CN115901210A - Fatigue test device applicable to main starting side stay bar structure of airplane - Google Patents

Abstract

The invention is suitable for the mechanical field of structural test, has provided a fatigue test device suitable for the main side stay bar structure of plane, including MTS testing machine, and engaging lug that MTS testing machine telescopic end connects, also include: the device comprises a support, a frame, a first dummy piece, a second dummy piece, a connecting assembly and a connecting rod; the support is provided with threads and is screwed into a clamping shaft at the lower end of the MTS testing machine through the threads; the support is fixed on the frame through a connecting assembly, and the first dummy piece and the second dummy piece are also fixed on the frame through the connecting assembly. The innovative opposite side strut beam test piece structure adopts the self-design supporting clamp, so that the test needing to be carried out on the self-balancing frame can be realized on an MTS (maximum transmission station) tester, the mounting precision of the test piece is improved, and the fatigue test of the side strut beam is realized relatively simply and efficiently; the support platform is innovatively adopted for bearing force, so that the bending moment born by the lower end frame is reduced, and the influence caused by the displacement of the lower end supporting clamp in the vertical direction is reduced.

Description

A Fatigue Test Device Applicable to Aircraft Main Lifting Side Brace Structure

technical field

The invention belongs to the field of structural test mechanics, and in particular relates to a fatigue test device suitable for the structure of aircraft main lift side struts.

Background technique

Among various engineering structures in the aerospace field, the side strut beam structure is an important part of the aircraft landing gear. The fatigue capacity test of the side strut beam structure is carried out through the fatigue test, and the life of the side strut beam structure under fatigue load is analyzed. It is an important research topic in structural design. The actual fatigue load tonnage of the side-strut beam structure is large, and the space for applying the load is small, and it is necessary to realize the application of specific angles and specific positions on the side-strut beam structure in the laboratory to assess the fatigue life of the material and provide a basis for structural design. scientific basis.

For a long time, it has been very difficult to achieve low cost for this type of material testing. For the fatigue test of the side brace beam structure, self-balancing frame can be used at present, but due to the complicated ultimate load borne by the test piece, the actual size of the test piece is relatively large, and the loading space of the actuator is also limited. In addition, The test piece also has requirements on the loading accuracy and loading frequency, which imposes strict requirements on the use environment and personnel operation, resulting in high experimental requirements and high experimental costs.

Contents of the invention

The purpose of the embodiments of the present invention is to provide a fatigue test device suitable for the main strut structure of an aircraft, aiming at solving the problems of complex structure and high experimental requirements of the existing fatigue test device for the main strut structure of an aircraft.

The present invention is realized in this way, a kind of fatigue test device suitable for aircraft main starting side strut structure, comprises MTS testing machine, and the connecting lug that the telescopic end of MTS testing machine is connected, also includes:

Support, frame, first dummy, second dummy, connecting assembly and connecting rod;

The support is provided with threads, and the support is screwed into the clamping shaft at the lower end of the MTS testing machine through threads;

The support is fixed on the frame through the connection assembly, and the first dummy part and the second dummy part are also fixed on the frame through the connection assembly;

The connecting rod is rotatably connected to the first dummy part through a pin shaft, and the two ends of the aircraft main side strut are respectively rotatably connected to the second dummy part and the connecting rod through a pin shaft;

The connecting lug is also rotatably connected with the aircraft's main starting side strut through a pin shaft.

In a further technical solution, the connecting ear is screwed to the telescopic end of the MTS testing machine.

In a further technical solution, the connection assembly includes bolts and matching nuts, and the support, the frame, the first dummy and the second dummy are all provided with through holes for passing through the bolts;

And the frame is connected with the support, the first dummy part and the second dummy part through two sets of bolts and matching nuts.

In a further technical solution, pads are provided on both sides of the first dummy and the second dummy, and through holes for passing bolts are provided on the pads.

In a further technical solution, the frame is provided with a plurality of slots for reducing weight.

