亚轨道飞行器上升段制导方法研究

Research on Guidance of the Ascent of Suborbital Launch Vehicle

为了更好地满足亚轨道飞行器的制导任务需求,基于亚轨道飞行器面对称的升力体外形,采用直线斜率形式的迎角变化规律,改进了现有的运载火箭制导方法。把直线斜率形式和指数形式的迎角变化规律对弹道的影响进行了对比。结果表明,直线斜率形式的迎角变化规律相对于指数形式的迎角变化规律具有转弯段时间可调性强、转弯效率高的优点,该项研究为相关领域研究提供了理论参考。

In order to plane symmetry lifting body satisfy the guidance task of Suborbital Launch Vehicle （SLV）, based on the SLV＇ s figuration, the SLV selects the straight slope formal attack angle,mending the of Launch Vehicle. This paper compares the attack angle change rule of straight slope form with exponen guidance tial form. The simulation results demonstrate that the straight slope formal attack angle change rule has better time adjustability in corner section and higher turning efficiency than the exponential attack angle change rule,which provides a theory reference to the study of relevant field.