Aerothermodynamics for reusable launch systems

被引：12

作者：

Weiland, C ^{[1
]}

Longo, J

Gülhan, A

Decker, K

机构：

[1] EADS ST, D-81663 Munich, Germany

[2] DLR Inst Aerodynam & Flow Technol, D-38108 Braunschweig, Germany

[3] DLR Inst Aerodynam & Flow Technol, D-51170 Cologne, Germany

[4] Tech Univ Munich, Lehrstuhl Fluidmech, D-85748 Garching, Germany

来源：

AEROSPACE SCIENCE AND TECHNOLOGY | 2004年 / 8卷 / 02期

关键词：

reusable launch vehicles; hypersonic flow; aerothermodynamics; high enthalpy windtunnel experiments; numerical simulations;

D O I：

10.1016/j.ast.2003.09.003

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The development of modem spacecrafts (launch and re-entry vehicles), either fully reusable or partly reusable needs powerful tools for the design of the aerodynamic shape with a guarantee for reliable flight and controllability along the complete ascent and descent trajectories. Experimental and numerical tools are available these days and for improving the reliability of vehicle design their capability has to be improved step by step. In the frame of the German TETRA Program very detailed technology work was carried out to reach this goal. The growth of the efficiency of these methods is demonstrated by some specific aerothermodynamic problems which are reported in this paper. (C) 2003 Elsevier SAS. All rights reserved.

引用

页码：101 / 110

页数：10

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