High-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings

A folding wing and long-endurance technology, applied in the aviation field, can solve the problems of unmanned aerial vehicles with too large wingspan, large space occupation, and difficulty in rapid deployment, so as to improve space utilization, reduce occupied volume, and light weight Effect

Active Publication Date: 2022-03-22
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In order to solve the problems of the existing high-altitude and long-endurance drones, which lead to excessively large wingspan during transportation and storage, high maintenance costs, and difficulty in rapid deployment, the present invention proposes a high-altitude drone with foldable and telescopic wings. Long-endurance drones can change the length of the wings of the drone during storage a...

Method used

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  • High-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings
  • High-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings
  • High-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings

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specific Embodiment approach 1

[0041] Specific implementation mode one: combine Figure 1 to Figure 16 Describe this embodiment, a high-altitude long-endurance UAV with foldable and telescopic wings described in this embodiment includes a fuselage 1, two front folding wings 2-a, two rear folding wings 2-b, two A front telescopic wing 3-a, two rear telescopic wings 3-b, two folding empennages 4, two folding propeller blades 5, a plurality of folding mechanisms and a plurality of telescopic mechanisms, the two sides of the fuselage 1 front respectively A front folding wing 2-a is symmetrically arranged, and a front telescopic wing 3-a is inserted into the outer end of the front folding wing 2-a, and a rear folding wing 2-b is respectively symmetrically arranged on both sides of the top of the rear part of the fuselage 1 , the outer end of the rear folding wing 2-b is inserted with a rear telescopic wing 3-b, a folding empennage 4 is symmetrically arranged on both sides of the rear of the fuselage 1, and two f...

specific Embodiment approach 2

[0045] Specific implementation mode two: combination Figure 1 to Figure 16 Describe this embodiment, the folding mechanism described in this embodiment includes a spring hook 7, a tension spring 8, a steel wire 9, a pulley 10, a round hole shaft seat 11-a, a semicircle hole shaft seat 11-b and a rotating shaft 16, and the spring hook 7 , pulley 10, round hole shaft seat 11-a, and semicircular hole shaft seat 11-b are all fixedly connected on the fuselage 1, and the inner side end of rotating shaft 16 is inserted on the round hole shaft seat 11-a, and the outer side end of rotating shaft 16 Inserted on the semicircular hole shaft seat 11-b, and the rotating shaft 16 is rotationally connected with the round hole shaft seat 11-a and the semicircular hole shaft seat 11-b, and one end of the steel wire 9 is fixed on the side wall of the rotating shaft 16, and the steel wire 9 The other end of the other end is connected with an end of the tension spring 8 after bypassing the pulley...

specific Embodiment approach 3

[0049] Specific implementation mode three: combination Figure 1 to Figure 16 Describe this embodiment, the folding mechanism in this embodiment also includes a shaft cover 12, the shaft cover 12 is fixed on the semi-circular hole shaft seat 11-b to form a complete round hole shaft seat, and is rotatably connected with the outer end of the rotating shaft 16 . Other compositions and connection methods are the same as those in the second embodiment.

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Abstract

The invention discloses a high-altitude long-endurance unmanned aerial vehicle with foldable telescopic wings, and relates to the technical field of aviation. The problems that an existing high-altitude long-endurance unmanned aerial vehicle occupies too large space during transportation and storage due to the fact that the wingspan is too large, the maintenance cost is high, and rapid deployment is difficult are solved. The unmanned aerial vehicle comprises a vehicle body, two front folding wings, two rear folding wings, two front telescopic wings, two rear telescopic wings, two folding empennages, two folding propeller blades, a plurality of folding mechanisms and a plurality of telescopic mechanisms, the front folding wings are symmetrically arranged on the two sides of the front end of the abdomen of the vehicle body respectively, and the front telescopic wings are inserted into the outer side ends of the front folding wings; the rear folding wings are symmetrically arranged on the two sides of the rear end of the top of the fuselage respectively, the rear telescopic wings are inserted into the outer side ends of the rear folding wings, the folding empennages are symmetrically arranged on the two sides of the rear portion of the fuselage respectively, and the two folding propeller blades are symmetrically arranged at the tail of the fuselage. The invention is used for the high-altitude long-endurance unmanned aerial vehicle.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a high-altitude long-endurance unmanned aerial vehicle with foldable and telescopic wings. Background technique [0002] Due to its good aerodynamic performance and good fuel economy, high-altitude and long-endurance UAVs are suitable for long-term reconnaissance and surveillance tasks at high altitudes, and can be used as unmanned combat platforms. HMI has the characteristics of rapid deployment, easy maintenance, and low operating cost. However, the wingspan and large wing area of ​​general high-altitude and long-endurance drones will cause the drones to take up too much space during transportation and storage, which not only increases the difficulty of ground maintenance and transportation, but also increases operating costs. It is also difficult to deploy quickly. [0003] In order to solve this problem, consider adopting the method of folding and deforming the wings, so ...

Claims

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Application Information

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IPC IPC(8): B64C1/30B64C3/56B64C11/28B64F1/04
CPCB64C1/30B64C3/56B64C11/28B64F1/04Y02T50/40
Inventor 高良赵杰朱延河刘刚峰蒋金豹
Owner HARBIN INST OF TECH
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