In order to enable the micro-nanosatellites equipped with microthrusters to better complete various space applications, it is necessary to estimate the thrust performance of the microthrusters in real-time on orbit. This paper proposes a real-time on-orbit estimation method for microthrust based on high-precision orbit determination. By establishing a high-precision orbit dynamic model, the microthrust generated by a microthruster is modeled as a first-order Markov model, combined with a high-precision GNSS measuring device, and the satellite position is obtained through the cubature Kalman filter algorithm, velocity, and thrust real-time on-orbit estimates. For a thrust of 100 μN, the error accuracy of the on-orbit estimation is 3.98%; for a thrust of 500 μN, the error accuracy is 1.79%; for a thrust of 5 mN, the error accuracy can be reduced to 1.43%; and when the thrust is 500 μN, the accuracy of orbit determination is 16 cm. This method solves the problem that the traditional on-orbit thrust estimation method cannot perform real-time on-orbit estimation of microthrust on the order of hundreds of μN. The real-time on-orbit estimation of microthrust of micro-nanosatellites equipped with microthrusters of the order of hundreds of micronewtons or even several mN to tens of mN has certain reference value.

中文翻译：

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基于高精度定轨的微型推进器推力实时在轨估计方法

为了使搭载微推进器的微纳卫星能够更好地完成各种空间应用，需要对微推进器的在轨推力性能进行实时估计。提出一种基于高精度定轨的微推力实时在轨估计方法。通过建立高精度轨道动力学模型，将微推力器产生的微推力建模为一阶马尔可夫模型，结合高精度GNSS测量装置，通过体积卡尔曼滤波算法、速度，并推动实时在轨估计。对于100 μ N的推力， 在轨估计误差精度为3.98%；推力为 500  μN，误差精度为1.79%；对于5 mN的推力，误差精度可以降低到1.43%；当推力为500  μ N时，定轨精度为16 cm。这种方法解决了问题，即传统的在轨推力估计方法不能执行实时微小推力的几百的数量级上在轨估计μ N.配微型纳米卫星的微小推力的实时在轨估计几百微牛顿甚至几mN到几十mN量级的微型推进器具有一定的参考价值。