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Leading-edge detachable type experiment wing structure based on piezoelectric deicing system

A kind of wing structure, disassembled technology, applied in deicing devices, aircraft parts, ground devices, etc., to achieve the effect of enriching the research content

Active Publication Date: 2016-01-20
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

Moreover, most of the current research on piezoelectric deicing systems focuses on flat panels. The research objects and models are simple, but there are few studies on actual wing airfoils. Therefore, the research on the piezoelectric deicing method under the premise of wing airfoils and deicing effect is particularly critical

Method used

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  • Leading-edge detachable type experiment wing structure based on piezoelectric deicing system
  • Leading-edge detachable type experiment wing structure based on piezoelectric deicing system
  • Leading-edge detachable type experiment wing structure based on piezoelectric deicing system

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Embodiment Construction

[0031] The present invention will be further explained below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the following specific embodiments are only used to illustrate the present invention but not to limit the scope of the present invention.

[0032] It can be seen from the accompanying drawings that this is a detachable leading edge experimental wing structure based on a piezoelectric deicing system. The surface of the experimental wing structure is covered with a skin, and the skin includes an airfoil that is laid on the leading edge of the wing. The leading edge skin of the wing and the trailing edge skin of the wing laid on the trailing edge of the wing, the piezoelectric sheet is pasted on the surface of the leading edge skin of the wing, and the vibration of the piezoelectric sheet is excited by energizing the piezoelectric sheet, and then the whole aircraft is excited. The skin on the leading edge of the wing vib...

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Abstract

The invention discloses a leading-edge detachable type experiment wing structure based on a piezoelectric deicing system. The structure comprises two leading-edge parts, one front-segment crossbeam, two rear-segment parts and one rear-segment crossbeam, wherein each leading-edge part and the rear-segment crossbeam are respectively arranged at the two ends of each rear-segment part, the rear-segment parts and the leading-edge parts are connected through the front-segment crossbeam, the two leading-edge parts are parallel to each other, the two leading-edge parts are symmetrical along a longitudinal center line of the experiment wing structure, and the spacing between the two leading-edge parts can be randomly adjusted. According to the invention, the leading-edge parts can be detachable and adjusted, and wing models with different wing expansion direction dimensions can be combined, such that diversity of research on piezoelectric deicing methods can be realized according to different adjustment wing structures of research objects.

Description

technical field [0001] The invention relates to a detachable leading-edge experimental wing structure based on a piezoelectric deicing system, which belongs to the technical field of aircraft experimental structures. Background technique [0002] When the aircraft flies in the cloud layer containing supercooled water droplets, the windward surface such as the lift surface of the wing and tail, and the leading edge of the air inlet will freeze, which poses a serious threat to flight safety. Therefore, it is necessary to take reasonable anti-icing and de-icing measures. ice measures. For the relevant anti-icing methods at the present stage, the piezoelectric deicing method, as a new type of deicing method, has broad development prospects due to its advantages of low energy consumption and high efficiency. [0003] The piezoelectric deicing system combined with the piezoelectric deicing method is mainly used in the deicing process of some small aircraft wing surfaces that are ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D15/00B64F5/00
Inventor 苗波朱春玲朱程香王渊
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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