一种运载火箭二级起控优化设计方法

固体运载火箭一二级分离一般为大气层内热分离,由于分离高度低、速度快,加之运载器气动静不稳定等特点,二级起控稳定性一直是火箭总体方案论证过程中的关键问题之一。针对二级起控影响因素进行了全面分析,提出了姿控参数在线辨识法,有效提高火箭姿态控制精度；提出了基于轨迹倾角的程序角在线构造技术,可有效降低二级起控过程气动干扰,进一步提高火箭二级起控能力,为解决固体运载火箭二级起控难题提供了技术支撑。

An Optimization Design Method for the Second-Stage Start-up Control of Launch Vehicle

Thermal separation schemes were usually used between the first and second stages of solid launch vehicles. Due to the low separation height, high separation speed, as well as the instability of aerodynamic static of the launch vehicles, the stability of the second-stage start-up control has always been a key issue in the overall rocket scheme demonstration. Here the influencing factors of the second-stage start-up control were analyzed comprehensively. The on-line identification methods of parameters for attitude control were proposed to improve the attitude control accuracy of launch vehicle. The on-line configuration methods of the program angle based on orbital inclination were proposed to reduce the aerodynamic interaction and further improve the ability of the second-stage start-up control. It provided technical supports for overcoming the second-stage start-up control problems of solid launch vehicles.