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Connection-wing-configuration novel vertical-take-off-and-landing unmanned aerial vehicle

A technology for vertical take-off and landing of drones, applied in the field of drones, which can solve problems such as large load capacity, low load capacity, and short battery life

Active Publication Date: 2019-07-09
夏季风
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005]Aiming at the deficiencies in the prior art, the present invention proposes a new type of vertical take-off and landing unmanned aerial vehicle with a joint wing configuration to solve the problems of fixed wings, multi-rotors, helicopters, etc. UAVs cannot take into account the rigid requirements of easy take-off and landing, large load capacity, simple control, and high reliability at the same time, and overcome the inherent defects of low load capacity and short battery life of conventional vertical take-off and landing drones in the market. To achieve the application purpose of meeting different environments, meeting different conditions, and adapting to different tasks with one platform

Method used

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  • Connection-wing-configuration novel vertical-take-off-and-landing unmanned aerial vehicle

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Embodiment 2

[0058] In the figure, the same reference numerals as those used in the above-mentioned embodiments still follow the definition of the reference numerals in the above-mentioned embodiments.

[0059] The newly appearing reference signs are defined as follows: 25, umbrella cabin; 251, second pin hole; 252, supporting plate; 253, spring; 26, hatch door; 261, first pin hole; 27, steering gear; 271, rocking Arm; 272, latch; 28, parachute; 281, parachute; 29, hanging point.

[0060] see Figure 6 to Figure 7 The difference between this embodiment and Embodiment 1 is that: the upper end of the fuselage 2 is provided with an umbrella cabin 25, the upper end of the umbrella cabin 25 has an opening, and the opening 511 of the umbrella cabin 25 is hinged with one end of the hatch door 26 , the other end of the hatch 26 is provided with a first pin hole 261, the inside of the fuselage 2 is provided with a second pin hole 251 corresponding to the first pin hole 261, and the inside of the f...

Embodiment 3

[0069] In the figure, the same reference numerals as those used in the above-mentioned embodiments still follow the definition of the reference numerals in the above-mentioned embodiments.

[0070] Newly occurring reference signs are defined as follows: 7. Swept wing.

[0071] see Figure 8 and Figure 9 , The difference between this embodiment and Embodiment 2 is that: the wingtips of the two front wings 3 are symmetrically connected with a swept wing 7 .

[0072] The set swept wing 7 can increase the lift and stability of the fuselage 2. In addition, it can also increase the load capacity and increase the flight speed, making the application scenarios of the swept wing 7 more abundant. Here, the front wing 3 can Corresponding pins and pin holes are set at the wing tip of the wing tip and the wing root of the swept wing 7, by inserting the pin into the pin hole, then inserting it into the pin hole through the top wire, and tightening the pin, so that the front wing 3 Faste...

Embodiment 4

[0074] In the figure, the same reference numerals as those used in the above-mentioned embodiments still follow the definition of the reference numerals in the above-mentioned embodiments.

[0075] Newly occurring reference signs are defined as follows: 8, straight wing.

[0076] see Figure 10 , this embodiment and image 3 The difference is that the swept wing 7 is replaced by a straight wing 8 in this embodiment.

[0077]The set straight wing 8 can increase the lift of the fuselage 2 to increase the load, making the application scenarios of the straight wing 8 more abundant. Here, corresponding pins can be set on the wing tip of the front wing 3 and the wing root of the straight wing 8 and the pin hole, by inserting the bolt into the pin hole, then inserting it into the pin hole through the top wire, and tightening the bolt, so that the front wing 3 and the straight wing 8 are fastened and spliced. This method of quick loading and unloading of Wing 8 effectively improves...

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Abstract

The invention provides a connection-wing-configuration novel vertical-take-off-and-landing unmanned aerial vehicle. The connection-wing-configuration novel vertical-take-off-and-landing unmanned aerial vehicle comprises a vehicle head, a vehicle body, front wings, back wings and a propeller power mechanism; the vehicle head is connected to the front end of the vehicle body; the two front wings arehorizontally and symmetrically connected to the front end of the vehicle body; the two back wings are horizontally and symmetrically connected to the back end of the vehicle body, the wingtip parts of the back wings and the wingtip parts of the front wings which are located on the same sides of the vehicle body are mutually connected, the two back wings and the two front wings are combined to form a rhombus shape, and the propeller power mechanism is perpendicularly arranged at the lower end of the single back wing and the lower end of the single front wing. According to the connection-wing-configuration novel vertical-take-off-and-landing unmanned aerial vehicle, the problems that unmanned aerial vehicles such as fixed wings, multi-rotation wings and a helicopter cannot meet the rigid requirements that take-off and landing are easy, the carrying capacity is large, control is easy, and the reliability is high are solved, the inherent defects that an existing conventional-layout vertical-take-off-and-landing unmanned aerial vehicle is low in carrying capacity and short in endurance time are overcome, and the application aims that a platform meets different environments, meets different conditions and adapts to different tasks are achieved.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a novel vertical take-off and landing unmanned aerial vehicle with a joint wing configuration. Background technique [0002] UAVs are called "air robots". From the birth of the first UAV in 1917 to the present for nearly 100 years, UAV technology has continued to improve, especially microelectronics, navigation, control, communication and other technologies. It has promoted the development of unmanned aerial vehicle systems and promoted the application of unmanned aerial vehicle systems in military and civilian fields. In recent years, the regulation of civilian drones has been gradually relaxed, as well as the regulation of domestic civilian drone policies and the deepening of low-altitude airspace reforms, prompting my country's civilian drone industry to show explosive growth. [0003] As the largest country in the world for civilian drones, my country has a ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/26B64C3/10B64D27/26B64D17/80B64D17/70
CPCB64C27/26B64C3/10B64D17/80B64D17/70B64U50/19B64D27/40
Inventor 夏季风
Owner 夏季风
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