近年来高超声速飞行器的研究受到世界各国的重视，具有重大的军事意义，其中导航、制导和控制是高超声速研究的关键技术。鉴于星光导航有着抗干扰能力强、导航精度高、自助式导航等特点，文中主要研究了高超声速飞行器使用星光导航方法的星图复原算法。考虑到高超带来的气动光学效应，在分析高速层流以及湍流流场的基础上，应用增量Wiener滤波器和有限支持域上的盲解卷积复原算法进行退化星图的复原。针对高速飞行器星光导航对复原星图的要求，仿真分析了复原星图的质心偏差及识别特征量变化。仿真结果显示，有限支持域上的盲解卷积复原算法精度较高，且经复原后的星图，能快速被高速飞行器星光导航系统正确识别。

In recent years,the hypersonic aircraft technology is paid more and more attention for its great significance for military application. The guidance, navigation and control technology is one of the key technologies of hypersonic aircraft. And as one of widely used automatic navigation method,which is of such advantages as high navigation accuracy, good anti-interference ability, and auto-navigation ability, the restoration algorithm of star map for hypersonic aircraft was studied in this paper. Considered the aero-optical effects caused by hypersonic flight, the simulation of turbulence-degrade star map was studied, and the increment Wiener filter and the restoration algorithm of iterative blind deconvolution in limitation support region were used for restoration of the turbulence-degraded star map, respectively. The simulation result shows that, the latter method is of higher precision and the restored star map can be identified by the celestial navigation system correctly.

传统航天器自主天文导航需要星敏感器、红外地平仪、磁强计等多种敏感器采集导航数据，增加了航天器的成本和复杂度。利用多视场星敏感器的特点，分别对恒星与地球进行成像，在完成姿态测量的同时，得到地心矢量信息，从而进行自主天文导航。首先建立地球几何模型，结合航天器轨道参数与多视场星敏感器的安装布局，实现各个视场内地球边缘的成像模拟，使用Steger算法提取地球边缘。综合考虑地球扁率的影响，对不同视场中观测到的地球边缘进行拟合得到精确地心矢量，最后进行基于星光角距的直接敏感地平导航仿真。仿真结果表明，在一个视场观测恒星，另外两个视场观测地球边缘的布局情况下，地心矢量精度和导航位置精度分别达到0.0172o(1σ)和190 m(1σ)。

The traditional methods for spacecraft autonomous navigation need several sensors, such as star sensor, infrared horizon sensor and magnetometer, to collect navigation data. As a result the load of spacecraft will gain in weight, size and power. Based on the advantages of multi- field of view (FOV) star tracker, an autonomous navigation method was proposed which used multi- FOV star tracker (MFST) to image the star and the earth respectively and got the orientation vectors of them. Combining with the orbit parameters of the spacecraft and the layout of the MFST, a mathematic model of the earth imaging was set up to implement the earth edge images in every single FOV. The Steger method was used to determine the earth edge in the images. Considering the earth oblateness, the orientation vector of the earth will be obtained through circle- fitting the earth edge points in each FOV. With the configuration that one FOV measures the navigation star and the other two FOV measures the earth ed