基于速度增量序列凸化的固体运载火箭制导算法  

Ascent Guidance for Solid Rocket Based on Velocity Increment Successive Convexification

作　　者：陈之润 郑新 赵鹏雷 于煜斌 Chen Zhirun;Zheng Xin;Zhao Penglei;Yu Yubin(Beijing Institute of Astronautics Systems Engineering,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《航天控制》2023年第1期39-46,共8页Aerospace Control

摘　　要：针对高低温偏差下固体发动机推力、耗尽时间和秒耗量散布大的问题,提出了一种以速度模值增量为自变量的固体运载火箭序列凸优化制导算法。该算法以速度增量替代传统的飞行时间为自变量建立动力学模型,采用序列凸优化算法求解多约束耗尽关机制导问题,并基于速度模值增量在线辨识高低温工况,修正内弹道模型。该方法相比以飞行时间为自变量的序列凸优化算法具有更高的制导精度和鲁棒性。最后,通过某型固体运载火箭高空飞行段制导数值仿真,验证了以速度增量为变量的序列凸优化算法和内弹道修正模型的有效性。Aiming at the large deviations of the thrust, mass flow rate and burnout time under different temperatures, a velocity increment based successive convexification method is proposed for solid rocket ascent guidance in this paper. The velocity increment is applied to this method as an independent variable for the dynamic model, and the successive convexification method is adopted by solving the ascent depleted shutdown guidance under multiple constraints. Moreover, the temperature conditions are recognized online by comparing the velocity increment for the purpose of parameters correction of interior ballistics. The precision and robustness of the successive convexification method based on the velocity increment are higher than that based on the flight time. Finally, the proposed guidance is verified through the numerical simulations of the ascent guidance for the solid rocket.

关 键 词：固体发动机 内弹道修正 速度模值增量 序列凸化 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]