A testing device and system for testing the deflection of an aircraft landing gear folding strut.

Abstract

This utility model discloses a testing device and system for testing the deflection of an aircraft landing gear folding strut. The testing device includes a first connecting block, a pressure-displacement sensor, a sleeve, a second connecting block, a first connecting rod, and a second connecting rod. The pressure-displacement sensor is disposed on the first connecting block, the first connecting rod, the sleeve, the second connecting rod, or the second connecting block. Both ends of the first and second connecting rods are provided with external threads, and both ends of the sleeve are respectively threaded to the first and second connecting rods. One end of the first connecting block is provided with a first connecting portion, and the other end of the first connecting block is threaded to the first connecting rod. One end of the second connecting block is provided with a second connecting portion, and the other end of the second connecting block is threaded to the second connecting rod. The testing device of this utility model solves the technical problem in the prior art where the deflection test of the folding strut and the elasticity test of the spring actuator cannot be performed simultaneously, resulting in low assembly efficiency.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft landing gear assembly and testing technology, specifically relating to an aircraft landing gear folding strut deflection testing device and its testing system. Background Technology

[0002] Aircraft landing gear is a crucial component of an aircraft, and its performance directly affects the aircraft's safety and reliability. The folding strut, as a key component of the landing gear, is primarily used to support and adjust the landing gear's retraction and extension movements. A folding strut typically consists of two parts: the strut body and a spring actuator. The strut body has a first connecting end and a second connecting end, and the two ends of the spring actuator are connected to the first and second connecting ends, respectively. The spring actuator provides elastic support force, while the strut body bears the main mechanical load.

[0003] The assembly of the folding strut structure is a complex and critical step in the aircraft landing gear assembly process. During assembly, the spring actuator needs to undergo elasticity testing to ensure its elastic performance meets design requirements; simultaneously, the folding strut needs to undergo deflection testing to verify its strength and safety standards under load. In traditional assembly processes, these two testing steps are performed separately: the spring actuator elasticity test is completed first, followed by the folding strut deflection test. During the deflection test, a load is applied to one or both ends of the strut, and a force sensor measures the load-bearing capacity, while a dial gauge measures the displacement, thus obtaining the load-bearing capacity and displacement changes. This separate testing method suffers from problems such as long assembly cycles, low production efficiency, and increased labor and equipment costs. Utility Model Content

[0004] In view of the existing technical problems, this utility model aims to provide an aircraft landing gear folding strut deflection testing device and its testing system. This testing device can solve the technical problem that the deflection test of the folding strut and the elasticity test of the spring actuator cannot be performed simultaneously in the prior art, resulting in low assembly efficiency.

[0005] To achieve the above objectives, the technical solution adopted by this utility model is as follows:

[0006] A device for testing the deflection of an aircraft landing gear folding strut, characterized by the following structure: It includes a first connecting block, a pressure-displacement sensor, a sleeve, a second connecting block, a first connecting rod disposed between the first connecting block and the sleeve, and a second connecting rod disposed between the sleeve and the second connecting block. The pressure-displacement sensor is disposed on the first connecting block, the first connecting rod, the sleeve, the second connecting rod, or the second connecting block. Both ends of the first and second connecting rods are provided with external threads, and both ends of the sleeve are respectively threaded to the first and second connecting rods. One end of the first connecting block is provided with a first connecting portion, which is detachably and fixedly connected to the first connecting end of the strut body on the folding strut. The other end of the first connecting block along its length is threaded to the first connecting rod. One end of the second connecting block is provided with a second connecting portion, which is detachably and fixedly connected to the second connecting end of the strut body on the folding strut. The other end of the second connecting block along its length is threaded to the second connecting rod.

