2m量级高速风洞强迫振动动导数试验技术研究

为满足大型运输机、先进战斗机、推进与机体一体化布局等现代高性能飞行器动导数风洞试验研究的需求,基于小振幅强迫振动动导数试验原理,在中国空气动力研究与发展中心2 m 量级高速风洞(FL-26和 FL-28)建立了一套俯仰、滚转及偏航的三通道动导数试验技术。在试验系统研制过程中,首先采用强度高、刚性好的航空轻质铝材和复合材料解决了亚跨超声速条件下大尺度试验模型研制问题；其次,结合动力学和运动学仿真分析手段,实现并优化了大载荷试验装置传动机构设计以及α、β耦合双转轴支撑结构设计的难题；最后,在测控系统研制部分,通过电机选取、电磁干扰屏蔽、滤波器设计等技术手段进一步提高了测试系统的精度。试验系统设计技术指标Ma=0.4~4.25,迎角α=-35°~35°,侧滑角β=-15°~15°,传动机构法向承载载荷≤10000 N。SDM 标模的验证试验结果表明,直接阻尼导数与文献值一致性较好,重复性试验数据误差基本控制在10%以内。目前,该项试验技术已经成功应用于某大型飞机模型的动导数风洞试验。

Forced-oscillation dynamic derivative test techniques in 2 meter scale high speed wind tunnels

In order to research dynamic derivatives of large transport aircraft,advanced fighter aircraft, propulsion and airframe integration aircraft in high speed wind tunnels, a dynamic derivative test technique based on the small amplitude forced-oscillation test principle has been developed in the 2 meter scale high speed wind tunnels (FL-26 and FL-28 )of China Aerodynamics Research & Development Center .In this paper,the composition of the system is introduced,and some key techniques in the development of the system are emphasized.Firstly, high strength,good rigidity of aviation lightweight aluminum or composite materials are used to solve the large scale test model development issues in subsonic, transonic and supersonic conditions;secondly,combination of dynamics and kinematics simulation analysis means are adopted,to realize and optimize high load test device for transmission mechanism design,and to solve the difficult design problem ofα、β coupling double rotating shaft supporting structure;at last,the development ideas of the test and control system part are presented,the accuracy of the test system is improved furthermore through some technical means, including the motor selection, electromagnetic interference shielding, filter design techniques and so on. The technical indicators of the test system are also presented,M number ranges from0.4 to 4.25, angle of attack from-35°to 35°and sideslip angle-15°to 15°,the bearing load of the transmission mechanism is up to no more than 10000N.The test results of the SDM standard model show that the direct damping derivative is in good agreement with the reference data,and the repeatability error of the test data is within 10%.The application of this system for an aircraft model is pres-ented,reasonable and reliable test data are obtained successfully.