The embodiment of the present invention provides a fatigue test device suitable for the main strut structure of the aircraft. The innovative structure of the test piece of the opposite side strut beam adopts the self-designed support fixture, so that the test that needs to be carried out on the self-balancing frame can be carried out in the Realized on the MTS testing machine, improving the installation accuracy of the test piece, enabling the fatigue test of the side brace beam to be realized relatively simply and efficiently; innovatively adopting the support platform to bear the force, reducing the bending moment borne by the lower end frame, and reducing the lower end support fixture The impact of displacement in the vertical direction; holes are designed on the frame to reduce the weight of the frame, which is convenient for accurate loading, and the test can be carried out simply and efficiently.

Description of drawings

Fig. 1 is a structural schematic diagram of a fatigue test device suitable for aircraft main lift side strut structure provided by an embodiment of the present invention;

Fig. 2 is a schematic diagram of the connection structure of the frame in Fig. 1 provided by an embodiment of the present invention;

FIG. 3 is a schematic diagram of the front view structure of FIG. 2 provided by an embodiment of the present invention.

In the drawings: support 1, frame 2, first dummy 3, second dummy 4, spacer 5, bolt 6, supporting nut 7, connecting rod 8, connecting ear 9, MTS testing machine 10, aircraft main Lift the side strut 11.

Detailed ways

In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

The specific implementation of the present invention will be described in detail below in conjunction with specific embodiments.

As shown in Fig. 1, a kind of fatigue test device applicable to the main strut structure of the aircraft that is provided by an embodiment of the present invention includes an MTS testing machine 10, and a connecting ear 9 connected to the telescopic end of the MTS testing machine 10, and also includes :

Support 1, frame 2, first dummy 3, second dummy 4, connecting assembly and connecting rod 8;

The support 1 is provided with threads, and the support 1 is screwed into the clamping shaft at the lower end of the MTS testing machine 10 by threads;

The support 1 is fixed on the frame 2 through the connection assembly, and the first dummy 3 and the second dummy 4 are also fixed on the frame 2 through the connection assembly;

The connecting rod 8 is rotatably connected to the first dummy part 3 through a pin shaft, and the two ends of the main side strut 11 of the aircraft are respectively rotatably connected with the second dummy part 4 and the connecting rod 8 through a pin shaft;

The connecting ear 9 is also rotatably connected with the aircraft main lift side strut 11 through a pin shaft.

In the embodiment of the present invention, the specific steps of the experiment are as follows:

Step 1, screw the support 1 on the clamping shaft at the lower end of the MTS testing machine 10;

Step 2, the frame 2 is fixed on the support 1 through the connecting component;

Step 3, the first dummy part 3 and the second dummy part 4 are fixed on the frame 2 through the connection assembly;

Step 4, the connecting rod 8 is connected to the first dummy part 3 through the rotation of the pin shaft, and the experimental angles Q and W are determined by selecting the connecting rod 8 with a suitable length;

Step 5, the aircraft's main lifting side strut 11 is rotationally connected with the connecting rod 8, the second dummy part 4 and the connecting ear 9 through pin shafts;

Step 6, open the MTS testing machine 10, the hydraulic cylinder on the MTS testing machine 10 drives the connecting ear 9 to realize the gradual loading of the test load, and generates an axial load on the main lifting side strut 11 of the aircraft, and performs a fatigue test;

Step 7. After the test is completed, turn off the hydraulic pressure and power supply, disassemble the test device and perform sanitary cleaning on the test device.

As shown in FIG. 1 , as a preferred embodiment of the present invention, the connecting ear 9 is screwed to the telescopic end of the MTS testing machine 10 .

In the embodiment of the present invention, it is convenient to fix the connecting ear 9 on the telescopic end of the MTS testing machine 10 by means of threaded connection.

As shown in Fig. 2, as a preferred embodiment of the present invention, the connecting assembly includes bolts 6 and matching nuts 7, and on the support 1, the frame 2, the first dummy 3 and the second dummy 4 Both are provided with through holes for passing through bolts 6 ; and the frames 2 are connected to the support 1 , the first dummy 3 and the second dummy 4 through two sets of bolts 6 and matching nuts 7 .

