A statically stable four-tilt-wing unmanned aerial vehicle

A drone and stable technology, applied in the field of drones, can solve the problems of high flight control system requirements, aircraft static instability, and large-occupancy control, and achieve the effects of reducing difficulty, increasing static stability, and easy control

Pending Publication Date: 2018-12-28
西安君晖航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] Existing tilt-wing UAVs mainly use complex control methods to solve the control requirements of different flight modes of the tilt-wing. The design is difficult, and the requirements for the flight control system are high, and the static instability of the aircraft itself will take up a lot of time. control

Method used

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  • A statically stable four-tilt-wing unmanned aerial vehicle
  • A statically stable four-tilt-wing unmanned aerial vehicle
  • A statically stable four-tilt-wing unmanned aerial vehicle

Examples

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Embodiment 1

[0020] Example 1, such as Figure 1 to Figure 5 Shown:

[0021] A statically stable four-tilt UAV, including a fuselage 1, a front tandem double front wing 2, a tandem double rear wing 3, a horizontal tail 4, a vertical tail 5, a propeller and a nacelle 6, Horizontal aerodynamic rudder surface 7, tilting device 8, tandem double front wing 2 and tandem double rear wing 3 are equipped with horizontal aerodynamic rudder surface 7, propeller and nacelle 6, vertical tail 5 and horizontal tail 4 Both are located at the tail of the fuselage 1, the two sides of the fuselage 1 are connected with the tandem double front wings 2 and the tandem double rear wings 3, and the horizontal aerodynamic steering surface 7 is placed on the tandem double front wings 2 and the tandem The rear edge of the double rear wing 3, the propeller and the nacelle 6 are located on the front edge of the tandem double front wing 2 and the tandem double rear wing 3, and the tandem double front wing 2 and the tan...

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Abstract

The invention discloses a statically stable four-tilt-wing unmanned aerial vehicle, including fuselage, forward tandem twin forward wings, tandem twin aft wings, vertical tail, Propeller and nacelle,horizontal aerodynamic rudder, tilting device, A horizontal aerodynamic rudder surface, a propeller and a nacelle are arranged on the tandem double-front wing and the tandem double-rear wing, the vertical tail and the horizontal tail are both located at the tail part of the fuselage, the horizontal aerodynamic rudder surface is arranged on the trailing edges of the tandem double front wing and thetandem double rear wing, The propeller and the nacelle are arranged at the leading edges of the tandem twin-forward wing and the tandem twin-aft wing, and the tandem twin-forward wing and the tandemtwin-aft wing are controlled by an upward tilting shaft of the tilting device located in the fuselage. The invention ensures the static stability of the unmanned aerial vehicle (UAV) under the high-speed cruise, and makes the UAV have better stability under the vertical take-off and landing or the high-speed cruise.

Description

technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a statically stable four-tilt-wing unmanned aerial vehicle. Background technique [0002] Tilt-wing or tilt-rotor drones have the advantages of both high-speed cruise of fixed wings and vertical take-off and landing and hovering of multi-rotors, and have become one of the hotspots in the research and development of drones. [0003] However, the two flight modes of the tilting wing, that is, the fixed-wing mode and the multi-rotor mode, are two completely different flight forms, and the requirements for balance and control are different. At the same time, the transition mode requirements between the two modes are more complicated. , so its control is more difficult than manipulation. [0004] In the invention patent CN 206087301 U, a four-rotor UAV with variable pitch propellers is provided, and the attitude in flight is adjusted by controlling the pitch of the p...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/28B64C27/26
CPCB64C27/26B64C27/28B64U10/25
Inventor 张冰融潘祈帆陈希平
Owner 西安君晖航空科技有限公司
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