Multi-rotor-wing unmanned aerial vehicle with power wing body

A multi-rotor unmanned aerial vehicle and power wing technology, applied in the field of unmanned aerial vehicles, can solve the problems of increasing the weight of the unmanned aerial vehicle, increasing the power consumption, and the power consumption of the lift, so as to reduce the weight, reduce the power consumption, Parking smooth effect

Pending Publication Date: 2018-07-06
北京白米科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The above design, in the case of a certain amount of energy carried by the UAV itself, only provides lift through the rotor power group and consumes a lot of power, which affects the range; and directly installing wings on the side of the fuselage increases the UAV itself. The self-weight will relatively increase the power consumption during the flight, which will affect the flight range under the condition of a certain amount of energy.

Method used

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  • Multi-rotor-wing unmanned aerial vehicle with power wing body
  • Multi-rotor-wing unmanned aerial vehicle with power wing body
  • Multi-rotor-wing unmanned aerial vehicle with power wing body

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0035] Such as figure 1 As shown, a powered wing body multi-rotor UAV includes a fuselage 1, a rotor power group 2, an empennage 4 and a fixed rotor power group 32, the rotor power group 2 is installed on both sides of the fuselage 1, and the empennage 4 is fixed on At the tail end of the fuselage 1, the fixed rotor is installed at the tail end of the fuselage 1 and behind the empennage 4. The rotor power group 2 can provide upward lift to facilitate vertical take-off and landing, while the fixed rotor power group 32 provides the forward thrust of the UAV.

[0036] combine figure 2 , the fuselage 1 is in the shape of a wing as a whole, and the curve of the section of the fuselage 1 can directly simulate the curve of a real aircraft wing, only in a reduced proportion. combine image 3 , the fuselage 1 includes a frame 15 and a casing 14, the casing 14 covers the surface of the frame 15, and the frame 15 is bonded inside. The upper surface of the casing 14 arches upwards to...

Embodiment 2

[0041] In order to further ensure the comparative stability of the transverse installation rod 21, as Figure 4 and Figure 5 As shown, the fuselage 1 includes a fuselage main body 16 and auxiliary support parts 17 fixed on both sides of the fuselage main body 16. Compared with the fuselage main body 16, the auxiliary support part 17 is closer to the vertical installation rod 22, and is installed horizontally. The rod 21 passes through the auxiliary support part 17 to fully support the transverse installation rod 21 and also increases the space for placing items inside the fuselage 1 to a certain extent. In order not to hinder the rotation of the rotor, the auxiliary support portion 17 is located between the two adjacent rotors, and a corner for the rotor rotation is formed between the auxiliary support portion 17 and the main body 16 of the fuselage, and the space at the corner is provided for the rotation of the rotor. space.

[0042]In order to make the connection between...

Embodiment 3

[0044] combine Figure 6 , in order to park the UAV more stably, the bottom of the fuselage 1 is fixed with a support foot 5, the lower end of the support foot 5 and the tail end of the fuselage 1 form a support plane, of course, it can also be at the tail end of the fuselage 1 Design auxiliary support feet 5.

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PUM

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Abstract

The invention discloses a multi-rotor-wing unmanned aerial vehicle with a power wing body. The multi-rotor-wing unmanned aerial vehicle is characterized by comprising a fuselage and rotor wing power sets mounted at two sides of the fuselage; the whole body of the fuselage is of a wing shape; a fixed rotor wing power set is mounted at the tail end of the fuselage, so that the aims of reducing the power consumption in a flight process and increasing a flying range are realized.

Description

technical field [0001] The invention relates to an unmanned aerial vehicle, in particular to a powered wing-body multi-rotor unmanned aerial vehicle. Background technique [0002] Unmanned aircraft, referred to as "unmanned aerial vehicle" ("UAV"), is an unmanned aircraft controlled by radio remote control equipment and its own program control device. UAV is actually a general term for unmanned aerial vehicles. From a technical point of view, it can be divided into: fixed-wing aircraft, unmanned vertical take-off and landing aircraft, multi-rotor UAV, etc. [0003] Existing multi-rotor drones can refer to the patent with the notification number CN206231620U. A drone includes a fuselage, a front wing and a rear wing fixed to the fuselage, a fixed-wing power group installed at the end, and a fixed-wing power group installed on the The rotor power pack on the side of the fuselage. The rotor power group can facilitate the vertical take-off and landing of the UAV, and the fixed...

Claims

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Application Information

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IPC IPC(8): B64C27/08B64C27/26
CPCB64C27/08B64C27/26B64U30/10B64U10/10B64U30/20B64U50/13
Inventor 石礼上刘继壮
Owner 北京白米科技有限公司
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