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Unmanned aircraft releasing mechanism, fixed-wing unmanned aircraft and vertical takeoff method thereof

A release mechanism and vertical take-off technology, applied in the field of aircraft, can solve problems such as affecting the endurance time and flight attitude, and achieve the effect of light weight, not easy to shake, and prolong the endurance time.

Inactive Publication Date: 2017-10-27
广东泰一高新技术发展有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, the common fixed-wing UAV wings that can take off and land vertically are composite flying-wing UAVs that combine multi-axis and fixed wings. However, this type of multi-rotor will no longer work after take-off. The UAV is equivalent to flying with redundant multi-rotors, which seriously affects the endurance time and flight attitude

Method used

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  • Unmanned aircraft releasing mechanism, fixed-wing unmanned aircraft and vertical takeoff method thereof
  • Unmanned aircraft releasing mechanism, fixed-wing unmanned aircraft and vertical takeoff method thereof
  • Unmanned aircraft releasing mechanism, fixed-wing unmanned aircraft and vertical takeoff method thereof

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Embodiment 1

[0043] Such as figure 1As shown, this embodiment provides a drone release mechanism, including: steering gear 101: steering gear 101 includes an output shaft; steering wheel 102: one end of the steering wheel 102 is fixedly connected to the output shaft; transmission rod 20: one end of the connecting rod 60 The other end of the rudder plate 102 is hinged with the latch rod 30: one end of the latch rod 30 is hinged with the other end of the connecting rod; the mounting block 40: the mounting block 40 is fixedly installed on the steering gear 101, and the middle part of the mounting block 40 is provided with a card slot 401, and the mounting block 40 A through hole 402 is provided in the horizontal direction, and the other end of the latch rod 30 extends through the through hole 402 into the slot 401. The inner wall of the slot 401 away from the steering wheel 102 is against the other end of the latch rod 30, and the steering gear 101 can drive the latch rod. 30 reciprocates in ...

Embodiment 2

[0048] Such as figure 2 As shown, the present embodiment provides a fixed-wing unmanned aerial vehicle, including the unmanned aerial vehicle release mechanism of embodiment 1; The other end of the connecting rod 60 is provided with a hanging ring 70;

[0049] Both the multicopter and the fixed-wing aircraft 50 structures are prior art.

[0050] The multi-axis aircraft and the fixed-wing aircraft 50 are connected through the unmanned aerial vehicle release mechanism. The fixed-wing aircraft 50 is hung on the latch rod 30 in the card slot 401 through the hanging ring 70 provided on the connecting rod 60 , and controlled by the steering gear 101. The rotation of the multi-axis aircraft and the fixed-wing aircraft 50 can be flexibly and quickly realized the switching between the fixation and release of the multi-axis aircraft and the fixed-wing aircraft 50, and the separation of the multi-axis aircraft and the fixed-wing aircraft 50 can be realized during flight, thereby avoidi...

Embodiment 3

[0052] Such as image 3 As shown, the present embodiment provides a fixed-wing unmanned aerial vehicle, including the unmanned aerial vehicle release mechanism of embodiment 1; The other end of the connecting rod 60 is connected with the aircraft 50, and the other end of the connecting rod 60 is provided with a hanging ring 70; the steering wheel 102 is fixedly connected with the multi-axis aircraft, and the hanging ring 70 is located in the slot 401 and is sleeved on the latch rod 30; it also includes a fixing ring 80 and a carbon fiber sleeve 90, the fixed ring 80 is fixedly installed on one end of the connecting rod 60, the carbon fiber sleeve 90 is arranged symmetrically on the fixed wing 50, the axis of the carbon fiber sleeve 90 is perpendicular to the axis of symmetry of the fixed wing 50, the inner wall of the fixed ring 80 is aligned with the carbon fiber sleeve The outer wall of the tube 90 is connected.

[0053] The carbon fiber casing 90 arranged on the fixed-wing...

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Abstract

The invention provides an unmanned aircraft releasing mechanism. The unmanned aircraft releasing mechanism comprises a steering engine, a tiller, a transmission rod and a mounting block, wherein the steering engine comprises an output shaft; one end of the tiller is fixedly connected to the output shaft; one end of a connecting rod and the other end of the tiller are in hinged connected with a latch rod, and one end of the latch rod is hinged to the other end of the connecting rod; the mounting block is fixedly mounted on the steering engine; a clamping slot is formed in the middle of the mounting block; a through hole is formed in the mounting block in the horizontal direction; the other end of the latch rod penetrates through the through hole and extends into the clamping slot; the inner wall of one side, away from the tiller, of the clamping slot is abutted against the other end of the latch rod; and driven by the steering engine, the latch rod can do reciprocating motion in the through hole. The unmanned aircraft releasing mechanism provided by the invention is stable to fly and long in cruising duration.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a release mechanism for a drone, a fixed-wing drone and a vertical take-off method thereof. Background technique [0002] Unmanned aerial vehicles refer to unmanned aerial vehicles controlled by wireless remote control equipment and their own control devices, such as unmanned helicopters, fixed-wing unmanned aerial vehicles, unmanned paragliders, etc. In the past ten years, drones have been widely used in aerial photography, power inspection, environmental monitoring, forest fire prevention, disaster inspection, anti-terrorism lifesaving, military reconnaissance, battlefield assessment and other fields. [0003] At present, the common fixed-wing UAV wings that can take off and land vertically are composite flying-wing UAVs that combine multi-axis and fixed wings. However, this type of multi-rotor will no longer work after take-off. The UAV is equivalent to flying with redundant...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D5/00
CPCB64D5/00B64U10/25B64U70/20
Inventor 曾俊黄山柯宗泽吴宽陈育昌邹星家陈业宏
Owner 广东泰一高新技术发展有限公司
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