Static test device for aircraft kitchen trolley

Abstract

A static test device for an aircraft kitchen trolley relates to the field of aircraft part tests and comprises a rack, limiting blocks are arranged on the left side and the right side in the rack respectively, the aircraft kitchen trolley is located in the rack, and the left end and the right end of the aircraft kitchen trolley are limited through the limiting blocks arranged on the same side respectively; the mounting base I is arranged at the side end of the rack, and a force applying mechanism I for applying pressure to the side face of the aircraft kitchen trolley is arranged on the mounting base I; the mounting seat II is arranged at the front end of the rack, and a force applying mechanism II for applying pulling force to the rear end of the airplane kitchen trolley is arranged on the mounting seat II; and the longitudinal limiting mechanism is arranged in the rack and used for limiting the front end of the aircraft kitchen trolley. The device can adapt to various types of trolleys and various working conditions and load directions, and is high in universality.

Description

Technical Field

[0001] The utility model relates to the field of aircraft component tests, and particularly to a static test device for an aircraft galley trolley. Background Art

[0002] The main function of the trolley is to transport and store various cabin service items (drinks, food, goods, and garbage) in the aircraft cabin. Trolleys are mainly divided into full-size trolleys and half-size trolleys. There will be certain differences in the appearance dimensions and center of gravity positions of trolleys produced by different manufacturers. The structure of the trolley should consider the maximum load in each direction. The test load should be greater than or equal to the value obtained by multiplying the weights of the items, the unloaded structure, and the adjacent equipment at their respective center of gravity positions by the respective limit load factors in their respective load directions. For material deviations, an overload factor of 1.15 should be multiplied, and for connectors, a local connector factor of 1.33 should be multiplied. The test load application time should be at least 3 seconds. The size of the test plate used to simulate the load on the equipment should not exceed 75% of the possible load area, and the stiffness of the test plate should be less than or equal to the stiffness of the load-bearing equipment panel. In the case of the ultimate load, no failure should occur; in the case of the limit load, no harmful permanent deformation should occur.

[0003] The load directions include forward loading, backward loading, lateral loading, downward loading, and upward loading. The loading conditions include the main restraint action of the test equipment with the door lock open; the secondary restraint action of the test equipment with the door lock closed; a 100% cargo load, simulating a loaded drawer, acting on the door; a 60% cargo load, simulating loose items, acting on the door; and the total load acting on the trolley structure frame.

[0004] Currently, a static test of the trolley uses a test device with a fixed position, and then fixed tooling is made according to the calculated center of gravity positions under various conditions for necessary restraint. Because static tests need to be carried out under different conditions and different load directions, it is necessary to switch the tension sensor and the thrust sensor, and the fixing device also needs to be adjusted timely. This not only affects the test efficiency but also cannot guarantee the stability of the test device and the reliability of the test results. Summary of the Invention

[0005] The utility model provides a device that can complete the static tests in two dimensions of thrust and tension of an aircraft galley trolley with one-time fixing to overcome the above-mentioned deficiencies in technology.

[0006] The technical solution adopted by the utility model to overcome its technical problems is:

[0007] A static test device for an aircraft galley trolley, comprising:

[0008] A frame, with limiting blocks respectively arranged on the left and right sides inside it. An aircraft galley cart is located in the frame, and its left and right ends are respectively limited by the limiting blocks arranged on the same side.

[0009] Mounting seat I, arranged at the side end of the frame. A force-applying mechanism I for applying pressure to the side surface of the aircraft galley cart is arranged on the mounting seat I.

[0010] Mounting seat II, arranged at the front end of the frame. A force-applying mechanism II for applying a pulling force to the rear end of the aircraft galley cart is arranged on the mounting seat II; and

[0011] A longitudinal limiting mechanism, arranged in the frame, for limiting the front end of the aircraft galley cart.

[0012] Furthermore, the above longitudinal limiting mechanism includes a main constraint limiter arranged at the upper end of the frame and a secondary constraint limiter arranged at the lower end of the frame. The front end of the aircraft galley cart is in contact with the main constraint limiter and the secondary constraint limiter.

[0013] Furthermore, the above force-applying mechanism I includes an oil cylinder I mounted on the mounting seat I, a pressure sensor, and a screw rod II horizontally arranged in the left-right direction. The axis of the oil cylinder I is horizontally arranged in the left-right direction. One end of the pressure sensor is connected to the head end of the piston rod of the oil cylinder I through a swivel joint II, and the other end is connected to the head end of the screw rod II through a swivel joint IV. The rear end face of the test plate II is in contact with the side end face of the aircraft galley cart, the rear end face of the spacer block II is in contact with the test plate II, and the tail end of the screw rod II sequentially passes through the spacer block II, the test plate II, the side end face of the aircraft galley cart and is locked by a nut II.

