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Helicopter dedicated damping device

A vibration-damping device, a technology for helicopters, applied in the directions of fuselage, aircraft parts, transportation and packaging, can solve the problem of narrow vibration-damping bandwidth, and achieve the effects of simple structure, reduced driving fatigue, and easy installation.

Active Publication Date: 2015-11-25
HARBIN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The dynamic vibration absorber can effectively reduce the vibration level, but the dynamic vibration absorber generally has a relatively narrow vibration reduction bandwidth, and usually needs to add a relatively large mass

Method used

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  • Helicopter dedicated damping device
  • Helicopter dedicated damping device
  • Helicopter dedicated damping device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0028] 1. Manufacture the vibration damping device according to the design drawings, material: 7010-T7451-δ25, standard ASNA3098.8870; wool size: 200×100, see the attachment for specific dimensions figure 1 , attached figure 2 , attached image 3 .

[0029] 2. The installation process of the vibration damping device is as follows:

[0030] 1) The vibration damping device is connected with the web 10 of the frame 1 and the side beam edge 11 with the connecting bolt 6, the connecting rivet 7 and the gasket 8; it is connected with the upper edge of the fuselage longitudinal beam 9, the lower edge of the Longitudinal beam web 14, floor 15, connect with connecting rivet 7. See attached for specific installation location Figure 4 .

[0031] 2) The side distance of the rivet is 7-8mm, the spacing is 18-20mm, the side distance of the bolt is 10-12mm, and the spacing is 18-20mm.

[0032] 3. Flight verification. A vertical acceleration sensor is arranged at the driver's pedals, ...

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Abstract

The invention belongs to the technical field of helicopter design, and especially relates to a helicopter dedicated damping device. The helicopter dedicated damping device is characterized by comprising a base plate (1), an upper edge strip (2), a lateral edge (3), a lower edge strip (4), and a vertical rib (5); the base plate (1) is in a trapezoid shape, the upper edge strip (2) is arranged on the upper bottom edge of the base plate (1), the lateral edge (3) is arranged on the lateral edge of the base plate (1), the lower edge strip is arranged on the lower bottom edge of the base plate (1), and the vertical rib (5) is parallel to the upper edge strip (2) and the lower edge strip (4) and is arranged on the median line of the base plate (1). The base plate (1) is connected to the fuselage vertical web (14) through rivets; the upper edge strip (2) is connected to the fuselage vertical beam upper edge strip (9) and floor (15) through rivets; the lower edge strip (4) is connected to the fuselage vertical beam lower strip (13) through rivets; and the lateral edge (3) is connected to the edge gasket (8), frame web (10), and beam edge strip (11) through bolts and rivets. The damping device has the advantages of simple structure and lightness, and is convenient to installed, and the connection rigidity is adjustable.

Description

technical field [0001] The invention belongs to the technical field of helicopter design, in particular to a special damping device for helicopters. Background technique [0002] With the development of helicopter design technology and the expansion of application fields, helicopter comfort has become an important research topic from the previous focus on helicopter flight performance and reliability strength. The index for evaluating the comfort of a helicopter is the level of body vibration. At present, helicopter vibration reduction technology mainly includes active control vibration reduction technology and passive vibration reduction technology. [0003] 1) Active control vibration reduction is to reduce the vibration and aerodynamic load of the helicopter blades by controlling the blades, so as to achieve the purpose of rotor vibration reduction. For example, NASA has carried out flight test and verification work with the CH-53 helicopter as the background since 1995...

Claims

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Application Information

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IPC IPC(8): B64C1/38
Inventor 高磊孙秀文张亚军赵泽乾
Owner HARBIN
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