低速增压风洞三点支撑系统的设计和验证

Design and Verification of Three Point Support System for Low Speed Supercharged Wind Tunnel

为提高大展弦比飞机模型和大载荷飞翼类模型风洞试验准度,提高支撑机构纵横向刚度和系统稳定性,有效降低试验模型失速后的抖动和机翼弹性形变,航空工业气动院在FL-9低速增压风洞开展了三点支撑试验系统的研究。以拟进行增压试验的某螺旋桨滑流模型为研究对象,对模型迎角运动机构、风挡逆向运动机构等进行了具体的设计分析及结构优化,按照试验模型姿态角对系统进行了验证。结果表明,该系统角度定位精度高,易于扣除支架干扰,风挡顺气流姿态保持良好,并且具备较高的纵横向刚度,对提高试验精准度有较大帮助。

In order to improve the wind tunnel test accuracy of high aspect ratio aircraft model and high load flying wing model,improve the longitudinal and transverse stiffness and system stability of support mechanism,and effectively reduce the flutter and elastic deformation of wing after stall of test model,AVIC Aerodynamics Research Institute has carried out the research of three point support test system in FL-9 low speed pressurized wind tunnel.Taking a propeller slipstream model for pressurization test as the research object,the angle of attack motion mechanism and windshield reverse motion mechanism of the model are analyzed and optimized.The system is verified according to the attitude angle of the test model.The results show that the system has high angular positioning accuracy,is easy to deduct the support interference,and the windshield downstream attitude maintains well,and it has high longitudinal and transverse stiffness,which is helpful to improve the test accuracy.