In this paper aerodynamic characteristics of maneuvering reentry vehicle of cruciform configuration and bifurcate configuration are compared by means of the wind tunnel test results. 利用典型状态的风洞试验结果对十字布局与叉字布局再入机动飞行器的气动特性进行了分析与比较。
Angle-of-attack and sideslip-angle are two important parameters for the aerodynamic analysis of reentry capsules of spacecraft from flight test data. 迎角和侧滑角是飞船返回舱再入飞行试验气动分析工作所需的重要参数。
The implement scheme, test system design, sub-missile position to reentry, balance of sub-munition and test results for interference force test of sub-missile in FL-31 hypersonic wind tunnel are presented in this paper. 本文给出了子母弹模型在高超声速风洞中的分离干扰测力的试验方案、试验系统设计、网格位置、天平研制和干扰试验结果。
For reentry capsules of spacecraft, making up the trajectory in black-out area is a key link of aerodynamic analysis from flight test data. 对于飞船返回舱,黑障区弹道再现是再入飞行试验气动分析工作的重要环节。
Arc-heated Wind Tunnel is one of the important ground-based experimental equipments to simulate the real reentry environment of the space aircraft. The test of Thermal Protecting System ( TPS) property and ablating experiments of thermal protecting materials need to be proceeded in Arc-heated Wind. 电弧加热风洞是用于模拟空间飞行器再入大气层飞行时真实环境的重要设备之一,返回式飞行器的热防护系统性能测试以及防热材料烧蚀试验都需要在电弧加热风洞中进行。