CN-122009522-A - Bearing test device for tail stay mechanism of transport aircraft

CN122009522ACN 122009522 ACN122009522 ACN 122009522ACN-122009522-A

Abstract

The invention relates to the technical field of airplane component testing, in particular to a bearing test device and a bearing test method for a tail boom mechanism of a transport airplane. The invention ensures that the load is accurately transferred along the vertical direction all the time in the loading process by restraining the double loading directions of the loading oil cylinder and the loading disc assembly, truly reproduces the complex working conditions of axial bearing and course/lateral offset bearing of the tail support mechanism in actual work, provides comprehensive and reliable test support for structural strength evaluation and deflection angle design conformity verification of the tail support mechanism, and further simulates the actual ground working condition by the simulation material in the loading disc assembly, thereby fitting the test working condition more and ensuring the test precision.

Inventors

FENG YUNWEN
HUANG JIASHU
XUE XIAOFENG
Cao Jinfan

Assignees

西北工业大学

Dates

Publication Date: 20260512
Application Date: 20260331

Claims (10)

1. The utility model provides a transportation class aircraft tail prop mechanism bears test device which characterized in that includes: the test bench assembly is horizontally provided with a cross beam; The clamp is detachably arranged on the cross beam, the clamping end of the clamp is vertically downward, and the clamp is used for clamping one end of the tail support mechanism; The loading assembly comprises a base arranged on the test bench assembly, a linear driving assembly is vertically arranged on the base, the output end of the linear driving assembly is connected with a loading disc assembly, the loading disc assembly comprises a loading shell, one end of the loading shell is closed, the closed end of the loading shell is connected with the output end of the driving assembly, a limiting ring flange is arranged at the opening end of the loading shell, a filling cavity is formed between the limiting ring flange and the loading shell and is used for filling simulation materials for simulating ground states, and the filling materials in the filling cavity are used for clamping end contact of the tail support mechanism; the first auxiliary positioning assembly is used for positioning the linear driving assembly in the vertical direction so as to limit the radial movement of the linear driving assembly; a second auxiliary positioning assembly for positioning the loading tray assembly; The load monitoring assembly is used for monitoring the load applied by the loading oil cylinder and the load actually born by the main support of the tail support mechanism in real time; and the displacement monitoring assembly is used for monitoring the telescopic displacement of the linear driving assembly in real time so as to limit the radial movement of the loading disc assembly.
2. The transport aircraft tail boom mechanism load test apparatus of claim 1, wherein the test stand assembly comprises: the test base is provided with two upright posts which are vertically arranged; an inclined support member which is inclined and supported between the test base and the lower part of the upright; wherein, the crossbeam erects in the top of two stands.
3. The bearing test device for the tail boom mechanism of the transportation aircraft according to claim 1, wherein a plurality of groups of positioning holes are formed in the cross beam, the plurality of groups of positioning holes are uniformly distributed along the cross beam, and the positioning holes are used for mounting clamps for adapting test pieces with different specifications.
4. The device for testing the loading of a tail boom mechanism of a transport aircraft according to claim 1, wherein the linear drive assembly comprises a loading cylinder having one end connected to the base and the other end detachably connected to the closed end of the loading housing of the loading tray assembly.
5. The device for testing the bearing capacity of the tail boom mechanism of the transport aircraft according to claim 2, wherein the test base is provided with a mounting base plate, a plurality of groups of mounting holes are formed in the mounting base plate, and each group of mounting holes forms a mounting position for mounting the base.
6. The transportation class aircraft tail boom mechanism load test apparatus of claim 2, wherein the first auxiliary positioning assembly comprises: Four groups of auxiliary upright posts are uniformly distributed on the test base around the base, wherein each group of auxiliary upright posts comprises two auxiliary upright posts, and the two auxiliary upright posts in each group of auxiliary upright posts are sequentially arranged along the radial direction of the linear driving assembly; The plurality of groups of screws are horizontally arranged on the auxiliary upright post along the length direction of the auxiliary upright post; The clamping plate assembly is arranged on the screw in a penetrating mode and locked through the nut, and is used for clamping the periphery of the linear driving assembly.
7. The transport aircraft tail boom mechanism load test device of claim 6, wherein the second auxiliary positioning assembly comprises: the bending-resistant clamp comprises an L-shaped supporting plate which is connected to the opposite surfaces of four groups of auxiliary upright posts through screws; And the cushion block is arranged on the outer peripheral surface of the loading shell, the surface of the cushion block is a plane, and a certain gap is formed between the surface of the cushion block and the surface of the L-shaped supporting plate of the bending-resistant clamp.
8. The load test device for the tail boom mechanism of the transportation type aircraft according to claim 4, wherein the load monitoring assembly comprises two groups of pressure sensors, one group of pressure sensors is arranged between a piston rod of the loading oil cylinder and the loading disc, is coaxially installed and rigidly connected with the piston rod of the loading oil cylinder and the loading disc and is used for monitoring the load applied by the loading oil cylinder in real time, and the other group of pressure sensors are integrated in the clamp and are used for monitoring the load actually born by the main support of the tail boom mechanism.
9. The device for testing the bearing capacity of the tail boom mechanism of the transport aircraft according to claim 4, wherein the displacement monitoring assembly comprises a displacement sensor, the displacement sensor is axially arranged along the cylinder body of the loading cylinder, and the detection end of the displacement sensor is rigidly connected with the tail end of the piston rod of the loading cylinder.
10. A method for carrying out a load test on a tail boom mechanism of a transport aircraft, characterized by adopting the load test device for the tail boom mechanism of the transport aircraft according to any one of claims 1 to 9, comprising the following test steps: The test preparation comprises checking the connection state of the test bed and each component, ensuring the connection to be firm and the components not to be damaged, connecting the loading oil cylinder with an external hydraulic control system, and calibrating the pressure sensor and the displacement sensor; the test piece clamping, namely connecting the fixed end of the tail support mechanism with a test piece fixing clamp, adjusting the clamping interval of the clamp and locking a bolt, so as to ensure that the clamping of the tail support mechanism is stable and the axis of the tail support mechanism is consistent with the loading direction; The loading position adjustment, namely loosening a fixed bolt of a base of a loading oil cylinder and a mounting bottom plate according to a deflection working condition required to be simulated in a test, and adjusting the course and the lateral mounting position of the base of the loading oil cylinder on the mounting bottom plate by utilizing a plurality of groups of mounting holes preset on the surface of the mounting bottom plate, so that the relative position of the base and the mounting bottom plate is fixed after the center of a loading disc assembly is aligned with the deflection position of a tail support mechanism; adjusting the position of an auxiliary upright post to enable the clamping plates at two sides to be attached to the cylinder body of the loading cylinder and clamped, and adjusting the L-shaped supporting plate of the bending-resistant clamp to ensure that a preset gap is kept between the L-shaped supporting plate and the periphery of the loading shell; The load application and monitoring comprises the steps of starting an external hydraulic control system, inputting hydraulic oil to a loading oil cylinder according to a preset loading mode, and applying vertical upward axial load to a tail support mechanism through a loading disc assembly; After the test is finished, slowly unloading the load, retracting a piston rod of the loading oil cylinder, loosening a clamp of the tail support mechanism, taking down the tail support mechanism, finishing test data and closing the control system.

