火箭推进

二元进气道常用于宽速域吸气式飞行器,相比于巡航类的飞行器,宽速域飞行器的飞行速域较大,进气道要兼顾高低速条件下的飞行要求存在一定的困难。提出了一种自由造型的二元进气道设计方法,采用类别形状函数法对二元进气道的压缩面进行参数化建模,将函数的控制参数作为优化变量直接对压缩面进行优化,设计时无须选择设计点。同时,根据进气道吸入流量和发动机需求流量之间的匹配关系,提出了一种适用于宽速域二元进气道优化设计的目标函数。结果表明,优化得到的二元进气道在马赫数2.5到8的范围内总压恢复系数和流量系数均能满足设计要求。

Two-dimensional air inlet is often used in wide-speed range air-breathing aircraft. Compared with cruise-type aircraft,the flight speed range of wide-speed range aircraft is larger,and it is difficult for the inlet to meet the flight requirements under both high-speed and low-speed conditions. A design method for the two-dimensional inlet with free-configuration is proposed in this paper. It uses the category shape function method to parametrically model the compression surface of the two-dimensional inlet. The control parameters of the function as optimization variables are used to optimize the compression surface directly,and there is no need to select design points during the design. In addition,according to the matching relationship between the intake flow and the demand flow of engine,an objective function suitable for the optimal design of a wide-speed two-dimensional inlet is proposed. The results show that both the flow coefficient and total pressure recovery coefficient can meet the design requirements in the range of Mach number 2.5 to 8.

引言
1 研究流程
2 目标函数
3 设计方法
4 算例分析
5 结论

图1 自由造型的二元进气道设计流程图<br/>Fig.1 Design flow chart of two-dimensional inlet with free-configuration

图1 自由造型的二元进气道设计流程图
Fig.1 Design flow chart of two-dimensional inlet with free-configuration

图2 自由造型的二元进气道构型<br/>Fig.2 Structure of two-dimensional inlet with free configuration

图2 自由造型的二元进气道构型
Fig.2 Structure of two-dimensional inlet with free configuration

图3 不同类别函数代表的几何外形
Fig.3 Geometric profile of different types of functions

图4 二元进气道基准构型<br/>Fig.4 Basic configuration of two-dimensional inlet

图4 二元进气道基准构型
Fig.4 Basic configuration of two-dimensional inlet

表1 优化变量取值范围<br/>Tab.1 Value range of optimization variables

表1 优化变量取值范围
Tab.1 Value range of optimization variables

图5 Isight求解过程<br/>Fig.5 Solving process of Isight

图5 Isight求解过程
Fig.5 Solving process of Isight

图6 目标函数收敛过程<br/>Fig.6 Convergence process of objective function

图6 目标函数收敛过程
Fig.6 Convergence process of objective function

表2 优化变量的取值<br/>Tab.2 Values of optimization variables

表2 优化变量的取值
Tab.2 Values of optimization variables

表3 全速域内的计算状态<br/>Tab.3 Calculation status in the full speed range

表3 全速域内的计算状态
Tab.3 Calculation status in the full speed range

图7 气动计算结构网格<br/>Fig.7 Structure grid of aerodynamic computing

图7 气动计算结构网格
Fig.7 Structure grid of aerodynamic computing

图8 优化构型的马赫数云图<br/>Fig.8 Mach number cloud map of optimized configuration

图8 优化构型的马赫数云图
Fig.8 Mach number cloud map of optimized configuration

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备注

引言

1 研究流程

2 目标函数

3 设计方法

4 算例分析

5 结论

期刊信息