远程能量输送飞行器轨道设计与优化  

Design and Optimization of the Long-Distance Energy Transmission Aircraft Trajectories

作　　者：刘纪福[1] 宋笔锋[1] 李占科[1] 

机构地区：[1]西北工业大学航空学院,陕西西安710072

出　　处：《飞行力学》2008年第5期51-54,共4页Flight Dynamics

基　　金：武器装备探索研究项目(7130629-2)

摘　　要：以微波、激光等新型推进技术为背景,在飞行器质点动力学方程基础上,采用序列二次规划算法对飞行器爬升段和盘旋下滑段飞行轨道进行了优化设计,并通过数值仿真给出了其最佳飞行轨道。结果表明,对于重量150 kg,最大升阻比为25的飞行器,在上升段动力系统最大推重比为0.6的情况下,飞行器可以10min爬升到预定的40 km高度;在盘旋下滑段提供4.8 kg的推力,飞行时间可达4.85 h。研究结果为该新型飞行器可行性提供了理论依据。At the background of new propulsion technology, such as microwave, laser, based on the aircraft particle dynamics model, using the sequential quadratic programming arithmetic to design and optimize the air craft＇ s climb and loitering flight trajectories and the optimized trajectories are given by numerical simulation. The results show that the aircraft with 150 kg, maximum lift-to-drag ratio 25 can climb up to 40 km altitude in 10 rain based on maximum thrust-to-weight ratio 0. 6 for climb phase. For loiter phase, loiter time can reach 4. 85 h with maximum thrust 4. 8 kg. The research provides theory support to the feasibility of the new aircraft.

关 键 词：推进技术 质点动力学 飞行轨道 序列二次规划算法 优化设计 数值仿真 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]