RBCC动力巡航飞行器爬升段弹道优化

国防科技大学 高超声速技术实验室,湖南 长沙 410073

火箭基组合循环发动机; 巡航飞行器; 爬升段; 弹道优化

Ascent trajectory optimization for RBCC powered cruise vehicle
XU Zheng, TAN Jianguo, ZHANG Dongdong

Hypersonic Technology Laboratory, National University of Defense Technology, Changsha 410073, China

RBCC; cruise vehicle; climbing phase; trajectory optimization

DOI: 10.3969/j.issn.1672-9374.2024.02.005

备注

RBCC动力飞行器爬升段弹道设计是其总体设计的重要问题之一。采用伪谱法对基于RBCC动力的巡航飞行器开展了弹道优化研究。以爬升段推进剂消耗量最小为性能目标,以飞行攻角为设计变量,建立了飞行器纵向平面内弹道优化模型,在获得飞行器气动特性和RBCC发动机性能的基础上,开展了爬升段弹道优化。结果表明:最优弹道包括平飞加速、等动压爬升、等速爬升等阶段; 火箭发动机应当以“开-关-开”模式工作,且火箭发动机无需大范围调节; 在适当的火箭发动机最大流量和动压约束下,该飞行器的动力段航程达到2 430 km。
The climbing trajectory optimization of the vehicle employing rocket based combined cycle(RBCC)engine has been an important issue during the overall design. The pseudo-spectral method was employed to perform the trajectory optimization of RBCC cruise vehicle. Taking the consumption of propellant as the performance index and the flight attack angle as the design variable, the longitudinal plane trajectory optimization model of the vehicle was established. Aerodynamic characteristic of the vehicle and the performance of RBCC were obtained, then climbing trajectory of the vehicle was optimized. Results show that: optimal trajectory includes acceleration with constant height, climbing with constant dynamic pressure, climbing with constant speed, etc; rocket engine works in mode of open-close-open, and there is no need to adjust rocket thrust greatly; the range of the vehicle reaches 2 430 km under the condition of appropriate maximum mass flow rate of rocket engine and appropriate constraint of dynamic pressure.
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