FD09风洞旋转天平试验系统研制  

Development of Rotary Balance System in FD09Wind Tunnel

作　　者：黄浩[1] 张永升[1] 刘丹[1] 

机构地区：[1]中国航天空气动力技术研究院第二研究所,北京100074

出　　处：《航空工程进展》2014年第4期429-434,共6页Advances in Aeronautical Science and Engineering

摘　　要：为了分析和预测飞机的尾旋特性,一般通过旋转天平风洞试验测定飞机模型在不同姿态角时绕风轴以不同旋转速率作等速旋转状态下的气动特性。针对上述情况,研制FD09低速风洞旋转天平试验系统,介绍该旋转天平试验系统的设计特点、性能指标,并进行SDM标模和战斗机模型对比验证。结果表明:本试验系统工作稳定可靠,试验结果与参考曲线有较好的重复性,并且本试验系统试验曲线的光滑性要更好一些,同时本试验系统给出的试验数据精度较高,可以用于开展型号试验及相关空气动力学研究。For the purpose of analyzing and predicting spin characteristics of aircraft,the rotary balance testing in wind tunnel is mainly used to measure aerodynamic forces acting on aircraft model rotating around the longitudinal axis of wind axes system.For this case,the rotary balance system is developed in FD09 low speed wind tunnel.The design feature and performance index of rotary balance system are introduced.Verification and comparison by using SDM（Standard Dynamic Model）and fighter plane model are performed.The results indicate that the rotary balance system of FD09 wind tunnel is stable and reliable,the repetition of test curves of FD09 wind tunnel are agree well with the reference curves,while the test curves of FD09 wind tunnel are more smoothly than reference curves,and the aerodynamic coefficients yielded by the rotary balance system of FD09 wind tunnel have high accuracy.The rotary balance system of FD09 wind tunnel can be put into the project tests and aerodynamic research.

关 键 词：旋转天平 尾旋特性 低速风洞 验证试验 试验精度 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]