折叠变体飞行器风洞试验模型研发

Research and development on the wind tunnel test model of morphing aircraft with folding wing

变体飞行器一直是航空领域研究的热点问题。针对某变体飞行器风洞试验任务提出的运动性能指标,设计开发了可控的折叠变体试验模型,对其设计方案及工作原理进行了阐述,对折叠变体机构进行了运动学与动力学分析,建立了位移、速度和加速度控制的数学模型,得出了机构的最大受力状态及各连接杆件的最大受力值,并进行了角度误差的分析与计算。结果表明,该试验模型能够对机翼折叠变体角度进行连续、稳定和精确控制,完全达到了设计要求的各项指标。

Morphing aircraft is the hot issue of research in the aviation field. In this paper, by referring to the movement perform- ance index proposed by the wind tunnel test task of certain morphing aircraft, the controllable-folding morphing test model has de- signed and developed. Its design plan and operating principle will be explained, the kinematics and dynamics analysis of the folding structure has been carried out, and the mathematical model controlling the displacement, velocity, acceleration was established. The maximum strained condition and the maximum stress value of various connection pieces were obtained, and the analysis and calculation of the angular error has been carried out. The test results have shown that this test model can realize continuous, stable and accurate control to the folding angle of the wings, and meeting various indices of the design requirement completely.