[0014] Furthermore, the above force-applying mechanism II includes an oil cylinder II mounted on the mounting seat II, a tension sensor, and a screw rod I horizontally arranged in the front-rear direction. The axis of the oil cylinder II is horizontally arranged in the front-rear direction. One end of the tension sensor is connected to the head end of the piston rod of the oil cylinder II through a swivel joint I, and the other end is connected to the head end of the screw rod I through a swivel joint III. The rear end face of the test plate I is in contact with the rear end face of the aircraft galley cart, the rear end face of the spacer block I is in contact with the test plate I, and the tail end of the screw rod I sequentially passes through the rear end face of the aircraft galley cart, the test plate I, the spacer block I and is locked by a nut I.

[0015] Furthermore, it further includes a height adjustment mechanism arranged in the mounting seat I and the mounting seat II. The mounting seat I and the mounting seat II adjust their horizontal heights through the height adjustment mechanism.

[0016] Further, the height adjustment mechanism includes a linear guide rail vertically installed on the frame, and a screw rod rotatably installed in mounting seat I or mounting seat II. The axis of the screw rod is arranged vertically. Mounting seat I or mounting seat II is installed on the guide rail slider of the linear guide rail. A support seat is installed at the lower end of the screw rod, and the lower end surface of the support seat contacts the ground.

[0017] The beneficial effects of the present utility model are as follows: It can adapt to various models of trolleys, various working conditions and load directions, with strong versatility. The aircraft galley trolley can achieve the tests of tensile force and pressure in one limit setting, without the need to disassemble precision equipment such as tensile sensors and thrust sensors, improving the test quality, enabling convenient use under different working conditions and different load directions, and the fixation and restraint of the trolley are simple, saving labor and material costs. Brief Description of the Drawings

[0018] Figure 1 is the three-dimensional structure diagram of the present utility model;

[0019] Figure 2 is the structure diagram of the aircraft galley trolley of the present utility model pushed into the frame;

[0020] Figure 3 is the structure diagram of the cylinder I part of the present utility model;

[0021] Figure 4 is the structure diagram of the cylinder II part of the present utility model;

[0022] Figure 5 is the structure diagram of the screw rod I part of the present utility model;

[0023] Figure 6 is the structure diagram of the screw rod II part of the present utility model;

[0024] Figure 7 is the structure diagram of the support seat part of the present utility model;

[0025] Figure 8 is the structure diagram of the main constraint limiter and secondary constraint limiter parts of the present utility model;

[0026] In the figure, 1. Frame; 2. Aircraft galley trolley; 3. Mounting seat I; 4. Cylinder I; 5. Mounting seat II; 6. Cylinder II; 7. Tensile sensor; 8. Main constraint limiter; 9. Secondary constraint limiter; 10. Adapter I; 11. Adapter II; 12. Pressure sensor; 13. Screw rod I; 14. Test plate I; 15. Spacer I; 16. Nut I; 17. Adapter III; 18. Screw rod II; 19. Test plate II; 20. Spacer II; 21. Nut II; 22. Adapter IV; 23. Screw rod; 24. Support seat; 25. Limit block; 26. Linear guide rail. Detailed Implementation Modes

[0027] The following will further describe the present utility model in conjunction with the appended Figure 1 drawings to Figure 8

[0028] A static test device for an aircraft galley trolley, comprising: a frame 1, with limiting blocks 25 respectively arranged on the left and right sides inside it. The aircraft galley trolley 2 is located in the frame 1, and its left and right ends are respectively limited by the limiting blocks 25 arranged on the same side; a mounting seat I 3, arranged at the side end of the frame 1, and a force-applying mechanism I for applying pressure to the side surface of the aircraft galley trolley 2 is arranged on the mounting seat I 3; a mounting seat II 5, arranged at the front end of the frame 1, and a force-applying mechanism II for applying a pulling force to the rear end of the aircraft galley trolley 2 is arranged on the mounting seat II 5; and a longitudinal limiting mechanism, arranged in the frame 1, for limiting the front end of the aircraft galley trolley 2. After the aircraft galley trolley 2 is moved into the frame 1, its left and right sides are respectively limited by the limiting blocks 25, and its front end is limited by the longitudinal limiting mechanism. Then, the force-applying mechanism I acts to apply pressure to the side surface of the aircraft galley trolley 2, and the force-applying mechanism II acts to apply a pulling force to the rear end of the aircraft galley trolley 2. The structure is simple and no additional special equipment needs to be added. It can adapt to various types of trolleys, various working conditions and load directions, and has strong versatility. The aircraft galley trolley 2 can achieve the tests of pulling force and pressure with one-time limiting, without the need to disassemble precision equipment such as pulling force sensors and thrust sensors, improving the test quality, enabling convenient use under different working conditions and different load directions, with simple fixing and restraint of the trolley, saving labor and material costs.

