Telescopic aviation aircraft undercarriage overhaul channel structure

Abstract

The invention discloses a telescopic aviation aircraft landing gear overhaul channel structure, and relates to the technical field of lifting mechanisms, the telescopic aviation aircraft landing gear overhaul channel structure comprises a base, the top of the base is provided with two lifting assemblies; the lifting seat is arranged on the upper portion of the base, and the lifting seat and the two lifting assemblies are fixed; the pneumatic assembly is arranged at the top of the base; and the four supporting assemblies are arranged at the four corners of the top of the base correspondingly, and the four supporting assemblies communicate with the pneumatic assembly. After lifting, the limiting assembly is driven by the pneumatic assembly to work, so that the base and the lifting seat are kept stable, even if the lifting assembly breaks down, it can be guaranteed that the lifting seat does not descend quickly, and meanwhile the safety of workers is further guaranteed by controlling and adjusting the descending speed of the lifting seat through the limiting assembly.

Description

Technical Field

[0001] The invention relates to the technical field of lifting mechanisms, in particular to a retractable aircraft landing gear maintenance channel structure. Background Art

[0002] The parts of the landing gear will wear out during use and need to be replaced in time to ensure the normal operation of the landing gear. Since the aircraft body is high, a lifting platform is required to provide a suitable working environment for the staff when inspecting the aircraft landing gear. Therefore, a retractable aircraft landing gear inspection channel structure is needed.

[0003] In the prior art, in order to avoid maintenance equipment occupying more airspace, most lifting platforms use connecting rods to achieve the lifting of the working platform. The connecting rod components in the connecting rod mechanism are subjected to great force, which may cause damage to the connecting rod components. The components may break during the lifting or maintenance process. If this happens, it will cause injuries to the staff. In order to increase the stability of the device, more connecting rod components are usually used, which also makes the device heavier as a whole and inconvenient to move, thereby hindering the maintenance work. Summary of the invention

[0004] The purpose of the present invention is to provide a retractable aircraft landing gear maintenance channel structure to solve the technical problems in the prior art.

[0005] The present invention provides a retractable aircraft landing gear maintenance channel structure, comprising:

[0006] A base, wherein two lifting assemblies are arranged on the top of the base;

[0007] A lifting seat, wherein the lifting seat is arranged above the base, and the lifting seat and the two lifting components are fixed;

[0008] A pneumatic assembly, wherein the pneumatic assembly is arranged on the top of the base;

[0009] Four support assemblies, the four support assemblies are respectively arranged at the four corners of the top of the base, and the four support assemblies are all connected to the pneumatic assembly;

[0010] Four limiting components, the four limiting components are respectively arranged on two side walls of the base, and the four limiting components are all fixed to the lifting seat, and the limiting components are connected to the pneumatic component;

[0011] Wherein, the pneumatic component comprises:

[0012] A tank body, which is fixed on the top of the base and is connected to four supporting assemblies;

[0013] Two first pistons are both slidably arranged in the tank body, two side walls of the tank body are both provided with transmission rods, two ends of the transmission rods are both fixed with transmission plates, and the two transmission plates are both fixed to the lifting assembly.

[0014] Preferably, the lifting assembly comprises:

[0015] Four fixed plates, two of which are fixed on the top of the base, and the other two are fixed on the bottom of the lifting seat, and a screw rod is rotatably arranged between each two of the fixed plates, one of which is close to the base, and the other is close to the lifting seat;

[0016] Two transmission seats, the two transmission seats are slidably arranged on the top of the base and the bottom of the lifting seat respectively, the side walls of the two transmission seats are provided with threaded holes, and the two screw rods pass through the two threaded holes respectively, and the transmission seats and the transmission plate are fixed;

[0017] A connecting rod, both ends of which are rotatably connected to two transmission seats.

[0018] Preferably, it also includes:

[0019] Two motors, the two motors are respectively fixed on the side walls of two fixed plates, and the output shafts of the two motors are respectively fixed to the nearest screw rods, each screw rod side wall is fixed with a transmission wheel, and the transmission wheels are rotatably connected to the nearest fixed plate, and the same transmission belt is sleeved on every two adjacent transmission wheels.

[0020] Preferably, the support assembly comprises:

[0021] A second sleeve, the second sleeve is fixed on the top of the base, and a second piston is slidably arranged in the second sleeve;

[0022] A second set of rods, the second set of rods is fixed to the bottom of the second piston, and the second set of rods passes through the bottom of the base;

[0023] A support plate is fixed to the bottom end of the second set of rods.

