Research on star-tracking correction technology for near-earth flight vehicles

By analyzing the traditional star-tracking correction technology,this paper studies the star-tracking direct correction method which is based on star sensor dynamic separation initial displacement angles and main errors of inertial measure unit（IMU） in order to carry out automatic navigation and improve the hitting accuracy and quick reaction capability of near-earth flight vehicles.Through comprehensive application and improvement of the best correction factor method,this paper proposes the startracking comprehensive correction method which combines the two methods above-mentioned and the accelerometer dynamic error separation technology.The simulation results show that obvious effects can be achieved by using the star-tracking integrated correction method.

星型装药固体火箭发动机工作过程仿真研究

基于FLUENT软件的UDF二次开发模块,完成了星型装药燃面点火和燃面退移的建模,研究了星型装药固体火箭发动机点火和燃面退移过程,结果表明:星型装药固体火箭发动机工作时,装药头部与尾部存在一定的压强差;相比于星根区域,星角区域的点火过程进行的更加缓慢;采用商用FLUENT软件可以实现简单的星型装药燃面退移过程模拟。