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.
檀朋硕,张青,王勇,等. 一种运载火箭二级起控优化设计方法[J]. 科学技术与工程, 2021, 21(36): 15454-15459.
Tan Pengshuo, Zhang Qing, Wang Yong, et al. An Optimization Design Method for the Second-Stage Start-up Control of Launch Vehicle[J]. Science Technology and Engineering,2021,21(36):15454-15459.