[0029] In an embodiment of the present utility model, the longitudinal limiting mechanism includes a main restraint limiter 8 arranged at the upper end of the frame 1 and a secondary restraint limiter 9 arranged at the lower end of the frame 1. The front end of the aircraft galley trolley 2 is in contact with the main restraint limiter 8 and the secondary restraint limiter 9. The main restraint limiter 8 and the secondary restraint limiter 9 are the same components as the main restraint limiter 8 and the secondary restraint limiter 9 for storing the position of the aircraft galley trolley 2 in the aircraft cabin, realizing the limitation of the front and rear positions of the aircraft galley trolley 2 and simulating the actual use environment of the aircraft galley trolley 2.

[0030] ​In an embodiment of the present utility model, the force application mechanism I may have the following structure. It includes an oil cylinder I 4 installed on the mounting seat I 3, a pressure sensor 12, and a screw rod II 18 horizontally arranged in the left-right direction. The axis of the oil cylinder I 4 is horizontally arranged in the left-right direction. One end of the pressure sensor 12 is connected to the head end of the piston rod of the oil cylinder I 4 through an adapter II 11, and the other end is connected to the head end of the screw rod II 18 through an adapter IV 22. The rear end face of the test plate II 19 is in contact with the side end face of the aircraft galley cart 2, and the rear end face of the spacer II 20 is in contact with the test plate II 19. The tail end of the screw rod II 18 passes through the spacer II 20, the test plate II 19, and the side end face of the aircraft galley cart 2 in sequence and is locked by a nut II 21. When the piston rod of the oil cylinder I 4 extends outwards, it applies pressure to the side end face of the aircraft galley cart 2 through the screw rod II 18 via the spacer II 20 and the test plate II 19, and the pressure value can be read through the pressure sensor 12.

[0031] In an embodiment of the present utility model, the force application mechanism II may have the following structure. It includes an oil cylinder II 6 installed on the mounting seat II 5, a tension sensor 7, and a screw rod I 13 horizontally arranged in the front-rear direction. The axis of the oil cylinder II 6 is horizontally arranged in the front-rear direction. One end of the tension sensor 7 is connected to the head end of the piston rod of the oil cylinder II 6 through an adapter I 10, and the other end is connected to the head end of the screw rod I 13 through an adapter III 17. The rear end face of the test plate I 14 is in contact with the rear end face of the aircraft galley cart 2, and the rear end face of the spacer I 15 is in contact with the test plate I 14. The tail end of the screw rod I 13 passes through the rear end face of the aircraft galley cart 2, the test plate I 14, and the spacer I 15 in sequence and is locked by a nut I 16. When the piston rod of the oil cylinder II 6 retracts inwards, it applies a tensile force to the rear end face of the aircraft galley cart 2 through the screw rod I 13 via the spacer I 15 and the test plate I 14, and the tensile force value can be read through the tension sensor 7.

[0032] Since holes are drilled in the aircraft galley cart 2 according to the central position for inserting the screw rod I 13 or the screw rod II 18 before the test, a height adjustment mechanism is also included in the mounting seat I 3 and the mounting seat II 5. The mounting seat I 3 and the mounting seat II 5 adjust their horizontal heights through the height adjustment mechanism. Adjusting the heights of the mounting seat I 3 and the mounting seat II 5 through the height adjustment mechanism can ensure that the drilling positions are flush with the axes of the oil cylinder I 4 or the oil cylinder II 6, making the screw rod II 18 coaxially connected with the oil cylinder I 4 and the screw rod I 13 coaxially connected with the oil cylinder II 6, improving the reliability of use.

