Four-point supporting and fixing device for double-fuselage model

Abstract

The invention relates to a four-point supporting and fixing device for a double-fuselage model, and belongs to the technical field of aeroelasticity tests. The device comprises a double-hole fixed bent knife, two supporting rods, two rear joint supporting sleeves, two front joint supporting sleeves, two front joint cylindrical surface fixing plates and two front supporting sleeve fastening studs.The double-hole fixed bent knife comprises two hollow columnar connecting cylinders and a connecting rod; one of the supporting rods is coaxially butted with one of the connecting cylinders; the othersupporting rod is coaxially butted with the other connecting cylinder; the outer wall of the middle of each supporting rod is sleeved with one rear joint supporting sleeve. The axial head end of eachsupporting rod is sleeved with one front joint supporting sleeve. Each front node supporting sleeve is fixedly connected with the corresponding supporting rod through a front supporting sleeve fastening stud; a front node cylindrical surface fixing plate is correspondingly arranged at the top of each front node supporting sleeve; according to the invention, the elastic fixation of the vibration characteristic test of the double-fuselage full-elastic model is realized.

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...

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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

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