Auxiliary turnover device for off-position disassembly, assembly and maintenance of aircraft hydraulic pump

Abstract

The utility model discloses an auxiliary turnover device for off-position disassembly and maintenance of a hydraulic pump of an airplane. The auxiliary turnover device comprises a speed reducer and a pump body adaptive seat arranged on an output shaft of the speed reducer. And the speed reducer drives the output shaft through the hand wheel so as to drive the pump body adaptive seat to turn over. A U-shaped fork is arranged at one end of the output shaft. The pump body adapter seat comprises a seat ring and a seat handle which are integrally and fixedly connected; and the seat handle is butted with the U-shaped fork. A first fastening screw hole is formed in the U-shaped fork, and the pump body adapter seat is fixedly installed on the output shaft of the speed reducer through cooperation of the first fastening hole and the first fastening piece. A plurality of second fastening holes are formed in the seat ring, the second fastening holes correspond to positioning screw holes in the hydraulic pump, and the hydraulic pump is screwed and fixed to the pump body adapter seat through matching of the second fastening holes and second fastening pieces. According to the auxiliary turnover device, the speed reducer with the large reduction ratio is used for driving the pump body adapter base to turn over, so that the hydraulic pump is driven to turn over, and the disassembly and assembly efficiency of the hydraulic pump is effectively improved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft ground maintenance technology, and in particular to an auxiliary tilting device used for disassembling and repairing aircraft hydraulic pumps. Background Technology

[0002] During the disassembly, assembly, and maintenance of hydraulic pumps in civil aircraft, the pump body often needs to be rotated due to the different locations where it needs to be disassembled or assembled. For example, the disassembly and assembly direction of the hydraulic pump shaft seal (positive position) is opposite to that of other parts (reverse position). When the pump body is fixed downwards according to the mounting holes, the operator needs to bend over and reach under the pump body to work when disassembling or assembling the shaft seal, or the pump body needs to be reversed and fixed again before disassembly and assembly.

[0003] The manufacturer-recommended pump body positioning fixture can only hold the pump body in place. You must first disassemble some parts, then remove the pump body from the fixture, reverse it, and reattach it to the fixture before finally disassembling the remaining pump body parts. This process of disassembling the pump body using the manufacturer's pump body positioning fixture has the following drawbacks:

[0004] 1. The entire disassembly and assembly process requires disassembling and assembling the pump body twice, once in the positive position and once in the negative position, on the positioning fixture. This makes disassembly and assembly difficult, which can easily cause damage to parts or injury to personnel, and the efficiency of disassembly, assembly and maintenance operations is low.

[0005] 2. The pump body mounting hole is facing downwards. When installing the shaft seal, it is easy to cause uneven installation of the shaft seal, resulting in damage to parts and waste of maintenance materials. If the positioning is changed, a lot of time will be wasted and the maintenance efficiency is low. Utility Model Content

[0006] To address the shortcomings of existing technologies, this utility model provides an auxiliary tilting device for disassembling and repairing aircraft hydraulic pumps, thereby overcoming the deficiencies in existing technologies.

[0007] To achieve the above objectives, this utility model provides the following technical solution:

[0008] An auxiliary tilting device for disassembling and repairing an aircraft hydraulic pump includes a speed reducer fixed on a maintenance bench and a pump body adapter mounted on the output shaft of the speed reducer.

[0009] The reducer drives the output shaft via a handwheel connected to the input shaft;

[0010] The output shaft is connected to the reducer via a spline; a U-shaped fork is provided at the end of the output shaft that is connected to the pump body adapter.

[0011] The pump body adapter includes an integrally fixed seat ring and a seat handle; the seat handle is connected to the U-shaped fork.

[0012] Furthermore, the U-shaped fork is provided with a first fastening screw hole, and the pump body adapter seat is fixedly installed on the output shaft of the reducer by cooperating with the first fastening hole and the first fastener.

[0013] Furthermore, the seat ring is provided with a plurality of second fastening holes, which correspond to the positioning screw holes on the hydraulic pump. The hydraulic pump is screwed and fixed on the pump body adapter seat by cooperating with the second fasteners through the second fastening holes.

[0014] Furthermore, the seat handle is provided with a number of third fastening holes, which correspond to the first fastening screw holes opened on the U-shaped fork of the reducer output shaft. The pump body adapter seat is fixedly installed on the reducer output shaft by cooperating with the first fastening holes, the third fastening holes and the first fastener.

[0015] Preferably, both the first fastener and the second fastener are 12.9 grade high-strength bolts.

[0016] Preferably, the spline is 50mm long, 10mm wide, and 4mm thick.

[0017] Preferably, the pump body adapter is a detachable component.

[0018] Preferably, the reduction ratio of the reducer is 1:50.

