Flexible telescopic extension mechanism of folding wing

Abstract

The invention discloses a flexible telescopic extension mechanism of a folding wing, and relates to the technical field of unmanned aerial vehicles. Comprising a control panel, an electric telescopic motor, an air pump, internal and external pressure sensors, wing ribs and a flexible skin. The electric telescopic motor and the air pump are arranged at one end close to the fuselage folding aluminum alloy side by side; the electric telescopic motor is connected with the inner side wing main beam and is used for driving the telescopic extension mechanism to extend and contract; the air pump is connected with the inner side wing auxiliary beam and used for maintaining the air pressure in the outer side wing; the wing can stretch out and draw back by driving the telescopic motor through the control panel, and the wing rib and flexible skin bonding mode is designed, so that the wing rib translates in the wingspan direction; the wing ribs are arranged at equal intervals, the original width of each section of flexible skin is the same, and overall coordination of the telescopic mechanism is guaranteed. The internal and external pressure sensor is responsible for monitoring internal and external air pressure, and then the air pump is used for adjusting the internal pressure of the telescopic wing. The device has the advantages of being simple in structure, light in weight and small in occupied space.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a flexible and retractable expansion mechanism for folding wings. Background technique [0002] Most of the traditional aircraft use a single aerodynamic layout to meet the aerodynamic requirements under a single design state. Folding drones need to meet more flight conditions, such as taking into account both high-speed cruise and low-speed empty cruise. At this time, the wing with a single aerodynamic layout can no longer meet the design requirements of the folding drone. This requires a wing design that can change its aerodynamic shape according to different flight conditions. For low-speed cruise flight conditions, increasing the wing span can increase the lift-to-drag ratio of the UAV, reduce the cruise speed, and achieve long-term airborne cruise. [0003] Folding drones are subject to their own miniaturization requirements, and the wingspan design size ...

AI Technical Summary

Problems solved by technology

Invention patent CN202110216786.0 discloses a folding drone, which uses the gear shaft to control the sweep angle of the wing to realize the cruise speed control of the drone, but the complicated mechanism of the shaft mechanism, the gear and the motor unit take up a lot of space and The weight of the aircraft cannot be reduced; the invention patent CN202110602628.9 discloses a retractable wing mechanism suitable for small unmanned aerial vehicles. The side wings are fixed relative to the fuselage of the UAV, and the length of the wings is adjusted by sliding the outer wings relative to the inner wings. The movement of the guide rails completes the movement process of the outer wing relative to the inner wing. In the scheme, the U-shaped beams of the outer wing and the inner wing are likely to cause the outer wing to turn up during the expansion and contraction process, so that the friction force increases and causes the expansion and contraction. It is difficult to shrink; the utility model CN201721827558.2 discloses a retractable wing for a folding-wing UAV. The telescopic rod is connected to the screw nut, the screw nut is threaded to the screw, the right end of the screw is fixedly connected to the axis of the turbine, the turbine is meshed with the worm, the worm is connected to the output shaft of the motor, and the switch of the motor is connected to the micro switch to realize the machine. Wing telescopic, the structure of the scheme is complicated, there are many parts and the high coordination requirements between parts are not practical; the invention patent

[0005] CN202010495384.4 provides a skeleton structure of a retractable wing, which is composed of a steering gear drive, a wing rib, a slide rail beam and a movement module unit, and each movement module unit includes eight transmission links and connecting rods A hinged connection structure is formed. This scheme is innovative but the driving mechanism is huge and complicated, and the practicability is not strong.

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