[0024] Preferably, it also includes:

[0025] A connecting pipe, one end of which passes through the side wall of the tank body and is located between the two first pistons, and the four second sleeves are all connected to the connecting pipe.

[0026] Preferably, the limiting component comprises:

[0027] A fixed block, wherein the fixed block is fixed on the side wall of the lifting seat;

[0028] A first sleeve, wherein the first sleeve penetrates and is fixed on the fixed block, a third piston is slidably arranged in the first sleeve, and a first sleeve rod is fixed at the bottom end of the third piston;

[0029] A connecting block, wherein the connecting block is fixed to the base, and the connecting block is fixed to the first set of rods;

[0030] A second solenoid valve is disposed through the top of the first sleeve.

[0031] Preferably, it also includes:

[0032] Two oil storage tanks, both of which are fixed on the top of the base, and each of which has a first tube body penetrating through the side wall of the oil storage tank;

[0033] A second tube body, wherein two ends of the second tube body are connected to two adjacent first sleeves, and the second tube body is connected to the first tube body;

[0034] The first solenoid valve has one end connected to the oil storage tank, and the other end connected to the connecting pipe.

[0035] Preferably, brake wheels are provided at the four corners of the bottom of the base.

[0036] Compared with the prior art, the beneficial effects of the present invention are:

[0037] The present invention drives the lifting seat to rise when the lifting component is set to work, so as to ensure that the staff can reach a suitable height for the maintenance work of the landing gear. When the lifting component is working, the air inside the tube body is compressed by the two first pistons, and the supporting component is pushed to work by the high-pressure gas, so that during the maintenance process, the device can maintain a high stability, thereby avoiding the occurrence of safety accidents caused by the movement of the device. After lifting, the limiting component is driven to work by the pneumatic component, so that the base and the lifting seat are kept stable. Even if the lifting component fails, it can be ensured that the lifting seat will not fall quickly. At the same time, the control of the limiting component can adjust the descending speed of the lifting seat, further ensuring the safety of the staff. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0039] Figure 1 It is a three-dimensional structural schematic diagram of the present invention;

[0040] Figure 2 is a schematic diagram of the second set of rods and support plates of the present invention;

[0041] Figure 3 It is a schematic diagram of the transmission wheel and transmission belt structure of the present invention;

[0042] Figure 4 It is a schematic diagram of the structure of the transmission plate, transmission rod and transmission seat of the present invention;

[0043] Figure 5 It is a schematic diagram of the cross-sectional structure of the tank body of the present invention;

[0044] Figure 6 is a schematic cross-sectional structural diagram of a second sleeve of the present invention;

[0045] Figure 7 It is a schematic diagram of the cross-sectional structure of the first sleeve of the present invention.

[0046] Reference numerals:

[0047] 1. Base; 2. Brake wheel; 3. Fixed plate; 4. Screw rod; 5. Motor; 6. Transmission seat; 7. Connecting rod; 8. Lifting seat; 9. First tube body; 10. Fixed block; 11. First sleeve; 12. First set of rods; 13. Connecting block; 14. Second tube body; 15. Oil storage tank; 16. Second sleeve; 17. Second set of rods; 18. Support plate; 19. Transmission wheel; 20. Transmission belt; 21. Tank body; 22. Transmission rod; 23. Transmission plate; 24. Connecting pipe; 25. First piston; 26. Second piston; 27. Third piston; 28. First solenoid valve; 29. ​​Second solenoid valve. DETAILED DESCRIPTION

[0048] The technical solution of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments.

[0049] The components of the embodiments of the present invention generally described and shown in the drawings herein may be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the drawings is not intended to limit the scope of the claimed invention, but merely represents selected embodiments of the present invention.

[0050] Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in the field without making any creative work shall fall within the scope of protection of the present invention.

[0051] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and "third" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0052] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0053] Combine the following Figures 1 to 7 As shown, an embodiment of the present invention provides a retractable aircraft landing gear maintenance channel structure, including:

[0054] A base 1, with two lifting components arranged on the top of the base 1;

[0055] A lifting seat 8, which is arranged above the base 1, and the lifting seat 8 and the two lifting components are fixed;

[0056] A pneumatic component, which is arranged on the top of the base 1;

[0057] Four support assemblies, the four support assemblies are respectively arranged at the four corners of the top of the base 1, and the four support assemblies are all connected to the pneumatic assembly;

[0058] Four limiting components, the four limiting components are respectively arranged on the two side walls of the base 1, and the four limiting components are all fixed to the lifting seat 8, and the limiting components are connected to the pneumatic components;

[0059] Among them, the pneumatic components include:

[0060] A tank body 21, which is fixed on the top of the base 1 and is connected to four supporting components;

[0061] Two first pistons 25 are slidably disposed in the tank body 21. Transmission rods 22 are disposed on the side walls of the two tank bodies 21. Transmission plates 23 are fixed to the ends of the two transmission rods 22, and the two transmission plates 23 are fixed to the lifting assembly.

