Three-airfoil layout vertical take-off and landing general aircraft

A vertical take-off and landing, layout technology, applied to aircraft parts, wings, power plant types, etc., can solve the problems of inability to realize direct force control, insufficient lift of general-purpose aircraft, poor safety and reliability, etc., and achieve favorable tilting and layout , Increase the static instability and ensure the effect of dynamic balance

Pending Publication Date: 2018-08-28
CHENGDU AERONAUTIC POLYTECHNIC
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  • Abstract
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  • Claims
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Problems solved by technology

[0009] In order to solve the problems existing in the prior art, the present invention provides a general-purpose vertical take-off and landing aircraft with a three-wing layout, which solves the problem that the lift of the general-purpose aircraft is i

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  • Three-airfoil layout vertical take-off and landing general aircraft
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  • Three-airfoil layout vertical take-off and landing general aircraft

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[0035] The embodiments of the present invention will be described in detail below in conjunction with the drawings.

[0036] The following describes the specific embodiments of the present invention to facilitate those skilled in the art to understand the present invention, but it should be clear that the present invention is not limited to the scope of the specific embodiments, for those of ordinary skill in the art, as long as various changes These changes are obvious within the spirit and scope of the present invention defined and determined by the appended claims, and all inventions and creations using the concept of the present invention are protected.

[0037] Such as Figure 1 to Figure 3 As shown, the three-wing layout of a vertical take-off and landing general-purpose aircraft includes: wing 1, fuselage 2, tail 3, canard 4, propulsion system and canard coaxial rotating device, power device and connecting device 5; power device includes The first power unit 6, the second po...

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Abstract

The invention discloses a three-airfoil layout vertical take-off and landing general aircraft, which comprises a wing, a fuselage, a tail wing, a duck wing, a power device, a connecting device, a propulsion system and a duck wing coaxial rotating device. The power device comprises a first power device, a second power device, a third power device and a fourth power device; the top of the fuselage is provided with the duck wing. Both ends of the duck wing are respectively provided with the first power device and the second power device. Both sides of the outer part of the fuselage and below theduck wing are respectively provided with wings. A connecting device is arranged below the wing. Both sides of the connecting device are respectively provided with the third power device and the fourthpower device. The bottom of the fuselage is provided with the tail wing. The control device is arranged inside the fuselage. The aircraft solves the problems of insufficient lift force, without direct force control, low static instability, low take-off and landing performance, poor safety reliability, heavy wing load, low take-off load and high use cost of the general aircraft.

Description

technical field [0001] The invention relates to the field of general-purpose aircraft, in particular to a vertical take-off and landing general-purpose aircraft with three-plane layout. Background technique [0002] The take-off and landing of general-purpose aircraft have conditional constraints, such as the need for a wide take-off runway, special site requirements, and a larger take-off site; general-purpose aircraft power devices are mainly turboprop engines and turboshaft engines with single power. Due to the limitation of power, the power cannot be tilted. [0003] The conventional layout of a general-purpose aircraft refers to the layout of the wing and the empennage. The conventional layout plus a horizontal front wing constitutes a three-plane layout, which not only can still maintain the beneficial interference of the canard detachment vortex at a short distance, but also improves the control efficiency and reduces the trim resistance by simultaneously operating t...

Claims

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Application Information

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IPC IPC(8): B64C3/00B64D27/18
CPCB64C3/00B64D27/18
Inventor 李吉赵兴霍蔚峰刘楚雨吴墙铵郑乐易林辉李健曾浩芸杨映根何智林蔡瀚宇杨林汤献金冯任杰唐文静张靖
Owner CHENGDU AERONAUTIC POLYTECHNIC
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