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Vertical takeoff method of fixed-wing unmanned aerial vehicle

A vertical take-off, fixed-wing 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, reducing unnecessary load and prolonging endurance time.

Inactive Publication Date: 2018-03-20
罗伟
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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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  • Vertical takeoff method of fixed-wing unmanned aerial vehicle
  • Vertical takeoff method of fixed-wing unmanned aerial vehicle
  • Vertical takeoff method of fixed-wing unmanned aerial vehicle

Examples

Experimental program
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Effect test

Embodiment 1

[0044] 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

[0049] 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;

[0050] Both the multicopter and the fixed-wing aircraft 50 structures are prior art.

[0051] 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

[0053] 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.

[0054] The carbon fiber casing 90 arranged on the fixed-wing...

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Abstract

The invention provides an unmanned aerial vehicle release mechanism. The mechanism comprises a steering engine, a rudder plate, a transmission rod, a latch rod and a mounting block; the steering engine comprises an output shaft; one end of the rudder plate is fixedly connected to the output shaft; one end of a connecting rod is hinged to the other end of the rudder plate, and one end of the latchrod is hinged to the other end of the connecting rod; the mounting block is fixedly installed on the steering engine, the middle of the mounting block is provided with a clamping groove, a through hole is formed in the transverse direction of the mounting block, the other end of the latch rod penetrates through the through hole and extends into the clamping groove, the inner wall of the side, awayfrom the rudder plate, of the clamping groove abuts against the other end of the latch rod, and the steering engine can drive the latch rod to make reciprocating movement in the through hole. The unmanned aerial vehicle release mechanism is stable during flying and long in battery life.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a vertical take-off method for a fixed-wing unmanned aerial vehicle. Background technique [0002] UAVs refer to unmanned aircraft controlled by wireless remote control equipment and their own control devices, such as unmanned helicopters, fixed-wing UAVs, and unmanned paragliders. 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 multi-rotors, which seriously affects the endurance time and flight at...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D5/00
CPCB64D5/00B64U70/20
Inventor 罗伟
Owner 罗伟
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