Wing folding and unfolding mechanism of unmanned aerial vehicle

A technology of a wing folding and unfolding mechanism, applied in the field of unmanned aerial vehicles, can solve the problems of unsuitable structure of small unmanned aerial vehicles, unfavorable overall structure storage and carrying, high quality, etc., and achieves strong changeability, easy transportation and launch. , the effect of improving combat capability

Inactive Publication Date: 2014-04-02
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The above three folding and unfolding mechanisms require the wing shafts to be independent of each other. For wings with a large chord length, the overall width of the wing exceeds the fuselage after folding, which is not conducive to the storage and carrying of the overall structure.
And they all use the actuator as the drive. Although the actuator has the characteristics of stability and reliability, but its mass is relatively large, it is not suitable for the structure of small drones.

Method used

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  • Wing folding and unfolding mechanism of unmanned aerial vehicle
  • Wing folding and unfolding mechanism of unmanned aerial vehicle
  • Wing folding and unfolding mechanism of unmanned aerial vehicle

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Embodiment Construction

[0025] Embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0026] Such as Figure 4 , Figure 5 , Figure 6 and Figure 7 As shown, a UAV wing folding and unfolding mechanism includes a fuselage reinforcement frame 9, and the wing shaft 2 passes through the upper beam of the fuselage reinforcement frame 9 and is fixedly connected to the first shaft joint 8. A torsion spring 12 is arranged between the first rotating shaft joint 8 and the fuselage reinforcement frame (9). The other end of the wing shaft 2 is provided with an upper wing 1 fixedly connected with the wing shaft 2 and a lower wing 3 sleeved on the wing shaft 2 and relatively rotatable. The first bevel gear 4 is sleeved on the wing shaft 2 and is fixedly connected with the lower wing 3, and a bushing 11 is installed between the first bevel gear 4 and the wing shaft 2, and the bushing 11 and the first bevel gear 4 For interference fit, it is a cl...

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Abstract

The invention discloses a wing folding and unfolding mechanism of an unmanned aerial vehicle. The mechanism mainly comprises a vehicle body reinforcing frame, a wing rotary shaft, a rotary body driving part, an upper wing, a lower wing and a coaxial contrarotation mechanism. When the unmanned aerial vehicle is launched, a fixed cylinder is opened, and coaxial contrarotation equal-angle movement of the upper and lower wings is realized through the coaxial contrarotation mechanism under the effect of a torsional spring. The mechanism disclosed by the invention is simple in integral structure, compact, high in transmission efficiency by applying gear drive and small in frictional force. The two wings share the rotary shaft, so that the area occupied by the wings is reduced and the unmanned aerial vehicle is convenient to transport and launch, thereby further improving the capacity of systematic combat.

Description

technical field [0001] The invention relates to the technical field of drones, in particular to a wing folding and unfolding mechanism of the drone. Background technique [0002] UAV is a high-efficiency, low-risk high-tech weaponry in modern warfare. The box-type launch system combines the functions of storage, transportation and launch together, which is the best way to achieve the requirements of mobility, operability and maintainability for its usual transportation. For large-aspect-ratio UAVs, a wing folding / deploying scheme is designed to solve the contradiction between the size of the launch box and the length of the wing span. In the design process of the folding wing, not only must the wings be opened as required, And when the wing is opened to the specified position, there must be a corresponding locking device to ensure that the mechanism is fully deployed. [0003] Commonly used actuators include direct connection type, linkage slider type and pinion-rack type....

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/56
Inventor 聂宏张明张钦张丹丹吴晓宇蒋锐
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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