The invention discloses a control-surface-free aircraft wing with variable camber, and belongs to the technical field of aircrafts. According to the method, aiming at the functional requirements of aircraft wings for bearing aerodynamic loads and camber changes, a force transmission route and a motion transmission route are comprehensively considered, and topological optimization analysis is carried out on the wing leading edge and the wing trailing edge; the weight of the wing front edge and the wing rear edge is reduced under the constraint condition that structural materials of the wing front edge and the wing rear edge both bear aerodynamic loads and generate large-range continuous and smooth flexible bending deformation; aiming at the characteristic that the front edge of the wing bears large aerodynamic load, the front edge of the wing generates large-range continuous and smooth flexible bending deformation by optimizing the number and the distribution mode of control points of the front edge of the wing; aiming at the characteristic that the aerodynamic load of the trailing edge part is small, the trailing edge of the wing adopts a corrugated structure driven by a piezoelectric plate, so that the trailing edge of the wing generates large-range continuous and smooth flexible bending deformation, and the wing has the advantages of high energy density, light weight, quietness and high efficiency.
本发明公开的一种可变弯度的无舵面飞行器机翼,属于飞行器技术领域。本发明针对飞行器机翼承受气动载荷和弯度变化的功能需求,综合考虑传力路线和运动传递路线,通过对机翼前缘、机翼后缘进行拓扑优化分析,在实现机翼前缘和机翼后缘结构材料兼顾承受气动载荷和产生大范围连续而平滑的柔性弯度变形的约束条件下,减轻机翼前缘和机翼后缘的重量;针对机翼前缘承受气动载荷大的特点,通过优化机翼前缘控制点的数量和分布方式,使机翼的前缘产生大范围连续而平滑的柔性弯度变形;针对后缘部分气动载荷小的特点,机翼后缘采用压电片驱动的波纹结构,使机翼的后缘产生大范围连续而平滑的柔性弯度变形,且具有能量密度高、重量轻、安静、高效的优点。
Control-surface-free aircraft wing with variable camber
一种可变弯度的无舵面飞行器机翼
2021-09-21
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
NTIS | 1973
NTIS | 1973
NTIS | 1973