空气动力学学报Issue(3)：315-319,5.DOI:10.7638/kqdlxxb-2013.0039
再入飞行器压心测量方法研究
Neasurement of pressure center of re-entry vehicle module
秦永明 1魏忠武 1董金刚 1陈强 1张江1
作者信息
- 1. 中国航天空气动力技术研究院，北京 100074
- 折叠
摘要
Abstract
In conventional force measure wind tunnel test,the balance can get the aerodynamic force of the aircraft and also the directly moment .It is while the pressure center is usually considered as the intersec-tion point between aerocraft's longitudinal axis and its aerodynamic force,which is not the virtually real value of the pressure center of the aircraft.How to obtain the pressure center of re-entry aerocraft accurately with the general method in wind tunnel test remains a difficult problem.In this paper,the position of re-entry ve-hicle’s pressure center was obtained through the technique of attack angle continuous change and real-time data acquisition.Also the pressure center of re-entry module change rule with the change of attack angle was obtained.Experiments demonstrated the feasibility of the proposed method.With the increasing of negatives attack angle,the contribution of axial force to pitch moment becomes great,while the influence of normal force is just the contrary,which results in thickcreased gap between the conventional measured value and the real value of vehicle’s center of pressure.The vertical position of re-entry aircraft’s load center is relatively small in the test.The final CA-Cm curve shows that the axial force CA should not be neglected or simplified in wind tunnel test.关键词
再入飞行器/压力中心/准确测量/风洞试验Key words
re-entry module/pressure center/exact meassure/wind tunnel test分类
航空航天引用本文复制引用
秦永明,魏忠武,董金刚,陈强,张江..再入飞行器压心测量方法研究[J].空气动力学学报,2014,(3):315-319,5.
