吸气式冲压发动机多点优化设计  

Multi-points design and optimization of air-breathing ramjets

作　　者：王青[1] 郭金雷 谷良贤[3] 

机构地区：[1]西安工程大学机电工程学院,西安710048 [2]上海机电工程研究所,上海201109 [3]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2017年第6期780-784,共5页Journal of Solid Rocket Technology

摘　　要：为满足高超声速飞行器宽速域范围内发动机高性能工作要求,基于实验设计方法和代理模型,建立了吸气式冲压发动机的多点优化设计方法,获得了宽速域范围内性能均较好的发动机最优构型。以推力系数、升力系数和力矩系数为优化目标,以某型高超声速飞行器为对象,选取三个典型状态点进行了冲压发动机的多点优化设计研究,得到了最优构型方案,并将多点最优构型和传统单点最优构型在宽速域范围内的性能进行了对比分析。分析结果显示,多点优化设计方法得到的最优构型在大部分飞行状态下都具有较好的性能,即多点优化设计方法在宽速域范围内确实能够提高冲压发动机性能,证实了该方法的有效性和优势。In order to meet high performance requirements of hypersonic vehicles, a multi-points design and optimization method for the integrated ramjet/scramjet engine was established. Based on the invented methodology here, an optimized engine configuration that works well over a range of flight conditions, was obtained. Taking coefficients of thrust, lift and moment as objective functions, a three-point optimization was done and an optimal ramjet configuration was found, based on Design of Experiment （DOE） and surro- gate model. Then, the performances of the optimal configuration were computed in a wide envelop of Mach numbers （Mas） and angles of attack （AOAs）. Comparing the performances of the optimal configuration with a reference one optimized on a single-point, it has been found that the optimal engine configuration has better performances through a wide flight envelope than the reference one. The results confirm the effectiveness and superiority of multi-points optimization method used in ramjet configuration design.

关 键 词：多点优化 宽速域范围 亚燃冲压发动机 超燃冲压发动机 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]