Abstract
Aiming at the experimental test of the body freedom flutter for modern high aspect ratio flexible flying wing, this paper conducts a body freedom flutter wind tunnel test on a full-span flying wing flutter model. The research content is summarized as follows: (1) The full-span finite element model and aeroelastic model of an unmanned aerial vehicle for body freedom flutter wind tunnel test are established, and the structural dynamics and flutter characteristics of this vehicle are obtained through theoretical analysis. (2) Based on the preliminary theoretical analysis results, the design and manufacturing of this vehicle are completed, and the structural dynamic characteristics of the vehicle are identified through ground vibration test. Finally, the theoretical analysis model is updated and the corresponding flutter characteristics are obtained. (3) A novel quasi-free flying suspension system capable of releasing pitch, plunge and yaw degrees of freedom is designed and implemented in the wind tunnel flutter test. The influence of the nose mass balance on the flutter results is explored. The study shows that: (1) The test vehicle can exhibit body freedom flutter at low airspeeds, and the obtained flutter speed and damping characteristics are favorable for conducting the body freedom flutter wind tunnel test. (2) The designed suspension system can effectively release the degrees of freedom of pitch, plunge, and yaw. The flutter speed measured in the wind tunnel test is 9.72 m/s, and the flutter frequency is 2.18 Hz, which agree well with the theoretical results (with flutter speed of 9.49 m/s and flutter frequency of 2.03 Hz). (3) With the increasing of the mass balance at the nose, critical speed of body freedom flutter rises up and the flutter frequency gradually decreases, which also agree well with corresponding theoretical results.
Highlights
The high aspect ratio flexible flying wing (HARFFW) is a quite favorable configuration in unmanned aerial vehicle (UAV) development because of its excellent aerodynamic performance.Usually, the rigid body pitch mode frequency of the flying wing will increase due to the tailless design, and the elastic modal frequency decreases due to the aspect ratio and flexibility of the wing increases
The structural dynamic characteristics of the body freedom flutter (BFF) wind tunnel test UAV were attained by performing a ground vibration test on the UAV by hammer impact method
The results show that as the mass balance at nose increases, the flutter speed gradually increases, and the flutter frequency gradually decreases
Summary
The high aspect ratio flexible flying wing (HARFFW) is a quite favorable configuration in unmanned aerial vehicle (UAV) development because of its excellent aerodynamic performance. Comprehensive experimental validation studies of BFF usually include the design and processing of the flexible flying wing aircraft and the formulation of the test scheme [9,10], updating of theoretical analysis model by ground vibration test [11], and verification of theoretical analysis by wind tunnel test [12]. A BFF flying wing UAV model is designed and a novel quasi-free-flying support system is introduced into the full-span BFF wind tunnel test. The overall work is summarized and pertinent conclusions are drawn
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