[0007] The pressure displacement sensor used in this application is a product of existing technology. This pressure sensor can simultaneously measure displacement and pressure, such as the integrated pressure displacement sensor disclosed in Chinese Utility Model Patent Publication No. CN207515841U. When using the testing device in this application, the testing device is installed at both ends of the support rod body to replace the spring actuator. The first connecting part is connected to the first connecting end of the support rod body, and the second connecting part is connected to the second connecting end of the support rod body. The gap between the testing device and the support rod body is adjusted using the first connecting rod, sleeve, and second connecting rod to match the characteristics of the actual spring actuator, thus meeting the installation requirements of different models of folding support rods. The pressure displacement sensor is used to detect stress and displacement changes in real time during the deflection test, obtaining deflection test data. After completing the deflection test, the testing device is disassembled, and the actual spring actuator is installed. The aircraft landing gear folding strut deflection testing device of this application can replace the spring actuator to provide support force during the deflection test, and free the spring actuator during the strut deflection test. This allows the folding strut deflection test and the spring actuator elasticity test to be carried out simultaneously in steps, which can significantly shorten the assembly cycle and improve production efficiency.

[0008] Specifically, a first nut is provided on the end of the first connecting rod near the first connecting block. The first nut is threadedly connected to the first connecting rod and abuts against the first connecting block. The pressure displacement sensor is fixed on the end of the first connecting rod near the sleeve and abuts against the sleeve. The first nut secures the thread between the first connecting block and the first connecting rod, and the pressure displacement sensor secures the thread between the first connecting rod and the sleeve. The gap between the testing device and the support rod body is adjusted by rotating the second connecting rod.

[0009] Specifically, each end of the second connecting rod is provided with a second nut, and both second nuts are threadedly connected to the second connecting rod. The two second nuts abut against the sleeve and the second connecting block, respectively. The threads between the second connecting rod and the sleeve, and between the second connecting rod and the second connecting block, are fixed by the two second nuts.

[0010] Preferably, the first connecting part is a V-shaped slot structure, which is used to engage with the first connecting end. By setting the V-shaped slot structure, it is easy to fix the first connecting part to the first connecting end and to quickly disassemble it, so as to quickly replace it with the actual spring actuator after the test is completed.

[0011] Preferably, the second connecting part has a V-shaped groove structure, which is used to engage with the second connecting end. By setting the V-shaped groove structure, it is easy to fix the second connecting part to the second connecting end and to quickly disassemble it, so as to quickly replace it with the actual spring actuator after the test is completed.

[0012] Preferably, the pressure displacement sensor is electrically connected to the data acquisition system. The data acquisition system can collect and record data during the testing process in real time, providing a reference for subsequent assembly.

[0013] Preferably, the axial center lines of the first connecting block, the first connecting rod, the sleeve, the second connecting rod, and the second connecting block are located on the same straight line.

[0014] Based on the same inventive concept, this application also provides an aircraft landing gear folding strut deflection testing system, including a strut body and a spring actuator, wherein the strut body is provided with a first connecting end and a second connecting end; it also includes the aircraft landing gear folding strut deflection testing device as described above, wherein the length of the testing device matches the length of the spring actuator; the first connecting end is detachably and fixedly connected to the first connecting part, and the second connecting end is detachably and fixedly connected to the second connecting part.

[0015] Specifically, when the spring actuator is installed on the support rod body, the straight line containing the axial center line of the spring actuator coincides with the axial center line of the test device.

[0016] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0017] 1. The landing gear folding strut deflection testing device of this utility model can replace the spring actuator to provide support force during the strut deflection test and complete the folding strut deflection test.

[0018] 2. The landing gear folding strut deflection testing device of this utility model releases the spring actuator during the strut deflection test, thereby enabling the spring actuator elasticity test to be performed simultaneously during the strut deflection test, which significantly shortens the assembly cycle and improves production efficiency.

[0019] 3. The landing gear folding strut deflection testing device of this utility model has a simple structure and is easy to operate. It can be widely used in the assembly testing of landing gear folding struts of various aircraft models. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the landing gear folding strut deflection testing device of this utility model;

[0021] Figure 2 This is a schematic diagram of the landing gear folding strut deflection testing system of this utility model.

