Air vehicle airfoil folding mechanism

A folding mechanism and aircraft technology, applied in the field of aircraft, can solve the problems of insufficient stability and maneuverability, and achieve the effects of low cost, high structural efficiency, and simple manufacturing

Active Publication Date: 2019-03-08
AVIC SHENYANG AERODYNAMICS RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the folding wing variants proposed by scholars from various countries essentially represent the advancement of the swept wing, and are generally based on the flying wing layout. However, the serious defect of this layout design is the lack of stability and controllability.

Method used

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  • Air vehicle airfoil folding mechanism
  • Air vehicle airfoil folding mechanism
  • Air vehicle airfoil folding mechanism

Examples

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Embodiment Construction

[0023] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0024] to combine Figure 1-4 As shown, what is disclosed in this embodiment includes a deformation system 3 and the deformation system is arranged between the aircraft fuselage 1 and the wing 2, the deformation system 3 includes several groups of folding hinges and several groups of folding surfaces, the deformation System 3 is respectively movably connected with aircraft fuselage 1 and wing 2 through the folding hinges, and the deformation system 3 keeps the leading edge of the wing 2 and the trailing edge of the deformation system 3 all the time during the deformation process; wherein the folding mechanism 3 It is fully unfolded at low speed, and the folding mechanism 3' is half unfolded at transonic speed; the outer side of the deformation system is covered with a flexible skin 20, and the deformation system is driven and deformed by the drive system, which is ar...

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Abstract

The invention relates to the technical field of air vehicles and in particular relates to an air vehicle airfoil folding mechanism. The air vehicle airfoil folding mechanism comprises a transformationsystem, wherein the transformation system is arranged between a fuselage and a wing of the air vehicle; the transformation system comprises a plurality of groups of folding hinges and a plurality offolding planes; the transformation system is movably connected with the fuselage and the wing of the air vehicle respectively through the folding hinges; in a transformation process of the transformation system, a front edge of the wing can keep moving along a tail edge of the transformation system all the time; advanced aerodynamic properties of a forward-swept wing and a folding wing are integrated to realize a novel forward-swept wing and folding wing combinatory transformation manner; the flight stability and the wide-speed-region flight performance are improved.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to an aircraft wing surface folding mechanism. Background technique [0002] In a broad sense, "variable aircraft" refers to an aircraft that actively changes its aerodynamic shape in order to obtain the required flight performance, environment and task adaptability. This definition covers almost all the methods used to change the shape of aircraft in the history of aviation. The morphing aircraft can change the shape of the aircraft locally or as a whole, so that the aircraft can be efficient, high-performance, and adapt to various flight environments and mission requirements in real time. It is one of the important research directions in the design of near space vehicles. Among them, the folding wing variant aircraft is a variant scheme that has attracted much attention in recent years. The folding wing variant proposed by Lockheed Martin in the MAS (Morphing Aircraft Structures...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/30B64C3/38
CPCB64C1/30B64C3/38
Inventor 李雪飞钱战森李俊李春鹏向先宏
Owner AVIC SHENYANG AERODYNAMICS RES INST
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