CN-120043882-B - Dynamic shearing testing device and testing method for flexible connection assembly of aircraft fuel system

CN120043882BCN 120043882 BCN120043882 BCN 120043882BCN-120043882-B

Abstract

The invention belongs to the technical field of testing, and in particular relates to a dynamic shearing testing device and a testing method for a flexible connecting component of an aircraft fuel system, wherein the testing device comprises a reciprocating component, a clamping component and a loading component, a second pushing block in the reciprocating component is connected with a first clamping block in the clamping component, the loading component is arranged at one side of the clamping component, the reciprocating component applies shearing load to the flexible connecting component, the clamping component is responsible for clamping and fixing a test tube, the loading component injects pressure into the test tube, through using flexible coupling assembly to connect two sections of test tubes, the pressurization module in the loading subassembly is controlled again and is pressurized and the electric cylinder in reciprocating assembly is exerted thrust to the test tube of accompanying to test the inside operating pressure and the outside shear load of flexible coupling assembly, provides standard equipment and method for developing flexible coupling assembly's life test research to provide the reference when flexible coupling assembly selects the type.

Inventors

ZHAO JIAXIN
Gu Bochao
WANG JINGXI
LU YUE
YANG HAIQIANG
CHENG WULIN
ZHAO LINGFENG
ZHOU ZHE
LI PENGFEI
XU JINGWEN
ZHANG PANLIN

Assignees

中国航空综合技术研究所

Dates

Publication Date: 20260505
Application Date: 20250228

Claims (7)

1. The dynamic shearing testing device for the flexible connection assembly of the aircraft fuel system is characterized by comprising a reciprocating assembly, a clamping assembly and a loading assembly, wherein a second pushing block in the reciprocating assembly is connected with a first clamping block in the clamping assembly, and the loading assembly is arranged on one side of the clamping assembly; The reciprocating assembly comprises a base, an electric cylinder mounting seat, an electric cylinder, a first push block, a second push block and an external pressure sensor, wherein the electric cylinder mounting seat is arranged at the first end of the base, the electric cylinder is mounted on the electric cylinder mounting seat, the output end of the electric cylinder penetrates through the electric cylinder mounting seat, the first end of the first push block is connected with the output shaft of the electric cylinder, and the second end of the first push block is connected with the first end of the second push block through the external pressure sensor; The clamping assembly comprises a first clamping block, a second clamping block, an axial limiting block, a lateral pipeline, a sliding rod, a sliding block, a supporting plate, a middle fixing plate and a middle pipeline, wherein the first clamping block is in butt joint with the second clamping block, the lateral pipeline is installed in a round hole formed by the butt joint of the first clamping block and the second clamping block, the supporting plate is arranged at the second end of the base, four corners of the supporting plate are provided with rectangular sliding grooves, the sliding block is installed in the rectangular sliding grooves and can slide in the rectangular sliding grooves, the sliding rod sequentially penetrates through slotted holes at two ends of the first clamping block and the second clamping block, the two ends of the sliding rod are respectively matched with the sliding block installed on the supporting plate, the middle fixing plate is arranged at the middle position of the two supporting plates, and the joints of the lateral pipeline and the first clamping block and the second clamping block and the joints of the middle fixing plate and the middle pipeline are respectively provided with the axial limiting block; The center line of the output shaft of the electric cylinder is spatially parallel to the center line of the sliding rod; The first clamping block, the second clamping block, the axial limiting block, the lateral pipeline, the sliding rod and the sliding block in the clamping assembly are symmetrically arranged on two sides of the middle fixing plate; The center line of the middle round hole of the lateral pipeline is collinear with the center line of the middle round hole of the middle pipeline.
2. The aircraft fuel system flexible connection assembly dynamic shear test device of claim 1, wherein the loading assembly comprises a pressurization module, a pressure transmission tube, a three-way adapter and an internal pressure sensor, the pressurization module is connected with a first end of the three-way adapter through the pressure transmission tube, and a second end of the three-way adapter is connected with the internal pressure sensor.
3. A method of testing a dynamic shear test device for flexible connection units of an aircraft fuel system according to claim 1 or 2, comprising the steps of: S1, building a test device, namely respectively installing a first accompanying test tube and a third accompanying test tube in the middle of two lateral pipelines, installing a second accompanying test tube in the middle of the middle pipeline, installing plugs at the outer side ends of the first accompanying test tubes, installing flexible connection components to be tested at the inner side ends of the first accompanying test tubes and the first ends of the second accompanying test tubes, installing flexible connection components to be tested at the second ends of the second accompanying test tubes and the inner side ends of the third accompanying test tubes, and connecting the outer side ends of the third accompanying test tubes with the third ends of the three-way adapter; S2, a dynamic shear test is carried out, namely a pressurizing module is started to inject pressure into a test accompanying tube, when the internal pressure of the test accompanying tube is increased to 0.02Mpa, the time t=0 ms is recorded, the internal pressure is continuously increased, when the internal pressure of the test accompanying tube reaches a first pressure maintaining value, the pressurizing is stopped and the pressure maintaining is continuously carried out, meanwhile, an electric cylinder is started to apply radial thrust to the test accompanying tube, a flexible connecting assembly is subjected to a shear load, when the shear load reaches a preset load value, the electric cylinder is stopped, the electric cylinder is kept to work reversely after a certain period, the shear load is attenuated to zero, after the shear load is reduced to zero, the pressurizing module is closed, and when the internal pressure of the test accompanying tube is attenuated to a low pressure value, the dynamic shear test of the flexible connecting assembly is completed once; s3, repeating the dynamic shearing test in the S2, and checking the flexible connection assembly after every N times of test cycles to judge whether the flexible connection assembly fails, wherein the method specifically comprises the following steps: S31, if the oil leakage quantity of the flexible connecting assembly is less than a leakage quantity threshold value, the damage degree of the flexible connecting assembly is less than a damage threshold value, and the internal pressure of the accompanying test tube is within a specified theoretical value range, continuing to test according to the increase repetition number of S2; S32, if the oil leakage amount of the flexible connection assembly is greater than a leakage amount threshold, or the damage degree of the flexible connection assembly is greater than the damage threshold, or the internal pressure of the accompanying test tube exceeds a specified theoretical value range, the flexible connection assembly fails, and the test is terminated.
4. The method for testing the dynamic shear test device of the flexible connection unit of the fuel system of the aircraft according to claim 3, further comprising S4, analyzing the service life and the change rule of the flexible connection unit.
5. The method for testing the dynamic shear test device for the flexible connection assembly of the aircraft fuel system according to claim 4, wherein in the step S2, the time range when the shear load of the flexible connection assembly is applied to the preset load value from zero is 1000-2000 ms, and when the shear load of the flexible connection assembly is the preset load value and is kept for 100ms, the internal pressure of the accompanying test tube is within 0.86-0.9 MPa.
6. The method of claim 4, wherein the test cycle rate in S3 is less than or equal to 40 cycles/min.
7. The method according to claim 5, wherein the first pressure maintaining value is set to 0.86Mpa in S2, the predetermined load value of the shear load of the flexible connection assembly is 161kg±1kg, and the low pressure value to which the internal pressure of the test tube is attenuated is 0.03 (+0.01/-0.02) Mpa.

