8m低速风洞虚拟飞行试验技术研究

Investigation of virtual flight test technique based on 8 m low speed wind tunnel

针对大尺寸缩比飞机模型的气动/运动/控制耦合问题,发展了基于8 m大型低速风洞的虚拟飞行试验技术,开展了4 m尺寸的大展弦比类飞机模型虚拟飞行验证试验,并将试验结果与虚拟飞行环境下的仿真结果进行对比。试验系统功能稳定可靠,设计的试验支撑装置运动范围大、可兼顾单/双/三自由度试验,且满足大载荷受力条件;姿态测量精度优于±0.3°,可实时测量舵面位置且延迟不足0.1 s;俯仰和滚转闭环控制试验响应历程和仿真结果平均偏差不超过5%。研究结果表明,8 m风洞虚拟飞行试验技术能够有效模拟大尺寸缩比模型的机动运动,并具备纵向、航向及横向耦合闭环控制试验模拟能力。

In order to explore the aerodynamics/flight dynamics/flight control coupling problem of large scale scaled aircraft model, the technique of virtual flight test based on 8 m large low speed wind tunnel was developed, and the virtual flight verification test of 4 m high aspect ratio aircraft model was carried out. The test results were comparized with the simulation results under virtval flight environment. The designed test support device has a large range of motion, which can take into account the single/double/three degrees of freedom test and meet the conditions of large load, the attitude measurement accuracy is better than ±0.3°, deflection angle of the control surface can be measured in real time and the delay is less than 0.1 s. The average deviation between the response history of pitch and roll closed-loop control test and the simulation result under virtual flight test environment is less than 5%. Investigation results show that the virtual flight test technology of 8 m wind tunnel can effectively simulate the maneuvering motion of the large scale scaled aircraft model, and has the ability to simulate maneuvers of pitch, yaw and roll coupling in closed-loop control test.