|Table of Contents|

Research of 2-D reflective supersonic inlet(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2014年01期
Page:
45-49
Research Field:
研究与设计
Publishing date:

Info

Title:
Research of 2-D reflective supersonic inlet
Author(s):
LIU Chang-an;  NAN Xiang-jun;  YAN Zhi-yong
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
-
PACS:
V211.48-34
DOI:
-
Abstract:
The design scheme of reflective supersonic inlet with two-stage compression wedge surfaces was adopted by X-51A vehicle. It is a compromise scheme, in which the multi-objective optimization is required in the inlet design. Proceeding from engine design, the 2-D reflective supersonic inlet similar to the X-51A's inlet is studied in this paper. In this study, the optimization variables were reasonably chosen based on the inlet design parameters, and the multi-objective optimization design of the reflective supersonic inlet with two-stage compression wedge surfaces was executed with the multi-objective particle swarm optimization method (MOPSO) according to the total pressure recovery coefficient, flux coefficient and exit Mach number, which were gotten by solving the 2-D inlet Euler flow equations. Through the optimization, the performance index parameter optimal changing relationship and structure of the supersonic inlet with two-stage compression wedge surfaces were achieved, which can help designers understand their design project and make their decisions better.

References:

[1]徐东来, 陈凤明,蔡飞超, 等. 反折式二元超声速进气道设计及数值研究[J]. 计算机仿真, 2010, 27(4): 67-70.
[2]黎明, 宋文艳, 贺伟. 高超声速二维混压式前体/进气道设计方法研究[J]. 航空动力学报, 2004, 19(4): 459-465.
[3]尤延铖, 梁德旺, 郭荣伟, 等. 高超声速三维内收缩式进气道/乘波前体一体化设计研究评述[J]. 力学进展, 2009, 39(5): 513-525.
[4]MUTZMAN R, MURPHY S. X-51 development: a chief engineer's perspective [R/OL]. [2011-04-13]. https: //www.aiaa.org.
[5]HANK J M, MURPHY J S, MUTZMAN R C. The X-51A scramjet engine flight demonstration program, AIAA 2008-2540[R]. USA: AIAA, 2008.
[6]李建平, 宋文艳, 王靛. 高超声速进气道设计方法研究[J]. 计算机仿真, 2008, 25(9): 50-54.
[7]刘兴洲. 飞航导弹动力装置[M]. 北京: 宇航出版社, 1992.
[8]罗世彬, 罗文彩, 丁猛, 等. 超燃冲压发动机二维进气道多级多目标优化设计方法[J]. 国防科技大学学报, 2004, 26(3): 1-6.
[9]林锉云, 董加礼. 多目标优化的方法与理论[M]. 长春: 吉林教育出版社, 1992.
[10]夏露, 高正红, 苏伟. Pareto遗传算法在气动外形优化中的应用[J]. 空气动力学学报, 2007, 25(2): 194-198.
[11]王允良, 李为吉. 基于混合多目标粒子群算法的飞行器气动布局设计[J]. 航空学报, 2008, 29(15): 1202-1206.
[12]安伟刚. 多目标优化方法研究及其工程应用[D]. 西安: 西北工业大学, 2005.
[13]KENNEDY J, EBERHART R C. Particle swarm optimi- zation[C]// Proceedings of the 1995 IEEE International Conference on Neural Networks.[S.l.]: IEEE, 1995: 1942-1948.
[14]NG K Y, TAN C M. Single and multiobjective wing planform and airfoil shape optimization using a swarm algorithm, AIAA 2003-2004[R]. USA: AIAA, 2003.
[15]张忠峰, 高云峰, 宝音贺西. 基于粒子群优化的高超声速飞行器航迹规划[J]. 系统仿真学报, 2009, 21(8): 2428- 2431.

Memo

Memo:
-
Last Update: 1900-01-01