Unmanned aerial vehicle

A technology of unmanned aerial vehicle and fuselage, which is applied in the direction of wings, unmanned aerial vehicles, motor vehicles, etc., and can solve the problems of not being able to adapt to limited area launch applications, small flight speeds, etc.

Inactive Publication Date: 2017-03-22
深圳市易飞方达科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Since fixed-wing UAVs have a minimum flight speed (i.e., stall speed), higher requirements are placed on the launcher’s hand throwing speed when using hand-throwing launch. The shooting speed and shooting posture are specially trained, and a certain open area is required, which cannot adapt to limited area launch applications

Method used

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Embodiment Construction

[0022] In order to make the objectives, technical solutions, and advantages of the present invention clearer, the drone according to the embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0023] See figure 1 The unmanned aerial vehicle of the embodiment of the present invention includes a fuselage 10, an electric propulsion mechanism 20, a wing 30, a vertical tail 40, a flat tail 50, and a buffer package 60. The electric propulsion 20 is arranged on the head of the fuselage 10, the wings 30 are arranged on both sides of the fuselage 10, the vertical tail 40 and the flat tail 50 are arranged on the tail of the fuselage 10, and the buffer pack 60 is arranged on the bottom of the fuselage 10. It can be understood that the UAV 100 also includes other functional components, such as a rudder, a hatch cover, etc. To save space, these other functional modules are not described in detail below.

[0024] The fuselage 10 is fo...

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Abstract

A fixed-wing unmanned aerial vehicle comprises a fuselage, an electric propulsion mechanism arranged at the head of the fuselage, wings arranged on the two sides of the fuselage and a horizontal tail arranged at the tail of the fuselage. Before the unmanned aerial vehicle takes off, the electric propulsion mechanism can provide larger than or equal to 5.4 kg tension for the unmanned aerial vehicle. The wings are airfoils high in lift coefficient. The horizontal tail is a stabilator. During launching of the unmanned aerial vehicle, zero-run-up hand throwing launching can be completed without providing the additional initial velocity, and the fixed-wing unmanned aerial vehicle can adapt to various area-limited environments, such as island reefs, mountain, roofs, ships and other usage environments.

Description

Technical field [0001] The invention relates to an unmanned aerial vehicle, in particular to a hand-thrown fixed-wing unmanned aerial vehicle. Background technique [0002] With the miniaturization and high integration of electronic payloads, small electric unmanned aerial vehicles, especially hand-launched electric unmanned aerial vehicles, are developing rapidly and are used in military and civilian applications. Traditional hand-thrown electric drones have the following problems to be solved urgently: [0003] Since fixed-wing UAVs have a minimum flight speed (that is, stall speed), when using hand-throwing launching, higher requirements are placed on the launcher’s hand throwing speed, and the launcher’s approach speed, Special training is required for shooting speed and shooting posture, and requires a certain open area, which cannot be adapted to limited area launch applications. Summary of the invention [0004] In view of this, the embodiments of the present invention prov...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C39/02B64C3/00B64C5/06B64C11/28B64C5/02
CPCB64C3/00B64C5/02B64C5/06B64C11/28B64C39/02B64U10/00B64U10/25B64U50/19
Inventor 张会军
Owner 深圳市易飞方达科技有限公司
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