer are recorded, the angular momentum and the angular momentum change rate of the momentum wheel in a satellite body coordinate system in the first circle of test arc section are calculated, and an environment moment estimated value is calculated; in the second circle of test arc section, the thruster is started, the angular speed of the satellite, the rotating speed of the momentum wheel and the moment of the magnetic torquer are recorded, the angular momentum and the angular momentum change rate of the momentum wheel of the second circle of test arc section in the satellite body coordinate system are calculated, and the estimated value of the thrust moment of the thruster is calculated according to the estimated value of the environment moment obtained by the first circle of test arc section; and calculating a thrust estimation value according to the relationship between the thrust moment and the thrust. The micro-thrust high-precision on-orbit estimation method is high in thrust estimation precision and suitable for on-orbit estimation of thrust below the hundred-milliN magnitude.
本发明提供一种微推力高精度在轨估计方法,包括如下步骤:选择卫星相邻两个圈次的相同弧段进行试验;在第一圈试验弧段中,推力器不开机,记录卫星的角速度、动量轮转速、磁力矩器力矩,计算第一圈试验弧段动量轮在卫星本体坐标系中的角动量和角动量变化率,并计算环境力矩估计值;在第二圈试验弧段中,推力器开机,记录卫星的角速度、动量轮转速、磁力矩器力矩,计算第二圈试验弧段动量轮在卫星本体坐标系中的角动量和角动量变化率,根据第一圈试验弧段获得的环境力矩估计值,计算推力器推力力矩估计值;根据推力力矩与推力的关系,计算推力估计值。本发明的微推力高精度在轨估计方法,推力估计精度高,适合百毫牛量级以下推力在轨估计。
Micro-thrust high-precision on-orbit estimation method
一种微推力高精度在轨估计方法
2024-01-30
Patent
Electronic Resource
Chinese
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