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Three-stage fixed-wing unmanned aerial vehicle

A technology of unmanned aerial vehicles and fixed wings, applied in the field of unmanned aerial vehicles, can solve the problems of not meeting the requirements of use and insufficient maximum lift coefficient, and achieve the effect of good low-speed flight performance, high load capacity, and low stall speed

Pending Publication Date: 2017-07-28
西安神骑航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Especially the existing unmanned aerial vehicles, the maximum lift coefficient is not enough, can not meet the requirements of use well

Method used

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  • Three-stage fixed-wing unmanned aerial vehicle
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  • Three-stage fixed-wing unmanned aerial vehicle

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Embodiment Construction

[0044] The technical solutions in the embodiments of the present invention will be clearly and completely described below. Obviously, the described embodiments are only some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0045] The core of the present invention is to provide a three-stage fixed-wing unmanned aerial vehicle, which has a higher maximum lift coefficient, so that the aircraft has a higher maximum lift.

[0046] A three-section fixed-wing unmanned aerial vehicle, the wing of the unmanned aerial vehicle is a three-section airfoil structure, including a slat 107 arranged on the leading edge of the wing, a main wing arranged in the middle of the wing, and a main wing arranged on the trailing edge of the wing. The main wing includes a centra...

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Abstract

The invention relates to a three-stage fixed-wing unmanned aerial vehicle. A wing of the unmanned aerial vehicle is of a three-stage wing shaped structure, the wing comprises a slat arranged at the front edge of the wing, a main wing arranged in the middle of the wing and a flap arranged at the rear edge of the wing, the main wing comprises a central wing and outer wings arranged on both sides of the central wing, the flap comprises a flap body arranged at the rear edge of the central wing and auxiliary flaps arranged at the rear edges of the outer wings. An advantage of the three-stage fixed-wing unmanned aerial vehicle is that use of the three-stage wing airfoil is an innovate point. Compared with an existing single-stage or two-stage airfoil used in the unmanned aerial vehicle, the three-stage airfoil has a higher maximum lift coefficient, so that the unmanned aerial vehicle has a higher maximum lift. The increase in maximum lift allows the unmanned aerial vehicle to have a higher load and a lower stalling speed, take off and land on shorter runways, and have better low-speed flight performance.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a three-stage fixed-wing unmanned aerial vehicle. Background technique [0002] In recent years, with the development of unmanned aerial vehicle technology and the reduction of cost, fixed-wing unmanned aerial vehicles have been widely used in various fields such as military, security, transportation, exploration, surveying and mapping, and meteorology. In the military field, fixed-wing UAVs are generally used for high-altitude and high-speed reconnaissance and strikes. In the civilian field, fixed-wing UAVs are generally used for aerial photography, surveying and mapping, and inspections. [0003] Various applications of drones have different technical requirements. For example, UAVs used for long-range reconnaissance have high requirements on the cruise of the aircraft, while UAVs that take off and land in the wild require that the aircraft must adapt to the rough take...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/28B64C3/10B64C5/06B64C5/02
CPCB64C3/10B64C3/28B64C5/02B64C5/06B64U10/25B64U2101/00
Inventor 马晓辉赵鹏涛刘磊沙少滨何忠伟欧明章
Owner 西安神骑航空科技有限公司
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