[0062] When the lifting assembly is working, it drives the lifting seat 8 to rise to ensure that the staff can reach a suitable height to facilitate the maintenance of the landing gear;

[0063] While the lifting assembly is working, the air inside the tube body 21 is compressed by the two first pistons 25, and the support assembly is pushed to work by the high-pressure gas, so that during the maintenance process, the device can maintain a high stability, thereby avoiding the occurrence of safety accidents caused by the movement of the device;

[0064] After lifting, the limiting component is driven by the pneumatic component to ensure that the base 1 and the lifting seat 8 remain stable. Even if the lifting component fails, the lifting seat 8 will not fall quickly. At the same time, the lowering speed of the lifting seat 8 is adjusted by controlling the limiting component, further ensuring the safety of the staff.

[0065] Furthermore, the lifting assembly includes:

[0066] Four fixed plates 3, two of which are fixed on the top of the base 1, and the other two are fixed on the bottom of the lifting seat 8, and a screw rod 4 is rotatably arranged between every two fixed plates 3, one of which is close to the base 1, and the other is close to the lifting seat 8;

[0067] Two transmission seats 6, the two transmission seats 6 are slidably arranged on the top of the base 1 and the bottom of the lifting seat 8 respectively, the side walls of the two transmission seats 6 are provided with threaded holes, and the two screw rods 4 pass through the two threaded holes respectively, and the transmission seats 6 and the transmission plate 23 are fixed;

[0068] The connecting rod 7 has two ends which are rotatably connected to the two transmission seats 6 respectively.

[0069] Furthermore, it also includes:

[0070] Two motors 5 are respectively fixed on the side walls of two of the fixed plates 3, and the output shafts of the two motors 5 are respectively fixed to the nearest screw rod 4. A transmission wheel 19 is fixed to the side wall of each screw rod 4, and the transmission wheels 19 are rotatably connected to the nearest fixed plate 3. The same transmission belt 20 is sleeved on every two adjacent transmission wheels 19.

[0071] When the two motors 5 are working, they drive the two corresponding screw rods 4 to rotate, thereby driving the two transmission seats 6 on the two screw rods 4 to approach each other, and through the action of the connecting rod 7, the lifting seat 8 gradually rises;

[0072] When the two transmission seats 6 approach each other, the two first pistons 25 in the tank body 21 are driven by the transmission plate 23 and the transmission rod 22 to move closer to each other, thereby compressing the gas between the two first pistons 25 in the tank body 21 .

[0073] Furthermore, the support assembly includes:

[0074] A second sleeve 16, the second sleeve 16 is fixed on the top of the base 1, and a second piston 26 is slidably arranged in the second sleeve 16;

[0075] A second rod 17, which is fixed to the bottom of the second piston 26 and passes through the bottom of the base 1;

[0076] The support plate 18 is fixed at the bottom end of the second set of rods 17.

[0077] Furthermore, it also includes:

[0078] A connecting pipe 24 , one end of which passes through the side wall of the tank body 21 and is located between the two first pistons 25 , and the four second sleeves 16 are all connected to the connecting pipe 24 .

[0079] The compressed gas enters the four second sleeves 16 through the connecting pipe 24, and the second piston 26 in the second sleeve 16 is pushed to move under the action of the gas pressure, so that the second rod 17 drives the support plate 18 to descend. When the support plate 18 contacts the ground, the friction provided by the support plate 18 ensures the stability of the base 1.

[0080] Further, restricted components include:

[0081] A fixed block 10, the fixed block 10 is fixed on the side wall of the lifting seat 8;

[0082] A first sleeve 11, which is fixed on the fixed block 10, a third piston 27 is slidably arranged in the first sleeve 11, and a first sleeve rod 12 is fixed to the bottom end of the third piston 27;

[0083] A connecting block 13, wherein the connecting block 13 is fixed to the base 1, and the connecting block 13 is fixed to the first set of rods 12;

[0084] The second solenoid valve 29 is disposed through the top of the first sleeve 11 .

