RBCC高超声速飞行器上升段轨迹快速优化  

Rapid ascent trajectory optimization of rocket-based combined cycle hypersonic vehicle

作　　者：闫循良[1] 王舒眉 王培臣 刘海礼 YAN Xunliang;WANG Shumei;WANG Peichen;LIU Haili(School of Astronautics,Northwestern Polytechnical University,Xi′an 710072,China;COMAC Flight Test Center,Shanghai 201323,China)

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]中国商飞民用飞机试飞中心,上海201323

出　　处：《西北工业大学学报》2023年第6期1064-1072,共9页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(11602296);中央高校基本科研业务费(G2022KY0613)资助。

摘　　要：针对火箭基组合循环(RBCC)高超声速飞行器上升段轨迹设计所具有的动力系统工作模态复杂、推力与飞行状态存在强耦合、模型强非线性且存在多种复杂约束限制等典型特征,设计了一种基于序列凸优化的RBCC动力上升段轨迹快速优化方法。针对攻角控制系统是否存在二阶滞后情况,分别建立了适用于RBCC高超声速飞行器上升段轨迹优化的数学模型。基于凸优化理论对原优化模型进行凸化和离散化处理,进而设计了改进的轨迹优化求解策略。以末端机械能最大为优化指标,针对攻角控制系统存在/不存在二阶滞后的情况分别进行了上升段轨迹优化仿真。结果表明,所构建模型和轨迹优化方法可以快速、有效地完成RBCC高超声速飞行器上升段轨迹优化,优化结果符合RBCC动力系统工作特点,且可为RBCC动力运用和攻角控制系统设计提供参考。The ascent trajectory design of a rocket-based combined cycle(RBCC)hypersonic vehicle has many typical characteristics,including the complex working mode of the RBCC power system,strong coupling between thrust and flight state,strong nonlinear model and many complex constraints etc.This paper proposes a rapid trajectory optimization method based on sequential convex optimization to optimize the complex ascent trajectory with the RBCC power system.Firstly,a mathematical model for optimizing the ascent trajectory of the RBCC hypersonic vehicle is established to describe the angle of attack control system with and without the second-order lag.Then,the optimization model is made convex and discretized based on the convex optimization theory,and a trajectory optimization strategy is improved.Finally,taking the maximum terminal mechanical energy as optimization objective,the ascent trajectory optimization is simulated in cases with and without the second-order lag in the angle of attack control system.The simulation results show that the proposed mathematical model and the ascent trajectory optimization method are rapid and reliable and that the optimization results meet the characteristics of the RBCC power system and provide reference for the application of a RBCC power system and the design of an angle of attack control system.

关 键 词：RBCC 高超声速飞行器 上升段轨迹优化 序列凸优化 控制系统二阶滞后 

分 类 号：V412.44[航空宇航科学与技术—航空宇航推进理论与工程]