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Composite-wing vertical take-off and landing aircraft

A vertical take-off and landing, aircraft technology, applied in aircraft, rotorcraft, motor vehicles, etc., can solve the problems of poor yaw control ability, low structure utilization, etc., to improve robustness, avoid negative effects, and improve overall performance Effect

Inactive Publication Date: 2016-05-04
CHENGDU JOUAV AUTOMATION TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Aiming at the control problem of the flight attitude of the compound wing aircraft in the above-mentioned prior art, the present invention provides a compound wing vertical take-off and landing aircraft, which is used to solve the problem of poor yaw control ability and low speed of the compound wing vertical take-off and landing aircraft in the prior art The problem of low structural utilization

Method used

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Examples

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Embodiment 1

[0036] like Figure 1 to Figure 4 As shown, a compound wing vertical take-off and landing aircraft comprises a fuselage 1, a wing 2, a tail brace 3, an empennage 4, a vertical power unit 5 and a horizontal power unit 6, and the wing 2 is fixed on the middle section of the fuselage 1 , the wing 2 is symmetrical with respect to the longitudinal direction of the fuselage 1;

[0037] There are two tail braces 3, and different tail braces 3 are respectively fixed on the wings 2 on different sides of the fuselage 1;

[0038] The horizontal power unit 6 is fixed on the fuselage 1, and the left and right ends of the empennage 4 are respectively fixedly connected with the tails of different tail braces 3,

[0039] Described vertical power unit 5 is four, and each tail brace 3 is provided with two vertical power units 5, and the two vertical power units 5 on the same side of the fuselage 1 are located at different positions in the length direction of the aircraft, and the fuselage 1 A...

Embodiment 2

[0045] The present embodiment is further limited on the basis of embodiment 1, as Figure 1 to Figure 4 As shown, the rear edge of the empennage 4 is also hingedly connected with two aerodynamic rudder surfaces that are in a left-right symmetrical relationship with each other. The aerodynamic rudder surface is an elevating rudder, so that the flight attitude of the aircraft can be adjusted through the aerodynamic rudder surface when the aircraft is flying in a fixed-wing attitude.

[0046] The wings 2 on both sides of the fuselage 1 are provided with a yaw control unit 7, the yaw control unit 7 includes a yaw propeller, and the yaw propeller is used to provide the wing 2 with a direction parallel to the length of the fuselage 1. direction, and the yaw control unit 7 is close to the end of the wing 2 .

[0047] In the above scheme, the yaw control unit 7 is used to provide the yaw moment, and the mechanism is as follows: the left and right yaw control units 7 of the aircraft a...

Embodiment 3

[0054] This embodiment is further limited on the basis of any one of the technical solutions provided by the above embodiments, such as Figure 1 to Figure 4 , in order to change the wing 2 output yaw moment and roll moment through the wing 2 under the high-speed flight state of the aircraft, and facilitate the adjustment of the above-mentioned yaw moment and roll moment at the same time, the wings 2 on each side of the fuselage 1 A piece of aileron is hingedly connected on the top, and the two ailerons are symmetrical with respect to the length direction of the fuselage 1. The inclination angle of the aileron and the wing 2, and the inclination angle of the aileron and the fuselage 1 are all adjustable.

[0055] As a specific implementation form of the drive device for braking the rotation of the level-flying propeller, the level-flying propeller is driven by an internal combustion engine or an electric motor. It is preferably set that the driving device includes an internal ...

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Abstract

The invention discloses a composite-wing vertical take-off and landing aircraft which adopts a special vertical power unit and an integral structure design. According to the scheme provided by the invention, compared with the prior art, the composite-wing vertical take-off and landing aircraft has the advantages that a maximum yaw control moment of the aircraft is largely improved, negative influence of yaw control saturation on aircraft posture control is avoided, and the robustness of the aircraft is improved; furthermore, the technical scheme of a tail boom is beneficial to improvement of the whole performance of the aircraft.

Description

technical field [0001] The invention relates to a fixed-wing aircraft, in particular to a compound-wing vertical take-off and landing aircraft. Background technique [0002] The composite wing layout is a solution for vertical take-off and landing aircraft that combines the fixed-wing layout and the multi-rotor layout. Flight functions such as climbing and descending can also overcome gravity through aerodynamic lift like a fixed-wing aircraft, and the power system can overcome aerodynamic resistance to achieve high-speed cruise flight. Due to its reliable structure, mature mechanical model, and relatively easy control and navigation during the transition between vertical flight and horizontal flight, the composite wing UAV has become a long-endurance vertical take-off and landing aircraft solution with low technical risk and high feasibility. [0003] Due to the above technical characteristics, compound wing vertical take-off and landing aircraft has been a research and de...

Claims

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Application Information

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IPC IPC(8): B64C27/22B64C27/24
CPCB64C27/22B64C27/24
Inventor 任斌王陈王利光
Owner CHENGDU JOUAV AUTOMATION TECH
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