[0085] Furthermore, it also includes:

[0086] Two oil storage tanks 15, both of which are fixed on the top of the base 1, and each of the side walls of the oil storage tank 15 is penetrated by a first tube body 9;

[0087] A second tube body 14, both ends of which are in communication with two adjacent first sleeves 11, and the second tube body 14 is in communication with the first tube body 9;

[0088] The first solenoid valve 28 has one end connected to the oil storage tank 15 and the other end connected to the connecting pipe 24 .

[0089] The switch of the first solenoid valve 28 is turned on, so that the compressed gas between the two first pistons 25 in the tank body 21 enters the oil storage tank 15 through the connecting pipe 24, so as to push the hydraulic oil in the oil storage tank 15 into the two first sleeves 11 through the first pipe body 9 and the second pipe body 14. When the gas in the first sleeve 11 is squeezed out by the hydraulic oil, the switch of the second solenoid valve 29 is turned off. At this time, as the lifting seat 8 continues to rise, the hydraulic oil continues to enter the first sleeve 11. When the lifting seat 8 stops rising, the switch of the first solenoid valve 28 can be turned off, so that The hydraulic oil in the first sleeve 11 cannot be output due to the incompressible nature of the hydraulic oil. Therefore, the lifting seat 8 and the base 1 are kept fixed by the first sleeve 11 and the first set of rods 12. Even after the connecting rod 7 is damaged, the flow of the lifting seat 8 can still be controlled to slowly input the hydraulic oil in the first sleeve 11 into the oil storage tank 15 to achieve a slow descent of the lifting seat 8. This can not only keep the lifting seat 8 stable during work, but also achieve a slow descent of the lifting seat 8 after the connecting rod 7 is damaged, thereby ensuring a safe working environment for the staff.

[0090] Furthermore, brake wheels 2 are provided at the four corners of the bottom of the base 1 .

[0091] The specific working method is: when in use, the device is moved to the landing gear of the aircraft through the action of the brake wheel 2;

[0092] Then, the switches of the two motors 5 are turned on. When the two motors 5 are working, they drive the two corresponding screw rods 4 to rotate, thereby driving the two transmission seats 6 on the two screw rods 4 to approach each other. Through the action of the connecting rod 7, the lifting seat 8 gradually rises. In this process, the first solenoid valve 28 is closed, so that the gas in the connecting pipe 24 cannot be discharged through the first solenoid valve 28, and the second solenoid valve 29 is turned on, so that the external gas can enter the first sleeve 11 through the second solenoid valve 29, so that the lifting seat 8 can rise normally;

[0093] In the process of the two transmission seats 6 approaching each other, the transmission of the transmission plate 23 and the transmission rod 22 makes the two first pistons 25 in the tank body 21 approach each other, so that the gas between the two first pistons 25 in the tank body 21 is compressed, and the compressed gas enters the four second sleeves 16 through the connecting pipe 24, and the second pistons 26 in the second sleeves 16 are pushed to move under the action of the gas pressure, so that the second sleeve rod 17 drives the support plate 18 to descend. When the support plate 18 contacts the ground, the friction provided by the support plate 18 ensures the stability of the base 1, and then the staff can board the lifting seat 8;

[0094] After the staff climbs onto the lifting seat 8, they continue to control the motor 5 to continue working, so that the lifting seat 8 rises further until it reaches a suitable height. Then, the switch of the first solenoid valve 28 is turned on, so that the compressed gas between the two first pistons 25 in the tank body 21 enters the oil storage tank 15 through the connecting pipe 24, so as to push the hydraulic oil in the oil storage tank 15 into the two first sleeves 11 through the first pipe body 9 and the second pipe body 14. When the gas in the first sleeve 11 is squeezed out by the hydraulic oil, the switch of the second solenoid valve 29 is closed. At this time, as the lifting seat 8 continues to rise, the hydraulic oil continues to enter the first sleeve 11. When the lifting seat 8 is lifted, the hydraulic oil continues to enter the first sleeve 11. After the seat 8 stops rising, the switch of the first solenoid valve 28 can be closed, so that the hydraulic oil in the first sleeve 11 cannot be output. Due to the incompressible nature of the hydraulic oil, the lifting seat 8 and the base 1 are kept fixed by the first sleeve 11 and the first set of rods 12. Even after the connecting rod 7 is damaged, the flow of the lifting seat 8 can still be controlled to slowly input the hydraulic oil in the first sleeve 11 into the oil storage tank 15 to achieve the slow descent of the lifting seat 8. The stability of the lifting seat 8 can be maintained during the work process, and the lifting seat 8 can be slowly descended after the connecting rod 7 is damaged, thereby ensuring a safe working environment for the staff.