Description

Dynamic shearing testing device and testing method for flexible connection assembly of aircraft fuel system Technical Field The invention belongs to the technical field of testing, and particularly relates to a dynamic shear testing device and a testing method for a flexible connection assembly of an aircraft fuel system. Background The flexible connecting component is an important connecting component in the aircraft fuel system and is used for connecting two sections of ducts, so that the sealing effect and the flexible buffering function of the ducts are ensured. The flexible connection unit is required to withstand not only the internal operating pressures created by the flow of fuel, but also external shear loads from the aircraft during operation. In the application process, if the flexible connection assembly fails, not only can fuel leakage possibly cause fire disaster, but also the failure of a flight control system can be caused, other systems and accessories are endangered, and disastrous results are caused. In actual flight conditions, flexible connection units are often in complex and varied environments, and they must have excellent pressure and shear resistance to ensure reliable operation of the fuel system, so testing of the flexible connection units is necessary. Currently, in practical outfield applications of flexible connection units, the experience of engineers is relied on to determine that no more sophisticated testing devices are available. In order to more scientifically and reasonably guide the external field maintenance, maintenance and replacement of new parts of the flexible connecting assembly to provide data support and reference and provide reference basis for designers in the process of selecting the flexible connecting assembly, it is highly required to design a dynamic shearing test device and a dynamic shearing test method for the flexible connecting assembly of the aircraft fuel system so as to develop life test research of the flexible connecting assembly. Disclosure of Invention In order to solve the defects in the prior art, the invention provides a dynamic shearing testing device and a testing method for a flexible connecting assembly of an aircraft fuel system, which are used for connecting two sections of test tubes by using the flexible connecting assembly, pressurizing the interiors of the test tubes by a pressurizing module in a loading assembly, applying radial thrust to the test tubes by utilizing an electric cylinder in a reciprocating assembly, completing the testing of the internal working pressure and the external shearing load which can be borne by the flexible connecting assembly, providing standard equipment and a standard method for developing the life test research of the flexible connecting assembly, and being widely applied to the aerospace field. In order to achieve the above purpose, the invention adopts the following technical scheme: The invention provides a dynamic shearing testing device for a flexible connecting component of an aircraft fuel system, which comprises a reciprocating component, a clamping component and a loading component, wherein a second pushing block in the reciprocating component is connected with a first clamping block in the clamping component, and the loading component is arranged on one side of the clamping component; The reciprocating assembly comprises a base, an electric cylinder mounting seat, an electric cylinder, a first push block, a second push block and an external pressure sensor, wherein the electric cylinder mounting seat is arranged at the first end of the base, the electric cylinder is mounted on the electric cylinder mounting seat, the output end of the electric cylinder penetrates through the electric cylinder mounting seat, the first end of the first push block is connected with the output shaft of the electric cylinder, and the second end of the first push block is connected with the first end of the second push block through the external pressure sensor; The clamping assembly comprises a first clamping block, a second clamping block, an axial limiting block, a lateral pipeline, a sliding rod, a sliding block, a supporting plate, a middle fixing plate and a middle pipeline, wherein the first clamping block is in butt joint with the second clamping block, the lateral pipeline is installed in a round hole formed by the butt joint of the first clamping block and the second clamping block, the axial limiting block is respectively arranged at the joint of the lateral pipeline and the first clamping block and the second clamping block, the supporting plate is arranged at the second end of the base, rectangular sliding grooves are formed in four corners of the supporting plate, the sliding block is installed in the rectangular sliding grooves, the sliding block can slide in the rectangular sliding grooves, the sliding rod sequentially penetrates through slotted holes in the two ends of the first clamping bloc