CN104849031A

CN104849031A - Bidirectional loading module

Info

Publication number: CN104849031A
Application number: CN201510200546.6A
Authority: CN
Inventors: 彭刚; 黄鹏; 李鸿; 王征宇; 岳宝成
Original assignee: Jiangxi Hongdu Aviation Industry Group Co Ltd
Current assignee: Jiangxi Hongdu Aviation Industry Group Co Ltd
Priority date: 2015-04-27
Filing date: 2015-04-27
Publication date: 2015-08-19

Abstract

The invention relates to a bidirectional loading module, and belongs to the technical field of an airplane structural intensity experiment apparatus. The bidirectional loading module comprises a first-grade lever, a first module and a second module. The first module and the second module are respectively built through two adhesive tapes, two hardwood blocks, two hollow aluminium rods, two collar screws, two transition levers and two connection screws. The bidirectional loading module controls a test spectrum to alternately change a load direction in real time along with programs of a slow test and a fatigue test while a testpiece structure is not damaged and a test device is not changed.

Description

A kind of biaxial loadings module

Technical field

The present invention relates to a kind of aircraft structure strength experimental provision, particularly relate to a kind of biaxial loadings module.

Background technology

Aircraft needs with much panel load simulated aircraft aerodynamic force or inertial force in stryctyrak test (as slow test, torture test), and each panel load draws load and compressive load two kinds.Under the condition of how not damage test part structure, need not change the outfit again test unit when, invent a kind of biaxial loadings module, alternation in real time to be met in the program-control test spectrum of slow test, torture test and changes the difficult point of loading direction.

Summary of the invention

The object of the present invention is to provide a kind of biaxial loadings module, it is under the condition of not damage test part structure, need not change the outfit again test unit when, alternation in real time to be met in the program-control test spectrum of slow test, torture test and changes loading direction.

For achieving the above object, the utility model have employed following technical proposals:

A kind of biaxial loadings module, comprise the 1st grade of lever, first module and the second module, the 1st grade of lever both sides, symmetry installs the first model calling screw rod and the second model calling screw rod respectively, the lower end of the first model calling screw rod connects the first module transition lever, a first module collar screw rod is respectively installed in first module transition lever both sides, two first module collar screw rod lower ends are respectively set with a hollow aluminium bar of the first module, two hollow aluminium bars of first module penetrate in the first module rubberized tape respectively, the first module hardwood block is established between two hollow aluminium bars of first module, the upper surface of the first module hardwood block is against the first module transition lever lower surface, the lower end of the second model calling screw rod connects the second module transition lever, a second module collar screw rod is respectively installed in second module transition lever both sides, two second module collar screw rod lower ends are respectively set with a hollow aluminium bar of the second module, two hollow aluminium bars of second module penetrate in the second module rubberized tape respectively, establish the second module hardwood block between two hollow aluminium bars of second module, the upper surface of the second module hardwood block is against the second module transition lever lower surface.

The present invention constitutes the loading lever system of aircraft structure strength test, it is under the condition of not damage test part structure, need not change the outfit again test unit when, in real time alternation to be met in the program-control test spectrum of slow test, torture test and changes loading direction.

Accompanying drawing explanation

Fig. 1 is schematic diagram of the present invention;

In the drawings: 101. first module rubberized tapes; 201. first module hardwood blocks; The hollow aluminium bar of 301. first module; 401. first module collar screw rods; 501. first module transition levers; 601. first model calling screw rods; 102. second module rubberized tapes; 202. second module hardwood blocks; The hollow aluminium bar of 302. second module; 402. second module collar screw rods; 502. second module transition levers; 602. second model calling screw rods; 7. the 1st grade of regulations and parameters bar.

Embodiment

As shown in Figure 1, a kind of biaxial loadings module, comprise the 1st grade of lever 7, first module and the second module, the 1st grade of lever 7 both sides, symmetry installs the first model calling screw rod 601 and the second model calling screw rod 602 respectively, and fixed by nuts and washers, the lower end of the first model calling screw rod 601 connects the first module transition lever 501, a first module collar screw rod 401 is respectively installed in first module transition lever 501 both sides, and fix with nut, two first module collar screw rod 401 lower ends are respectively set with a hollow aluminium bar 301 of the first module, two hollow aluminium bars 301 of first module penetrate in the first module rubberized tape 101 respectively, the first module hardwood block 201 is established between two hollow aluminium bars 301 of first module, the upper surface of the first module hardwood block 201 is against the first module transition lever 501 lower surface, the lower end of the second model calling screw rod 602 connects the second module transition lever 502, a second module collar screw rod 402 is respectively installed in second module transition lever 502 both sides, and fix with nut, two second module collar screw rod 402 lower ends are respectively set with a hollow aluminium bar 302 of the second module, two hollow aluminium bars 302 of second module penetrate in the second module rubberized tape 102 respectively, the upper surface of the second module hardwood block 202, second module hardwood block 202 is established to be against the second module transition lever 502 lower surface between two hollow aluminium bars 302 of second module.

First module hardwood block 201 is clamped by the first module hollow aluminium bar 301, first module collar screw rod 401, first module transition lever 501.

Second module hardwood block 202 is clamped by the second module hollow aluminium bar 302, second module collar screw rod 402, second module transition lever 502.

The present invention uses rubberized tape, hollow aluminium bar, hardwood block, collar screw rod, transition lever to form a load-on module unit, and the size of each load-on module unit can be determined according to panel load size; Each module in charge panel load, two module composition primary lever, in like manner form the loading lever system of aircraft structure strength test step by step.

In the present invention, rubberized tape is pasted onto aircraft surfaces node location place; Hardwood block is by hollow aluminium bar, collar screw rod, the clamping of transition lever; Collar screw rod is used for fixing transition lever, clamps hardwood block simultaneously.

Claims

1. a biaxial loadings module, comprise the 1st grade of lever, first module and the second module, it is characterized in that, the 1st grade of lever both sides, the first model calling screw rod and the second model calling screw rod are installed respectively, the lower end of the first model calling screw rod connects the first module transition lever, a first module collar screw rod is respectively installed in first module transition lever both sides, two first module collar screw rod lower ends are respectively set with a hollow aluminium bar of the first module, two hollow aluminium bars of first module penetrate in the first module rubberized tape respectively, the first module hardwood block is established between two hollow aluminium bars of first module, the upper surface of the first module hardwood block is against the first module transition lever lower surface, the lower end of the second model calling screw rod connects the second module transition lever, a second module collar screw rod is respectively installed in second module transition lever both sides, two second module collar screw rod lower ends are respectively set with a hollow aluminium bar of the second module, two hollow aluminium bars of second module penetrate in the second module rubberized tape respectively, establish the second module hardwood block between two hollow aluminium bars of second module, the upper surface of the second module hardwood block is against the second module transition lever lower surface.

2. a kind of biaxial loadings module according to claim 1, is characterized in that, the first module hardwood block is by the hollow aluminium bar of the first module, the first module collar screw rod, the first module transition lever clamping.

3. a kind of biaxial loadings module according to claim 1, is characterized in that, the second module hardwood block is by the hollow aluminium bar of the second module, the second module collar screw rod, the second module transition lever clamping.

4. a kind of biaxial loadings module according to claim 1, is characterized in that, when carrying out static(al) or torture test, draws load by first order lever, first, second module transition lever, collar screw rod, hollow aluminium bar, and rubberized tape passes to testpieces step by step; Compressive load passes through first order lever, first, second module transition lever, and hardwood block passes to testpieces step by step; Realize when test unit need not be changed the outfit, follow slow test, the program-control test spectrum of torture test becomes in real time and change loading direction.