In the embodiment of the present invention, the support 1, the first dummy 3 and the second dummy 4 are all provided with two through holes for passing through the bolts 6. When installing, the support 1, the first dummy 3 and the second dummy 4 The second dummy 4 is all placed in the interlayer of the frame 2, then the bolt 6 is passed through the through hole, and the supporting nut 7 is screwed on the bolt 6 to get final product.

As shown in Figures 1-3, as a preferred embodiment of the present invention, pads 5 are provided on both sides of the first dummy 3 and the second dummy 4, and the pads 5 are provided with useful The through hole for passing through the bolt 6.

In the embodiment of the present invention, pads 5 are provided on both sides of the first dummy 3 and the second dummy 4, thereby reducing the gap between the first dummy 3 and the second dummy 4 and the frame 2 , increase the stability of the connection between the first dummy 3 and the second dummy 4, and avoid movement of the first dummy 3 and the second dummy 4 during the experiment, so as to improve the accuracy of the experiment.

As shown in FIG. 2 , as a preferred embodiment of the present invention, the frame 2 is provided with a plurality of slots for reducing weight.

In the embodiment of the present invention, a plurality of slot holes are provided on the frame 2 in multiple directions to reduce the quality of the frame 2 .

In the above-mentioned embodiment of the present invention, a kind of fatigue test device suitable for the main lift side strut structure of the aircraft is provided, and the specific steps of the experiment are as follows:

Step 1, screw the support 1 on the clamping shaft at the lower end of the MTS testing machine 10;

Step 2, the frame 2 is fixed on the support 1 through the bolt 6 and the supporting nut 7;

Step 3, the first dummy part 3, the second dummy part 4, and the cushion block 5 are all fixed on the frame 2 by bolts 6 and supporting nuts 7;

Step 4, the connecting rod 8 is connected to the first dummy part 3 through the rotation of the pin shaft, and the experimental angles Q and W are determined by selecting the connecting rod 8 with a suitable length;

Step 5, the aircraft's main lifting side strut 11 is rotationally connected with the connecting rod 8, the second dummy part 4 and the connecting ear 9 through pin shafts;

Step 6, open the MTS testing machine 10, the hydraulic cylinder on the MTS testing machine 10 drives the connecting ear 9 to realize the gradual loading of the test load, and generates an axial load on the main lifting side strut 11 of the aircraft, and performs a fatigue test;

Step 7. After the test is completed, turn off the hydraulic pressure and power supply, disassemble the test device and perform sanitary cleaning on the test device.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. Any modifications, equivalent replacements and improvements made within the spirit and principles of the present invention should be included in the protection of the present invention. within range.

Claims (5)

1. A kind of fatigue test device that is applicable to aircraft main side strut structure, comprises MTS testing machine, and the connecting lug that MTS testing machine telescopic end connects, it is characterized in that, also comprises: Support, frame, first dummy, second dummy, connecting assembly and connecting rod; The support is provided with threads, and the support is screwed into the clamping shaft at the lower end of the MTS testing machine through threads; The support is fixed on the frame through the connection assembly, and the first dummy part and the second dummy part are also fixed on the frame through the connection assembly; The connecting rod is rotatably connected to the first dummy part through a pin shaft, and the two ends of the aircraft main side strut are respectively rotatably connected to the second dummy part and the connecting rod through a pin shaft; The connecting lug is also rotatably connected with the aircraft's main starting side strut through a pin shaft. 2 . The fatigue test device suitable for aircraft main lift side strut structure according to claim 1 , wherein the connecting ear is screwed to the telescopic end of the MTS testing machine. 3 . 3. The fatigue test device suitable for aircraft main side strut structure according to claim 1, characterized in that, the connecting assembly includes bolts and matching nuts, and the support, frame, first dummy and second dummy Both dummy parts are provided with through holes for inserting bolts; And the frame is connected with the support, the first dummy part and the second dummy part through two sets of bolts and matching nuts. 4. according to claim 3, be applicable to the fatigue test device of aircraft main side strut structure, it is characterized in that, the both sides of described first dummy and the second dummy are all provided with pads, and described pads There are through holes for inserting bolts. 5 . The fatigue test device applicable to the main strut structure of an aircraft according to claim 1 , wherein the frame is provided with a plurality of slots for reducing weight. 6 .

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