[0022] In the figure

[0023] 1-First connecting block; 101-First connecting part; 2-First nut; 3-First connecting rod; 4-Pressure displacement sensor; 5-Sleeve; 6-Second nut; 7-Second connecting rod; 8-Second connecting block; 801-Second connecting part; 9-Data acquisition system; 10-Support rod body; 1001-First connecting end; 1002-Second connecting end. Detailed Implementation

[0024] The present invention will be described in detail below with reference to the accompanying drawings and embodiments. It should be noted that, unless otherwise specified, the embodiments and features described in the embodiments of the present invention can be combined with each other. For ease of description, the terms "upper," "lower," "left," and "right" appearing below only indicate that they correspond to the upper, lower, left, and right directions in the accompanying drawings and do not limit the structure.

[0025] like Figure 1As shown, the aircraft landing gear folding strut deflection testing device of this embodiment includes a first connecting block 1, a pressure displacement sensor 4, a sleeve 5, a second connecting block 8, a first connecting rod 3 disposed between the first connecting block 1 and the sleeve 5, a second connecting rod 7 disposed between the sleeve 5 and the second connecting block 8, and a data acquisition system 9. The pressure displacement sensor 4 is electrically connected to the data acquisition system 9. Both ends of the first connecting rod 3 and the second connecting rod 7 are provided with external threads, and both ends of the sleeve 5 are respectively connected to the first connecting rod 3 and the second connecting rod 7 by threads. The pressure displacement sensor 4 is fixed on the first connecting rod 1 near one end of the sleeve 5, and the pressure displacement sensor 4 abuts against the sleeve 5. The length of the first connecting block 1 is 45mm, and one end of the first connecting block 1 is provided with a first connecting part 101. The first connecting part 101 adopts a V-shaped groove structure with an inscribed circle diameter of 20mm. The V-shaped groove is used to engage with the first connecting end 1001 of the strut body 10 on the folding strut. The other end of the first connecting block 1 along its length is threaded to the first connecting rod 3. A first nut 2, which is a hexagonal nut, is provided on the end of the first connecting rod 3 near the first connecting block 1. The first nut 2 is threaded to the first connecting rod 1 and abuts against the first connecting block 1. The second connecting block 8 is 50mm long. One end of the second connecting block 8 is provided with a second connecting portion 801, which adopts a V-shaped groove structure with an inscribed circle diameter of 12mm. This V-shaped groove is used to engage with the second connecting end 1002 of the support body 10 on the folding support rod. The other end of the second connecting block 8 along its length is threaded to the second connecting rod 7. Both ends of the second connecting rod 7 are provided with second nuts 6, both of which are threaded to the second connecting rod 7 and abut against the sleeve 5 and the second connecting block 8, respectively. The axial center lines of the first connecting block 1, the first connecting rod 3, the sleeve 5, the second connecting rod 7, and the second connecting block 8 are located on the same straight line.

[0026] This embodiment also provides an aircraft landing gear folding strut deflection testing system, including a strut body 10, a spring actuator, and the aircraft landing gear folding strut deflection testing device described above. The strut body 10 is provided with a first connecting end 1001 and a second connecting end 1002. The length of the testing device matches the length of the spring actuator. The first connecting end 1001 is detachably and fixedly connected to the first connecting part 101, and the second connecting end 1002 is detachably and fixedly connected to the second connecting part 801. When the spring actuator is installed on the strut body 10, the straight line containing the axial center line of the spring actuator coincides with the axial center line of the testing device.

[0027] In this embodiment, the testing device is installed at both ends of the support rod body 10 to replace the spring actuator. The first connecting part 101 is engaged with the first connecting end 1001 of the support rod body 10, and the second connecting part 801 is engaged with the second connecting end 1002 of the support rod body 10. The gap between the testing device and the support rod body 10 is adjusted using the second connecting rod 7 to match the characteristics of the actual spring actuator, thus meeting the installation requirements of different models of folding support rods. The pressure displacement sensor 4 is used to detect stress and displacement changes in real time during the deflection test, obtaining deflection test data. After the deflection test is completed, the testing device is disassembled, and the actual spring actuator is installed. Because this testing device can replace the spring actuator in testing the support characteristics during the deflection test, the spring actuator can be freed up for elasticity testing during the deflection test, allowing the two assembly tests to be performed simultaneously, greatly shortening assembly time and improving production efficiency.

