Dynamic stiffness active compensation method of thin-wall cylinder shell

A thin-walled cylindrical, active compensation technology, applied in aircraft parts, fuselage, transportation and packaging, etc., can solve the problems of insignificant aerothermal effect, insignificant improvement of structural dynamic stiffness, and inability to actively adjust structural dynamic stiffness.

Inactive Publication Date: 2017-07-25
HARBIN INST OF TECH
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Problems solved by technology

[0004] The invention provides an active compensation method for the dynamic stiffness of a thin-walled cylindrical shell, which solves the problem that the traditional method overcomes the aerothermal effect to adjust the structural stiffness characteristics of the aircraft, and the aerothermal effect is not obvious, the improvement of the structural dynamic stiffness is not obvious, and the structural dynamic stiffness cannot be actively adjusted.

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  • Dynamic stiffness active compensation method of thin-wall cylinder shell
  • Dynamic stiffness active compensation method of thin-wall cylinder shell
  • Dynamic stiffness active compensation method of thin-wall cylinder shell

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Embodiment Construction

[0013] The technical solutions of the present invention will be further described below in conjunction with the accompanying drawings and through specific implementation methods.

[0014] see figure 1 As shown, an active compensation method for dynamic stiffness of a thin-walled cylindrical shell in this embodiment includes;

[0015] Step 1. Select several concentrated force application points 2 on both ends of the thin-walled cylindrical shell 3, and the concentrated force application points 2 are evenly distributed along the circumference of the two ends;

[0016] Step 2: Apply a constant concentrated force F of the same magnitude, parallel to the axis of the thin-walled cylindrical shell and outwards at the concentrated force application point 2 on both ends of the thin-walled cylindrical shell 3 .

[0017] At the concentrated force application point 2 on the two ends of the thin-walled cylindrical shell 3, a constant concentrated force F of the same size and direction par...

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Abstract

The invention relates to a structural dynamic stiffness compensation method, in particular to a dynamic stiffness active compensation method of a thin-wall cylinder shell. The problems that when the pneumatic heat effect which changes aircraft structural stiffness characters is overcome through a traditional mode, changing of the pneumatic heat effect is not obvious, improvement of the structural dynamic stiffness is not obvious, and the structural dynamic stiffness cannot be actively adjusted are solved. The method comprises the steps that one, a plurality of concentrated force exerting points are selected on the two end faces of the thin-wall cylinder shell correspondingly and evenly distributed in the circumferential directions of the two end faces; and two, constant concentrated force the same in size, parallel to the axis of the thin-wall cylinder shell in direction and towards the outer side is exerted at the concentrated force exerting points of the two end faces of the thin-wall cylinder shell. The dynamic stiffness active compensation method of the thin-wall cylinder shell is used for structural dynamic stiffness adjustment.

Description

technical field [0001] The invention relates to a method for compensating dynamic stiffness of a structure, in particular to a method for actively compensating dynamic stiffness of a thin-walled cylindrical shell. Background technique [0002] After decades of continuous development, human beings have made unprecedented achievements in the research of aircraft, and the speed of various aircraft has also been continuously improved. Subsonic, transonic, supersonic and hypersonic aircraft emerge in endlessly. When the aircraft is flying at high speed, the elastic force, inertial force, aerodynamic force, and thermal effect acting on the thin-walled cylindrical shell structure of the aircraft are coupled with each other, which is easy to cause aerothermoelastic problems. The aerothermal effect will change the stiffness characteristics of the aircraft. As a result, the flutter velocity of the thin-walled cylindrical shell structure of the aircraft decreases, which has a serious i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/38
CPCB64C1/38
Inventor 岳洪浩俞正旺李雨时王雷邓宗全
Owner HARBIN INST OF TECH
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