| RBCC动力飞行器上升段轨迹优化设计 |
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| 引用本文： | 罗哲,王舒眉,闫循良,李新三.RBCC动力飞行器上升段轨迹优化设计[J].红外与激光工程,2022,51(8):20210956-1-20210956-8. |
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| 作者姓名： | 罗哲 王舒眉 闫循良 李新三 |
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| 作者单位： | 1.火箭军工程大学 导弹工程学院，陕西 西安 710025 |
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| 基金项目： | 国家自然科学基金（61503390）；陕西省自然科学基础研究计划（2020 JQ-491） |
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| 摘 要： | 针对火箭基组合循环（Rocket Based Combined Cycle，RBCC）动力系统工作模态复杂、与飞行状态耦合程度高的特性，建立了一种适用于RBCC动力高超声速飞行器的动力段轨迹优化模型。同时，针对RBCC动力飞行器，基于凸优化理论建立了上升段轨迹优化设计框架和求解策略。在此基础上，进行了上升段末端机械能最大算例仿真。仿真结果表明，相关模型和轨迹优化方法具备良好的可行性，优化结果符合RBCC动力系统工作特点。论文提出的轨迹优化方法可有效处理复杂工作模态下RBCC助推飞行器上升段轨迹优化问题，为未来关于这一类轨迹设计与优化的工作提供了一些新的思路。
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| 关 键 词： | RBCC 凸优化 上升段 机械能 |
| 收稿时间： | 2021-11-30 |
Trajectory optimization design of ascending stage of RBCC powered hypersonic vehicle |
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| Affiliation: | 1.College of Missile Engineering, Rocket Military Engineering University, Xi’an 710025, China2.Academy of Astronautics, Northwestern Polytechnical University, Xi’an 710072, China |
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| Abstract: | Aiming at the characteristics of complex working mode and high coupling with flight state of rocket based combined cycle (RBCC) power system, a trajectory optimization model for RBCC powered hypersonic vehicle was established. At the same time, the trajectory optimization design framework and solution strategy for RBCC powered aircraft were established based on convex optimization theory. On this basis, the maximum mechanical energy at the end of the rising section was simulated. The simulation results show that the relevant models and trajectory optimization methods are feasible, and the optimization results accord with the working characteristics of RBCC power system. The trajectory optimization method proposed in this paper can effectively deal with the trajectory optimization of RBCC assisted aircraft in the ascending phase under complex working modes, and provides some new ideas for this kind of trajectory design and optimization in the future. |
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