[0028] The above embodiments should be understood as being used only to illustrate the utility model more clearly, and not to limit the scope of the utility model. After reading this utility model, any modifications of the embodiments by those skilled in the art in various equivalent forms fall within the scope defined by the appended claims.

Claims

1. A device for testing the deflection of an aircraft landing gear folding strut, characterized in that: It includes a first connecting block (1), a pressure displacement sensor (4), a sleeve (5), a second connecting block (8), a first connecting rod (3) disposed between the first connecting block (1) and the sleeve (5), and a second connecting rod (7) disposed between the sleeve (5) and the second connecting block (8). The pressure displacement sensor (4) is disposed on the first connecting block (1) or the first connecting rod (3) or the sleeve (5) or the second connecting rod (7) or the second connecting block (8). Both ends of the first connecting rod (3) and the second connecting rod (7) are provided with external threads, and both ends of the sleeve (5) are respectively connected to the first connecting rod (3) and the second connecting rod (7) by threads; One end of the first connecting block (1) is provided with a first connecting part (101), which is used to be detachably and fixedly connected to the first connecting end (1001) of the main body (10) of the folding support rod. The other end of the first connecting block (1) along the length direction is connected to the first connecting rod (3) by a thread. One end of the second connecting block (8) is provided with a second connecting part (801), which is used to be detachably and fixedly connected to the second connecting end (1002) of the main body (10) of the folding support rod. The other end of the second connecting block (8) along the length direction is connected to the second connecting rod (7) by a thread.

2. The aircraft landing gear folding strut deflection testing device according to claim 1, characterized in that: The first connecting rod (3) is provided with a first nut (2) at one end near the first connecting block (1). The first nut (2) is connected to the first connecting rod (1) by a thread, and the first nut (2) abuts against the first connecting block (1). The pressure displacement sensor (4) is fixed on the first connecting rod (1) at one end near the sleeve (5), and the pressure displacement sensor (4) abuts against the sleeve (5).

3. The aircraft landing gear folding strut deflection testing device according to claim 2, characterized in that: The second connecting rod (7) has a second nut (6) at both ends. The two second nuts (6) are connected to the second connecting rod (7) by threads. The two second nuts (6) abut against the sleeve (5) and the second connecting block (8) respectively.

4. The aircraft landing gear folding strut deflection testing device according to claim 1, characterized in that: The first connecting part (101) is a V-shaped slot structure, which is used to engage with the first connecting end (1001).

5. The aircraft landing gear folding strut deflection testing device according to claim 1, characterized in that: The second connecting part (801) is a V-shaped slot structure, which is used to engage with the second connecting end (1002).

6. The aircraft landing gear folding strut deflection testing device according to claim 1, characterized in that: The pressure displacement sensor (4) is electrically connected to the data acquisition system (9).

7. The aircraft landing gear folding strut deflection testing device according to claim 1, characterized in that: The axial center lines of the first connecting block (1), the first connecting rod (3), the sleeve (5), the second connecting rod (7), and the second connecting block (8) are located on the same straight line.

8. A deflection testing system for an aircraft landing gear folding strut, comprising a strut body (10) and a spring actuator, wherein the strut body (10) is provided with a first connecting end (1001) and a second connecting end (1002); characterized in that: It also includes an aircraft landing gear folding strut deflection testing device as described in any one of claims 1 to 7, wherein the length of the testing device matches the length of the spring actuator; the first connecting end (1001) is detachably and fixedly connected to the first connecting part (101), and the second connecting end (1002) is detachably and fixedly connected to the second connecting part (801).

9. The aircraft landing gear folding strut deflection testing system according to claim 8, characterized in that: When the spring actuator is installed on the support rod body (10), the straight line containing the axial center line of the spring actuator coincides with the axial center line of the test device.

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