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A four-point support fixture for a twin-fuselage model

A four-point support and fixing device technology, which is applied in the direction of measuring devices, machine/structural parts testing, instruments, etc., can solve the problems of structural super-static indetermination, affecting experimental results, model damage, etc., and achieves small internal loads and high test results. accurate effect

Active Publication Date: 2022-01-04
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] (1) Since the support position of the strut is not necessarily the modal fulcrum of the wing, the vibration form of the wing cannot be simulated
[0005] (2) The vibration simulation of the fuselage is disturbed. Since the boundary conditions are fixed, the vibration characteristics of the fuselage cannot be simulated.
[0006] (3) Due to the use of fixed supports in two or more positions of the fuselage, the structure will be super-statically indeterminate, and corresponding internal stress will be generated, which will affect the experimental results and even cause damage to the model
[0007] (4) It is generally difficult to realize the simulation of aeroelasticity test

Method used

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  • A four-point support fixture for a twin-fuselage model
  • A four-point support fixture for a twin-fuselage model
  • A four-point support fixture for a twin-fuselage model

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Embodiment Construction

[0030] The present invention will be further elaborated below in conjunction with embodiment.

[0031] The invention provides a four-point support and fixing device for a double-fuselage model, which establishes a fully elastic support mechanism for a double-fuselage structure, uses the elastic support method to realize the real simulation of the structural characteristics of the aircraft, and provides reliable support for the development and innovation of the double-fuselage structure. test technical support.

[0032] like figure 1 As shown, the four-point support fixture mainly includes double-hole fixed scimitars 8, 2 poles 3, 2 rear node support sleeves 10, 2 front node support sleeves 4, 2 front node cylinder fixing plates 5, 2 rear node fixing bolts 12, 2 front support sleeve fastening studs 13 and the external double fuselage model; wherein, the double-hole fixed scimitar 8 includes 2 hollow columnar connecting cylinders 81 and 1 connecting rod 82; 2 The connecting cy...

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Abstract

The invention relates to a four-point support and fixing device for a double fuselage model, which belongs to the technical field of aeroelasticity test; The front node column surface fixing plate, 2 front support sleeve fastening studs; the double-hole fixed scimitar includes 2 hollow columnar connecting cylinders and 1 connecting rod; one of the rods is coaxially connected with one of the connecting cylinders; Another support rod is coaxially connected with the other connecting cylinder; a rear node support sleeve is set on the middle outer wall of each support rod; a front node support sleeve is set on the axial head end of each support rod; each front node support sleeve The support sleeve and the corresponding support rod are fixedly connected by a front support sleeve fastening stud; the top of each front node support sleeve is correspondingly provided with a front node cylinder fixing plate; the invention realizes the full elastic model of the double fuselage Elastic fixation for vibration characterization tests.

Description

technical field [0001] The invention belongs to the technical field of aeroelasticity tests, and relates to a four-point support and fixing device for a double fuselage model. Background technique [0002] Generally speaking, during the aeroelastic test, the model needs to be elastically supported, and the support position should be the node position of the mode shape of the model. For the dual-fuselage model, there are vibrations in both directions of the fuselage and the wing. In the past, in the vibration test of this type of aircraft structure model, the node positions were rigidly fixed. Fix the model to the pole with bolts or other means. [0003] However, the existing model fixing methods have the following deficiencies: [0004] (1) Since the support position of the strut is not necessarily the modal fulcrum of the wing, the vibration form of the wing cannot be simulated. [0005] (2) The vibration simulation of the fuselage is disturbed. Since the boundary condit...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M5/00G01M9/00
CPCG01M5/0066G01M9/00
Inventor 侯英昱吕计男刘子强
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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