Description

Bearing test device for tail stay mechanism of transport aircraft Technical Field The invention relates to the technical field of airplane component testing, in particular to a bearing test device and a test method for a tail stay mechanism of a transport airplane. Background The tail stay mechanism is a key safety device of a transportation type aircraft with a rear cargo compartment door, is usually arranged near the rear cargo compartment door of the rear part of the aircraft body or at the rear sections of landing gear cabins at two sides, and is a hydraulic support structure with a retraction function. The tail stay component of the part of the light and small transport aircraft also has the jack function and is used for assisting the maintenance operation of the landing gear. The tail support mechanism is required to bear cargo load in the loading and unloading process and course and lateral offset load generated by random body offset in service, the working condition is severe, and the difference of different airplanes in the aspects of task requirements, structural configuration and the like is obvious, so that the design of the tail support mechanism is highly customized. Therefore, the actual bearing stress state of the tail stay mechanism is complex, the actual bearing stress state is difficult to accurately simulate only through theoretical calculation, if the bearing performance does not reach the standard, faults such as stay bar retraction, pressure relief and structural fracture are easily caused, and whether the tail stay mechanism meets the design index requirement needs to be verified through experiments. Therefore, it is desirable to provide a carrier class aircraft tail boom mechanism load test apparatus to address the above-mentioned issues. Disclosure of Invention Aiming at the problems that the actual bearing stress state of a tail stay mechanism in the prior art is complex and difficult to accurately simulate only through theoretical calculation, if the bearing performance does not reach the standard, the faults of stay rod retraction, pressure relief and structural fracture are easy to cause, and whether the tail stay mechanism meets the design index requirement needs to be verified through experiments, the invention provides a bearing test device for a transport aircraft tail stay mechanism, which realizes the accurate simulation of complex working conditions of axial bearing and course/lateral deflection bearing of the tail stay mechanism and provides a reliable test for verifying the structural strength, bearing stability and deflection angle design compliance of the tail stay mechanism so as to solve the existing problems. The first aspect of the invention provides a bearing test device for a tail boom mechanism of a transport aircraft, which adopts the following technical scheme that: the test bench assembly is horizontally provided with a cross beam; The clamp is detachably arranged on the cross beam, the clamping end of the clamp is vertically downward, and the clamp is used for clamping one end of the tail support mechanism; The loading assembly comprises a base arranged on the test bench assembly, a linear driving assembly is vertically arranged on the base, the output end of the linear driving assembly is connected with a loading disc assembly, the loading disc assembly comprises a loading shell, one end of the loading shell is closed, the closed end of the loading shell is connected with the output end of the driving assembly, a limiting ring flange is arranged at the opening end of the loading shell, a filling cavity is formed between the limiting ring flange and the loading shell and is used for filling simulation materials for simulating ground states, and the filling materials in the filling cavity are used for clamping end contact of the tail support mechanism; the first auxiliary positioning assembly is used for positioning the linear driving assembly in the vertical direction so as to limit the radial movement of the linear driving assembly; a second auxiliary positioning assembly for positioning the loading tray assembly; The load monitoring assembly is used for monitoring the load applied by the loading oil cylinder and the load actually born by the main support of the tail support mechanism in real time; and the displacement monitoring assembly is used for monitoring the telescopic displacement of the linear driving assembly in real time so as to limit the radial movement of the loading disc assembly. The invention further provides a test bench assembly comprising: the test base is provided with two upright posts which are vertically arranged; an inclined support member which is inclined and supported between the test base and the lower part of the upright; wherein, the crossbeam erects in the top of two stands. According to the technical scheme, a plurality of groups of positioning holes are formed in the cross beam, the plurality of groups of positioning hole