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论文:2023,Vol:41,Issue(6):1064-1072 |
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引用本文： |
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闫循良, 王舒眉, 王培臣, 刘海礼. RBCC高超声速飞行器上升段轨迹快速优化[J]. 西北工业大学学报 |
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YAN Xunliang, WANG Shumei, WANG Peichen, LIU Haili. Rapid ascent trajectory optimization of rocket-based combined cycle hypersonic vehicle[J]. Journal of Northwestern Polytechnical University |
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| RBCC高超声速飞行器上升段轨迹快速优化 |
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| 闫循良1, 王舒眉2, 王培臣1, 刘海礼1 |
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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 |
| 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。 |
| 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
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| Rapid ascent trajectory optimization of rocket-based combined cycle hypersonic vehicle |
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| YAN Xunliang1, WANG Shumei2, WANG Peichen1, LIU Haili1 |
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1. School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. COMAC Flight Test Center, Shanghai 201323, China |
| Abstract: |
| 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. |
| Key words:
rocket-based combined cycle
hypersonic vehicle
ascent trajectory optimization
sequential convex optimization
second-order lag of control system
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| 收稿日期: 2022-09-13
修回日期:
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| DOI: 10.1051/jnwpu/20234161064 |
| 基金项目: 国家自然科学基金(11602296)与中央高校基本科研业务费(G2022KY0613)资助 |
| 通讯作者:
Email： |
| 作者简介: 闫循良(1984-),西北工业大学副研究员,主要从事飞行动力学与制导、轨迹设计、协同作战及攻防对抗研究。e-mail:yanxl@nwpu.edu.cn
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