[0033] In this embodiment, the height adjustment mechanism includes a linear guide rail 26 vertically installed on the frame 1, and a screw rod 23 rotatably installed in the mounting base I 3 or the mounting base II 5. The axis of the screw rod 23 is arranged vertically. The mounting base I 3 or the mounting base II 5 is installed on the guide rail slider of the linear guide rail 26. A support base 24 is installed at the lower end of the screw rod 23, and the lower end surface of the support base 24 is in contact with the ground. Rotating the screw rod 23 can make it move up and down along the axis, thereby driving the mounting base I 3 or the mounting base II 5 to move up and down under the guidance of the linear guide rail 26.

[0034] Finally, it should be noted that the above are only the preferred embodiments of the present invention and are not used to limit the present invention. Although the present invention has been described in detail with reference to the foregoing embodiments, for those skilled in the art, they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A static test device for an aircraft galley trolley, characterized in that, Comprising: A frame (1), with limiting blocks (25) respectively arranged on the left and right sides inside it. The aircraft galley cart (2) is located in the frame (1), and its left and right ends are respectively limited by the limiting blocks (25) arranged on the same side; A mounting seat I (3), arranged at the side end of the frame (1), and a force-applying mechanism I for applying pressure to the side surface of the aircraft galley cart (2) is arranged on the mounting seat I (3); A mounting seat II (5), arranged at the front end of the frame (1), and a force-applying mechanism II for applying a pulling force to the rear end of the aircraft galley cart (2) is arranged on the mounting seat II (5); and A longitudinal limiting mechanism, arranged in the frame (1), for limiting the front end of the aircraft galley cart (2).

2. The static test device for an aircraft galley trolley according to claim 1, characterized in that: The longitudinal limiting mechanism includes a main constraint limiter (8) arranged at the upper end of the frame (1) and a secondary constraint limiter (9) arranged at the lower end of the frame (1). The front end of the aircraft galley cart (2) is in contact with the main constraint limiter (8) and the secondary constraint limiter (9).

3. The static test device for an aircraft galley trolley according to claim 1, characterized in that: The force-applying mechanism I includes an oil cylinder I (4) installed on the mounting seat I (3), a pressure sensor (12), and a screw rod II (18) horizontally arranged in the left-right direction. The axis of the oil cylinder I (4) is horizontally arranged in the left-right direction. One end of the pressure sensor (12) is connected to the head end of the piston rod of the oil cylinder I (4) through a swivel joint II (11), and the other end is connected to the head end of the screw rod II (18) through a swivel joint IV (22). The rear end face of the test plate II (19) is in contact with the side end face of the aircraft galley cart (2), the rear end face of the spacer block II (20) is in contact with the test plate II (19), and the tail end of the screw rod II (18) sequentially passes through the spacer block II (20), the test plate II (19), the side end face of the aircraft galley cart (2) and is locked by a nut II (21).

4. The static test device for an aircraft galley trolley according to claim 1, wherein: The force-applying mechanism II includes an oil cylinder II (6) installed on the mounting seat II (5), a tension sensor (7), and a screw rod I (13) horizontally arranged in the front-rear direction. The axis of the oil cylinder II (6) is horizontally arranged in the front-rear direction. One end of the tension sensor (7) is connected to the head end of the piston rod of the oil cylinder II (6) through a swivel joint I (10), and the other end is connected to the head end of the screw rod I (13) through a swivel joint III (17). The rear end face of the test plate I (14) is in contact with the rear end face of the aircraft galley cart (2), the rear end face of the spacer block I (15) is in contact with the test plate I (14), and the tail end of the screw rod I (13) sequentially passes through the rear end face of the aircraft galley cart (2), the test plate I (14), the spacer block I (15) and is locked by a nut I (16).

5. The static test device for an aircraft galley trolley according to claim 1, characterized in that: It further includes a height adjustment mechanism arranged in the mounting seat I (3) and the mounting seat II (5), and the mounting seat I (3) and the mounting seat II (5) adjust their horizontal heights through the height adjustment mechanism.

6. The static test device for an aircraft galley trolley according to claim 5, characterized in that: The height adjustment mechanism includes a linear guide rail (26) vertically installed on the frame (1), and a screw rod (23) rotatably installed in the mounting seat I (3) or the mounting seat II (5). The axis of the screw rod (23) is arranged vertically. The mounting seat I (3) or the mounting seat II (5) is installed on the guide rail slider of the linear guide rail (26). A support seat (24) is installed at the lower end of the screw rod (23), and the lower end surface of the support seat (24) is in contact with the ground.

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