弹用二元混压超声速进气道设计与试验研究

【作者】 董家峰；

【导师】 李进贤；

【作者基本信息】 西北工业大学 ， 航空宇航推进理论与工程， 2007， 硕士

【摘要】 固体火箭冲压发动机以其良好的性能和巨大的潜在应用优势为世界航空和航天所瞩目，而超声速进气道是其关键部件之一，开展相关研究具有重要的理论意义和工程应用价值。 文中论述了弹用进气道的发展和国内外研究现状，分析了超声速进气道的特点，分别研究了二维和三维混压式超声速进气道的设计方法，采用等激波强度法对唇口楔角混压式进气道进行了设计，并对设计点和非设计点流场进行了数值模拟，通过对数值模拟结果的分析，确定了性能最优的进气道型面方案和进气道布局方案；在理论分析基础上，设计了进气道1／3缩比模型，对缩比模型进行了吹风试验。结合数值模拟和风洞试验的结果，对进气道流场特征进行了研究。 进行了多方案二元混压超声速进气道设计和筛选，确定了主设计方案，并完成试验研究。实验结果表明，按该设计理论设计的进气道在一定马赫数、攻角和侧滑角范围内具有良好的工作性能，满足了设计要求，研究中采用的一维波系设计、二维仿真选择进气道型面、三维仿真确定进气道布置方案、通过模型风洞吹风试验验证的技术路线是高效、合理、可行的。更多还原

【Abstract】 Due to the good performance and potential appliance dominance of the solid rocket ramjet,the attention of many countries focuses on the study of the solid rocket ramjet. Consequently the study of supersonic inlet is significant in theory and engineering application.This thesis introduces the development of the solid rocket ramjet technology domestically and abroad. Characteristics of supersonic inlet are analyzed in this paper. The design methods of two-dimensional and three-dimensional mixed compression supersonic inlet and isolater are studied. The two-dimensional mixed compression supersonic inlet with wedge lip is designed by using the method of equal shock wave intensity. The software was employed to simulate the flow field of the design and off-design conditions. The optimal scheme was determined by adjusting the model size of two-dimensional inlet and the distribution of inlet. On the basic of theory analysis, a 1/3 scale model of a 2-D mixed-compression supersonic intake was tested. the two-dimensional mixed compression supersonic inlet has been studied experimentally and numerically.Through many schemes design and filter of 2-D mixed-compression supersonic intake, confirm the design scheme of experimental investation. The experimental results show that according as this design method, to a certainty range of mach number, attack angle and sideslip angle, intake has favorable capability. In the process of study, it is a supernal efficiency and reasonable and feasible technical route to designed by one-dimensional wave series theory and confirmed the model size of inlet by two-dimensional numerical simulation and confirmed the distribution of inlet by the three-dimensinal numerical simulation and tested by wind tunnel test of reduced scale model.更多还原