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A coaxial rotor variant vertical take-off and landing aircraft

A vertical take-off and landing, aircraft technology, applied in the aviation field, can solve the problems of large power, large wing area, high static pull requirements, etc., achieve strong stability and wind resistance, improve landing safety, and achieve energy management. and comprehensive utilization

Active Publication Date: 2021-07-16
CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this kind of aircraft has high requirements on the static tension of the power propeller, and requires a large amount of power, and because the center of gravity of the aircraft is high, the wing area is large, and the wind resistance in the take-off and landing state is poor.

Method used

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  • A coaxial rotor variant vertical take-off and landing aircraft
  • A coaxial rotor variant vertical take-off and landing aircraft
  • A coaxial rotor variant vertical take-off and landing aircraft

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Embodiment Construction

[0022] The details and operations of the present invention will be described in connection with the accompanying drawings. This patent is a vertical start and landing aircraft, including: front body 1, medium body 2, rear body 3, front pad 4, high speed pad 5, rear paddle 6, front rotor 7 , Foldable waist push propeller 8 and a hind rotor 9, where

[0023] The front body 1 and the middle body 2 are connected between the front pad 4, the front rotor 7 is mounted on the front pad 4;

[0024] In the middle body 2, the rear body 3 is connected between the high-speed pad 5, and the foldable waist push propeller 8 is mounted on the high speed pad 5;

[0025] The rear body 3 is equipped with a rear paddle 6, and the hind rotor 9 is mounted on the paddle 6.

[0026] The front rotor 7 and the rear rotor 9 can be rotated in reverse.

[0027] The front rotor 7 and a rear rotor 9 can be separately pitch.

[0028] figure 2 with image 3 It is shown that the two modalities of the aircraft are v...

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Abstract

This patent is designed for a small unmanned aerial vehicle and belongs to the field of aviation. A kind of coaxial rotor variant vertical take-off and landing aircraft is characterized in that it comprises: front fuselage (1), middle fuselage (2), rear fuselage (3), front paddle disc (4), high-speed paddle disc ( 5), the rear paddle disc (6), the front rotor (7), the foldable hip propeller (8) and the rear rotor (9), wherein the front fuselage (1) and the middle fuselage (2) pass through the front The paddle disc (4) is connected, and the front rotor (7) is installed on the front paddle disc (4); the middle fuselage (2) and the rear fuselage (3) are connected by a high-speed paddle disc (5), and the waist thruster can be folded Propeller (8) is installed on the high-speed paddle disc (5); Rear paddle disc (6) is equipped with at rear fuselage (3) tail end, and rear rotor (9) is installed on the rear paddle disc (6). The invention effectively reduces the demand on the aircraft power unit, and is compatible with vertical take-off and landing and long-time cruise.

Description

Technical field [0001] This patent is a small unmanned aircraft design and belongs to the aviation field. Background technique [0002] Compared to aircraft with horizontal takeoff mode, vertical start-offline adaptability is good, and currently common vertical start-offlines generally use rotor layout and tail layout. [0003] The lift of the rotor layout aircraft is provided by the rotor, and the efficiency of the rotor is high in the takeoff and hover state, and the rotor is not high in the air, and the high speed and long cruise flight cannot be achieved. [0004] The tail seat layout uses a large thrust propeller to pull the aircraft directly from the ground, complete the forward flight attitude conversion in the air, and the lift of the flying state will be provided by the wing; landing must be replaced by reverse flight attitude The end of the machine. However, this aircraft requires high static tensile force of the power propeller, and it is necessary to have a large powe...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/24B64C29/02
CPCB64C27/24B64C29/02B64U10/25
Inventor 金曦孙兆虎史文卿王劲王鑫
Owner CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
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