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通过对多副天线接收的载波相位测量数据进行差分,全球定位系统(GPS)接收机能确定由天线基线确定的坐标系的姿态。本文调研了使用GPS确定航天器姿态的可能性。肯定了当前GPS的应用情况。考虑了几种可供选择的结构,并且确定了满足大多数应用需要的一种基本结构。本文主要介绍在喷气推进实验室(JPL)的飞行系统试验台(FST)上做过试验的这种基本结构的样机。描述了该试验装置并给出了试验结果。本文分析了GPS定姿误差分配的限制因素,介绍了GPS的应用前景,讨论了为满足这些应用所需做的改进工作。
By differentiating the carrier phase measurement data received by multiple antennas, a global positioning system (GPS) receiver can determine the attitude of the coordinate system as determined by the antenna baseline. This article investigates the possibility of using GPS to determine a spacecraft’s attitude. Affirmed the current GPS applications. Several alternative architectures have been considered and a basic structure that meets the needs of most applications has been identified. This article focuses on a prototype of this basic structure that has been tested on the Flight System Test Bed (FST) of the Jet Propulsion Laboratory (JPL). The test device is described and the test results are given. This paper analyzes the limiting factors of GPS attitude error distribution, introduces the application prospect of GPS, and discusses the improvements needed to meet these applications.