本文已被：浏览 1025次 下载 0次
中文摘要: 本文研究了基于星载GPS的简化动力学实时精密自主定轨模型和算法，并将实时自主定轨软件应用于浙江大学皮星二号（ZDPS-2）在轨飞行任务中去。本文阐述了软件所采用的动力学模型、观测模型和估计算法框架，以及实现时所采取的可靠性设计方法。在此基础上，利用GRACE卫星GPS接收机在轨数据，对该自主研发的实时精密自主定轨软件进行了验证。结果表明：实时定轨位置精度在X、Y、Z三轴上的RMS (Root-Mean-Square)值分别为1.3133m、0.9052m、0.9648m，速度精度在X、Y、Z三轴上的RMS值分别为2.1mm/s、1.2mm/s、1.5mm/s，接近国际研究水平。此外，基于皮星二号任务载荷-微型单频GPS接收机进行了半实物仿真试验。结果表明：定轨位置精度达到5m左右，速度精度达到10mm/s以内，与接收机自身定轨软件解算结果对比，定轨精度得到大幅提升，使其能满足一般皮纳卫星的应用需求 。
Abstract:The present study investigates the algorithm and prototype implementation of real-time reduced dynamic orbit determination based on a spaceborne GPS receiver, and the software of real-time orbit determination (RTOD) has applied to the mission of ZDPS-2. This paper describes the dynamic model of the spacecraft motion, the GPS measurement model, the estimation filter model, as well as the method to ensure the reliability of RTOD solution. Then, a simulative test has carried out to process spaceborne GPS flight data from the GRACE satellite using the RTOD software. This test demonstrates that the position accuracy (RMS) of the orbits in X, Y, Z axes is 1.3133m、0.9052m、0.9648m respectively and the velocity accuracy (RMS) in X, Y, Z axes is 2.1mm/s、1.2mm/s、1.5mm/s respectively, which is comparable to the international level. Moreover, hardware-in-the-loop simulation has been performed for the ZDPS-2 satellite, making use of the single-frequency GPS receiver measurements. The results show that the RTOD solution is able to achieve the position accuracy (RMS) of about 5m and the velocity accuracy (RMS) of about 10mm/s, meaning that the orbital accuracy is improved as compared to the single-point orbit solution of the GPS receiver itself. So the RTOD algorithm and software can meet the requirement of nano-satellite applications like the ZDPS-2 satellite.
keywords: Real-time orbit determination ZDPS-2 GRACE satellite Hardware-in-the-loop simulation GPS receiver
文章编号：cg16000122 中图分类号： 文献标志码：
基金项目:国家自然科学基金
引用文本：