冲压增程弹丸气动及结构设计
摘要本文主要是研究冲压增程弹丸阻力特性以及结合进气道工作特性数据获得发动机的推力，进而对弹丸结构进行设计。首先对影响弹丸阻力的因素进行了分析，从进气道不同捕获面积、不同来流马赫数、进气道不同压缩形式三个因素对弹丸阻力特性的影响进行详细数值仿真研究分析，以数值模拟结果提取弹丸冷态内外阻力系数等相关参数进行详细对比分析，得出各因素对弹丸阻力特性的影响特点。接着对进气道不同锥面形式弹丸在不同马赫数下进行数值模拟，控制反压得出对应的最大总压恢复系数及相应的质量流量系数，计算获得冲压发动机推力。最后对发动机整体和各零部件结构进行设计，并进行了强度校核。60977
毕业论文关键词 冲压增程弹丸 进气道 阻力 总压恢复 结构
毕业设计说明书（论文）外文摘要
Title The aerodynamic and structural design of SFRJ projectile
Abstract
The drags characteristic of the SFRJ projectile was studied in this article, and also the structure design also was studied combined with the data of the inlet characteristics and the engine thrust. Firstly, according to the working principle of the SFRJ projectile, the overall structure of the SFRJ projectile was analyzed. Secondly, the factors affecting the projectile drag was analyzed. A detailed numerical simulation analysis was carried out on the effecting of the drag characteristics of the projectile, from three factors of the different inlet capture area and the different free stream mach number and the different compression form of inlet. Inside and outside drag coefficient of passive flight projectile and other related parameters was extracted from the numerical simulation results, and these parameters were analyzed in detail, then the characteristics has been obtained from the effect of various factors on the projectile drag characteristics. Thirdly, the numerical simulation of projectile was carried out in different cone inlet forms and at different Mach number，and the corresponding maximum total pressure recovery and mass flow ratio were obtained by the form of controlling the back pressure. Next, ramjet thrust was calculated by above data. Finally, whole and each part of the engine structure design and make a strength check.
Keyword SFRJ inlet resistance total pressure recovery structure
目 次
绪论 1
1.1 研究背景与意义 1
1.2.1 冲压增程弹丸技术研究进展 2
1.2.2 关键技术 5
1.3 本文主要研究内容及章节安排 6
冲压增程弹丸气动设计 7
2.1引言 7
2.2 CFD简介 8
2.3 数学模型 9
2.4 模型简化与边界条件 12
2.4.1 模型简化 12
2.4.2 边界条件 13
2.5 弹丸气动设计 14
2.5.1