超燃冲压发动机变结构进气道设计  

Variable inlet of two dimensional scramjet engine

作　　者：王青[1] 谷良贤[1] 龚春林[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2012年第6期732-735,741,共5页Journal of Solid Rocket Technology

摘　　要：针对超燃冲压发动机宽马赫数、攻角范围内高性能工作要求,建立了基于多目标优化的变结构进气道设计方法,获得了进气道结构随马赫数和攻角变化的调节规律。以总压恢复系数、压升比和阻力系数为优化目标,以二维混压式进气道为对象,采用遗传算法进行了基准进气道优化设计,得到Pareto非劣解;以一组Pareto非劣解为基准,在不同马赫数和攻角下进行了进气道变结构优化设计,拟合得到进气道结构随马赫数和攻角变化曲线。仿真结果证实了理论分析的正确性,并发现进气道变结构实现了发动机大范围内高性能工作;进气道高度可变,使得发动机在亚燃和超燃模态均能正常起动和稳定工作;以高马赫数作为设计马赫数,变结构设计后,发动机性能提高。In order that scramjet engine can work reliably over a wide range of Mach number and attack angles,a multi-objective optimization design for two-dimensional variable inlet was established.Total pressure recovery coefficient,static pressure rise and drag coefficient were selected as objective functions to form the multi-objective optimization of the two-dimensional scramjet mixed compression inlet.Based on one-dimensional aerodynamics analysis method,a multi-objective genetic algorithm was employed to find Pareto solutions on the design-condition.Then for different Mach numbers and angles of attack,optimal variable inlets,of which partial compression angles,angle and length of cowl and inlet height were variable,were obtained.The correctness of theoretical analysis was confirmed by simulations,and several conclusions were achieved.Firstly,the engine could work efficiently through a wide envelop of mach numbers and angles of attack by employing the optimal variable inlets.Secondly,the alterable inlet height makes the engine start and work steadily in both ramjet and scramjet mode.Thirdly,with the high mach number as the design mach number,the engine performance is improved by variable inlet design.

关 键 词：超燃冲压发动机 多目标优化 Pareto非劣解 变结构进气道 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]