高压捕获翼位置设计方法研究
THE DESIGN METHOD RESEARCH FOR THE POSITION OF HIGH PRESSURE CAPTURING WING
查看参考文献34篇
|
文摘
|
高压捕获翼构型是一种合理利用机体/上置翼(简称捕获翼)间的耦合关系提高飞行器升力,进而大幅提高升阻比的高速飞行器新概念构型. 基于其设计原理,捕获翼的位置与机体压缩激波和自身二次压缩激波的位置均直接相关,一般难以利用理论方法直接获得. 针对这一问题,本文运用均匀实验设计方法在设计空间内获取样本点并利用计算流体力学分析和迭代获得其设计位置,之后通过构造代理模型建立捕获翼位置与设计参数间的模拟映射关系,进而发展了一种捕获翼位置设计的有效方法. 在方法研究基础上以锥体--捕获翼组合构型作为实例对其进行验证. 结果表明,该方法可在较大设计空间范围内准确判定捕获翼的设计位置. 此外,针对这一构型还开展了基于代理模型的设计参数单因素分析. 发现在设计空间内,前缘压缩角、来流马赫数、和捕获翼钝化半径等3个关键参数均与捕获翼位置呈单调正比例关系. |
|
其他语种文摘
|
The high pressure capturing wing configuration is a novel conceptual form which improves lift and lift-todrag ratios by the coupling relationship between the body and HCW. Based on the deign principle, the HCW position is determined by body compression shock and its own compression shock, while it is hard to obtain directly using theory. In order to solve this problem, this paper developed a kind of effective method to design the position of capturing wing. The method is based on the analysis of parameters which determine the position of capturing wing, combined with the uniform experimental design method, the computational fluid dynamics analysis and surrogate model building to obtain the relationship between the position of capturing wing and the design parameters. The results from the validation case of cone body combination with capturing wing showed that this method can determine the optimal position of capturing wing in a large design space. In addition, cone compression angle, free field Mach number and blunted radius of capturing wing are the key parameters affecting the position of capturing wing for the cone combination capturing wing. The results from the analysis of surrogate model showed that the position of capturing wing is in monotonic proportional relationship among the above three parameters. |
|
来源
|
力学学报
,2016,48(3):576-584 【核心库】
|
|
DOI
|
10.6052/0459-1879-15-391
|
|
关键词
|
高速飞行器
;
高压捕获翼
;
均匀实验设计
;
多项式代理模型
|
|
地址
|
中国科学院力学研究所, 高温气体动力学国家重点实验室, 北京, 100190
|
|
语种
|
中文 |
|
文献类型
|
研究性论文 |
|
ISSN
|
0459-1879 |
|
学科
|
力学;航空、航天技术的研究与探索;航空 |
|
基金
|
国家自然科学基金资助项目
|
|
文献收藏号
|
CSCD:5713551
|
参考文献 共
34
共2页
|
|
1.
Kuchemann D.
The Aerodynamic Design of Aircraft,1978
|
被引
13
次
|
|
|
|
|
2.
叶友达. 近空间高速飞行器气动特性研究与布局设计优化.
力学进展,2009,39(6):683-694
|
被引
46
次
|
|
|
|
|
3.
Sullivan R B.
X-34 program overview. AIAA Paper 1998-3516,1998
|
被引
2
次
|
|
|
|
|
4.
Jazra T. Design of an airbreathing second stage for a rocket-scramjet-rocket launch vehicle.
Journal of Spacecraft and Rockets,2013,50(2):411-422
|
被引
6
次
|
|
|
|
|
5.
Walker S.
The DARPA/AF falcon program: The hypersonic technology vehicle #2 (HTV-2) flight demonstration phase. AIAA Paper 2008-2539,2008
|
被引
2
次
|
|
|
|
|
6.
Walker S.
TBCC propulsion for a mach 6 hypersonic airplane. AIAA Paper 2009-7238,2009
|
被引
2
次
|
|
|
|
|
7.
Nonweiler T R F. Delta wings of shapes amenable to exact shockwave theory.
Journal of the Royal Aeronautical Society,1963,67:39-40
|
被引
11
次
|
|
|
|
|
8.
Bowcutt K G.
Viscous optimized hypersonic waveriders. AIAA Paper 1987-0272,1987
|
被引
2
次
|
|
|
|
|
9.
Corda S.
Viscous optimized hypersonic waveriders designed from axisymmertirc flow fields. AIAA-88-0396,1988
|
被引
2
次
|
|
|
|
|
10.
Rodi P E.
Integration of optimized leading edge geometries onto waverider configurations. AIAA 2015-1700,2015
|
被引
1
次
|
|
|
|
|
11.
Liu J. Novel approach for designing a hypersonic gliding-cruising dual waverider vehicle.
Acta Astronautica,2014,102:81-88
|
被引
8
次
|
|
|
|
|
12.
Lobbia M.
Optimization of waverider-derived crew reentry vehicles using a rapid aerodynamics analysis approach. AIAA Paper 2015-0757,2015
|
被引
2
次
|
|
|
|
|
13.
Cui K. Waverider configurations derived from general conical flowfields.
Acta Mechanica Sinica,2007,23(3):247-255
|
被引
9
次
|
|
|
|
|
14.
Cui K. The effect of conical flowfields on the performance of waveriders at Mach 6.
Chinese Science Bulletin,2007,52(1):51-64
|
被引
4
次
|
|
|
|
|
15.
Liu J. Numerical and experimental study on waverider with blunt leading edge.
Computers & Fluids,2013,84:203-217
|
被引
2
次
|
|
|
|
|
16.
Santos W F N.
Leading edge thickness impact on drag and lift in hypersonic wedge flow. AIAA Paper 2007-615,2007
|
被引
1
次
|
|
|
|
|
17.
Lobbia M. Experimental investigation of a mach 3.5 waverider designed using computational fluid dynamics.
AIAA Journal,2014,53(6):1590-1601
|
被引
18
次
|
|
|
|
|
18.
崔凯. 6马赫锥体流场对乘波体性能的影响及规律.
科学通报,2006,57(24):2830-2837
|
被引
4
次
|
|
|
|
|
19.
张锋涛. 基于神经网络技术的乘波体优化设计.
力学学报,2009,41(3):418-424
|
被引
7
次
|
|
|
|
|
20.
Li Y.
Integration methodology for waveriderderived hypersonic inlet and vehicle forebody. AIAA Paper 2014-3229,2014
|
被引
1
次
|
|
|
|
|
了解气象卫星更多信息，请访问