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Helicopter fuselage negative stiffness dynamic vibration absorption and isolation device and helicopter thereof

A technology of dynamic vibration absorption and negative stiffness, applied in the field of vibration reduction, can solve problems such as amplification, and achieve the effects of simple maintenance, convenient operation and low cost

Active Publication Date: 2022-07-15
SHANGHAI JIAO TONG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Although dynamic anti-resonance can effectively isolate vibrations at the rotor excitation frequency, it amplifies vibrations in the frequency band after this frequency

Method used

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  • Helicopter fuselage negative stiffness dynamic vibration absorption and isolation device and helicopter thereof
  • Helicopter fuselage negative stiffness dynamic vibration absorption and isolation device and helicopter thereof
  • Helicopter fuselage negative stiffness dynamic vibration absorption and isolation device and helicopter thereof

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Embodiment Construction

[0029] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the inventive concept. These all belong to the protection scope of the present invention.

[0030] like figure 1 Shown is a schematic structural diagram of the negative stiffness dynamic vibration absorption and isolation device for the helicopter body of the present invention. like figure 2 Shown is a schematic diagram of the connection between the helicopter rotor and the fuselage of the negative stiffness dynamic vibration isolation device of the helicopter fuselage of the present invention. like image 3 Shown is the basic principle diagram of the negative stiffness dynamic vibration absorptio...

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Abstract

The invention provides a helicopter body negative stiffness dynamic vibration absorption and isolation device in the technical field of vibration reduction. The helicopter body negative stiffness dynamic vibration absorption and isolation device comprises an inclined supporting rod, and the inclined supporting rod comprises a supporting rod body, a cavity structure, a main bearing elastic element, a viscoelastic element, a mass block, a negative stiffness element and a negative stiffness element compression amount adjusting mechanism. The viscoelastic element is fixedly arranged on a bottom boss of the supporting rod, the mass block is fixedly arranged on the viscoelastic element, the negative stiffness element is connected to the mass block, and the viscoelastic element, the mass block, the negative stiffness element and the main supporting elastic element are arranged in parallel. By arranging the main supporting elastic element, the viscoelastic element, the mass block, the negative stiffness element and the negative stiffness element compression amount adjusting mechanism, the negative stiffness element compression amount adjusting mechanism can achieve the corresponding negative stiffness element compression amount when the negative stiffness is optimal, and the device has the advantages of being safe, reliable, light in weight, small in size, low in cost and convenient to operate; and the vibration in the frequency band after the main excitation frequency of the rotor wing is not amplified again.

Description

technical field [0001] The invention relates to the technical field of vibration reduction, in particular to a negative stiffness dynamic vibration absorption and vibration isolation device of a helicopter body and a helicopter thereof. Background technique [0002] Helicopter plays an important role in carrying out special tasks such as civil and military operations. Due to the complexity of its working dynamic environment, the vibration load caused by the rotor of the helicopter will be transmitted to the cockpit of the helicopter, causing vibration and noise, which seriously affects the occupants and pilots. It affects the ride comfort of the crew and affects the fatigue of the helicopter components. Reducing the transmission of rotor vibration loads to the fuselage has very significant value and significance. However, due to the heavy weight of the helicopter's rotor and cockpit, and the need to transmit the lift generated by the rotor to the main drive system through t...

Claims

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Application Information

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IPC IPC(8): F16F15/02F16F15/04F16F15/08F16F15/22B64C27/04
CPCF16F15/022F16F15/046F16F15/085F16F15/22B64C27/04F16F2228/063F16F2230/32F16F2232/08Y02T50/40
Inventor 黄修长华宏星
Owner SHANGHAI JIAO TONG UNIV
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