逃逸飞行器模型高超声速风洞自由翻滚动导数试验技术

 高超声速风洞模型自由翻滚动导数试验技术是为满足航空航天飞行器 0°～ 360°全攻角范围内的动导数测量及产生极限环振动现象的研究之急需而研制。简要介绍了试验技术研制的自由翻滚试验装置、液体轴承、角度测试系统与系统建模的大攻角非线性数据处理技术。该项技术已成功地为逃逸飞行器模型提供了满意的试验数据

FREE TUMBLING DYNAMIC STABILITY DERIVATIVE TEST TECHNIQUE FOR THE ESCAPE CAPSULE MODEL AT HYPERSONIC WIND TUNNEL

The wind tunnel test technique for dynamic stability derivatives of the model free to tumble at hypersonic speeds has been developed to meet the urgent needs for dynamic derivative measurements of aerospace vehicles at angles of attack of 0°～360° and for mechanism study of limit cycle oscillation phenomenon. Both the hardware of the test technique, such as free tumbling test rigs, liquid bearing, angular measurement system, etc. , and the software, non linear system identification data processing technique are introduced concisely in this paper. By this technique, applicable hypersonic dynamic stability derivatives data of the escape capsule model have been obtained successfully.