埋入式进气道设计  

Design of Submerged Inlet

作　　者：郭荣伟[1] 刘少永[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《南京航空航天大学学报》2001年第1期8-12,共5页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：针对导弹用进气道的结构特点，提出了一种大偏距、短扩压的埋入式进气道设计方法．该方法通过变更进气道的中心线、面积规律、中心线的倾斜角及双纽线喉道的设计参数，并通过采用进气道唇口光顺技术成功地实现了埋入式进气道设计的ＣＡＤ化。该ＣＡＤ技术与ＣＦＤ技术的结合能大幅度地缩短埋入式进气道设计周期、降低研制成本。实验结果表明，由该文提出的方法设计的埋入式进气道不做任何型面修改即可达到较好的气动性能。Due to the advantages of submerged inlets in decreasing the frontal drag, reducing the radar cross scction (RCS) to improve the survivability, the submerged inlets have been adopted in many kinds of missiles. Considering the structure characters (big offset and short diffuser) of missile inlet, a design method for the submerged inlets used in the missiles is presented. This approach, by alternating the inlet centre line and area regularity, modifying the parameters of the throat and smoothing the inlet mouth with the aid of computer, can give different profiles of a submerged inlet automatically. Combined this CAD technique with CFD, a variety of submerged inlet can be more quickly and more economically designed. The experimental results show that a submerged inlet with high performance could be obtained from the data provided by the method.

关 键 词：埋入式进气道 中心线 面积规律 喉道 唇口光顺 设计 融合体式 

分 类 号：V228.7[航空宇航科学与技术—飞行器设计]