[0095] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A retractable aircraft landing gear maintenance channel structure, characterized in that: include: A base (1), wherein two lifting assemblies are arranged on the top of the base (1); A lifting seat (8), wherein the lifting seat (8) is arranged above the base (1), and the lifting seat (8) and the two lifting components are fixed; A pneumatic component, wherein the pneumatic component is arranged on the top of the base (1); Four support assemblies, the four support assemblies are respectively arranged at the four corners of the top of the base (1), and the four support assemblies are all connected to the pneumatic assembly; Four limiting components, the four limiting components are respectively arranged on two side walls of the base (1), and the four limiting components are all fixed to the lifting seat (8), and the limiting components are connected to the pneumatic components; Wherein, the pneumatic component comprises: A tank body (21), wherein the tank body (21) is fixed on the top of the base (1), and the tank body (21) is connected to four supporting components; Two first pistons (25), both of which are slidably disposed in the tank body (21), both side walls of the tank bodies (21) are provided with transmission rods (22), both ends of the two transmission rods (22) are fixed with transmission plates (23), and both transmission plates (23) are fixed to the lifting assembly.

2. The retractable aircraft landing gear maintenance channel structure according to claim 1 is characterized in that: The lifting assembly comprises: Four fixed plates (3), two of which are fixed on the top of the base (1), and the other two are fixed on the bottom of the lifting seat (8), and a screw rod (4) is rotatably arranged between each two of the fixed plates (3), one of which is close to the base (1), and the other is close to the lifting seat (8); Two transmission seats (6), the two transmission seats (6) are slidably arranged on the top of the base (1) and the bottom of the lifting seat (8), the side walls of the two transmission seats (6) are both provided with threaded holes, and the two screw rods (4) pass through the two threaded holes respectively, and the transmission seats (6) and the transmission plate (23) are fixed; A connecting rod (7), both ends of which are rotatably connected to two transmission seats (6).

3. The retractable aircraft landing gear maintenance channel structure according to claim 2 is characterized in that: Also includes: Two motors (5), the two motors (5) are respectively fixed on the side walls of two of the fixing plates (3), and the output shafts of the two motors (5) are respectively fixed to the nearest screw rods (4), a transmission wheel (19) is fixed to the side wall of each screw rod (4), and the transmission wheel (19) is rotatably connected to the nearest fixing plate (3), and the same transmission belt (20) is sleeved on every two adjacent transmission wheels (19).

4. The retractable aircraft landing gear maintenance channel structure according to claim 3 is characterized in that: The support assembly comprises: A second sleeve (16), the second sleeve (16) being fixed on the top of the base (1), and a second piston (26) being slidably disposed in the second sleeve (16); A second rod (17), the second rod (17) being fixed to the bottom of the second piston (26), and the second rod (17) passing through the bottom of the base (1); A support plate (18) is fixed to the bottom end of the second sleeve rod (17).

5. The retractable aircraft landing gear maintenance channel structure according to claim 4 is characterized in that: Also includes: A connecting pipe (24), one end of which passes through the side wall of the tank body (21) and is located between the two first pistons (25), and the four second sleeves (16) are all connected to the connecting pipe (24).

6. The retractable aircraft landing gear maintenance channel structure according to claim 5, characterized in that: The restriction components include: A fixed block (10), wherein the fixed block (10) is fixed on a side wall of the lifting seat (8); A first sleeve (11), the first sleeve (11) is passed through and fixed on the fixed block (10), a third piston (27) is slidably arranged in the first sleeve (11), and a first sleeve rod (12) is fixed to the bottom end of the third piston (27); A connecting block (13), wherein the connecting block (13) and the base (1) are fixed, and the connecting block (13) and the first set of rods (12) are fixed; A second solenoid valve (29), wherein the second solenoid valve (29) is disposed through the top of the first sleeve (11).

7. The retractable aircraft landing gear maintenance channel structure according to claim 6, characterized in that: Also includes: Two oil storage tanks (15), both of which are fixed on the top of the base (1), and each of which has a first tube body (9) running through its side wall; A second tube body (14), wherein two ends of the second tube body (14) are in communication with two adjacent first sleeves (11), and the second tube body (14) is in communication with the first tube body (9); A first solenoid valve (28), one end of the first solenoid valve (28) is connected to the oil storage tank (15), and the other end of the first solenoid valve (28) is connected to the connecting pipe (24).

8. The retractable aircraft landing gear maintenance channel structure according to claim 2, characterized in that: Braking wheels (2) are arranged at the four corners of the bottom of the base (1).

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