[0019] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0020] 1) The auxiliary tilting device used in this case for the disassembly, assembly and maintenance of the aircraft hydraulic pump uses a high reduction ratio reducer to drive the pump body adapter to tilt, thereby driving the hydraulic pump to tilt and lock, effectively improving the disassembly and assembly efficiency of the hydraulic pump, avoiding damage to parts, and improving the safety of the hydraulic pump disassembly and assembly operation.

[0021] 2) The auxiliary tilting device used for disassembly, assembly and maintenance of the aircraft hydraulic pump in this case is designed with a pump body adapter seat that matches the hydraulic pump of different part numbers and has sufficient strength. It can be adapted to different models of hydraulic pumps and has strong adaptability.

[0022] 3) The auxiliary tilting device used for disassembly, assembly and maintenance of the aircraft hydraulic pump in this case has a simple structure, low manufacturing cost and is conducive to promotion.

[0023] To provide a clearer understanding of this invention, the preferred embodiments of this invention will be described below in conjunction with the accompanying drawings. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0025] Attached image labels:

[0026] 1-Reducer, 2-Output shaft, 3-Pump body adapter seat; 11-Handwheel, 12-Input shaft; 21-U-shaped fork, 22-First fastener; 31-Seat ring, 32-Seat handle, 311-Second fastening hole. Detailed Implementation

[0027] In the description of this utility model, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. In the description of this utility model, unless otherwise stated, "a plurality of" means two or more.

[0028] Furthermore, if terms such as "first" or "second" are used for descriptive purposes only, they are mainly used to distinguish different devices, components or parts (the specific types and structures may be the same or different), and are not used to indicate or imply the relative importance or quantity of the indicated devices, components or parts, and should not be construed as indicating or implying relative importance.

[0029] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," "sleeved / connected," "connected," etc., should be interpreted broadly. For example, "connection" 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 an indirect connection through an intermediate medium; it can be a connection within two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.

[0030] Please also refer to Figure 1 This utility model provides an auxiliary tilting device for disassembling and repairing an aircraft hydraulic pump, including a reducer 1 fixed on a maintenance platform and a pump body adapter 3 mounted on the output shaft 2 of the reducer 1. The reducer 1 drives the pump body adapter 3 to tilt through the output shaft 2.

[0031] The reducer 1 has a reduction ratio of 1:50, which enables the reducer 1 to achieve self-locking at any position. The reducer 1 drives the output shaft 2 through the handwheel 11 connected to the input shaft 12. Rotating the handwheel 11 causes the output shaft 2 to rotate, thereby causing the hydraulic pump (not shown in the figure) on the pump body adapter 3 to flip.

[0032] The output shaft 2 is reliably connected to the reducer 1 via a spline with a length of 50mm, a width of 10mm, and a thickness of 4mm. A U-shaped fork 21 is provided at one end of the output shaft 2 that is connected to the pump body adapter 3. A first fastening screw hole is provided on the U-shaped fork 21. The pump body adapter 3 can be fixedly installed on the output shaft 2 of the reducer 1 by cooperating with the first fastening hole and the first fastener 22.

[0033] Pump body adapter 3 includes an integrally fixedly connected seat ring 31 and seat handle 32;

[0034] The seat ring 31 is provided with a plurality of second fastening holes 311, which correspond to the positioning screw holes on the hydraulic pump, so that the hydraulic pump can be screwed and fixed on the pump body adapter seat 3 through the cooperation of the second fastening holes 311 and the second fastener.

[0035] The seat 32 is provided with several third fastening holes, which correspond to the first fastening screw holes opened on the U-shaped fork 21 of the output shaft 2 of the reducer 1. The pump body adapter 3 can be fixedly installed on the output shaft 2 of the reducer 1 by cooperating with the first fastening hole, the third fastening hole and the first fastener 22.

[0036] Preferably, in this embodiment, the pump body adapter 3 is a detachable part. Depending on the model of the hydraulic pump that the airline needs to install or remove, different models of pump body adapter 3 can be selected to adapt to it.

[0037] Preferably, in this embodiment, both the first fastener 22 and the second fastener are 12.9 grade high-strength bolts, which ensures reliable connection while enabling easy assembly and disassembly.

[0038] The operating procedure of the auxiliary tilting device in this case under actual working conditions is as follows:

[0039] 1. Connect the pump body adapter 3 to the output shaft 2 of the reducer 1 using the first fastener 22;

[0040] 2. Connect the hydraulic pump to the pump body adapter 3 via the second fastener;

[0041] 3. During the disassembly, assembly and maintenance of the hydraulic pump, the output shaft 2 of the reducer 1 is driven by manually rotating the handwheel 11, thereby realizing the rotation of the hydraulic pump. Since the reduction ratio of the reducer 1 is 1:50, the reducer 1 can achieve self-locking after being rotated into position.

[0042] Compared to existing technologies, the auxiliary tilting device used for disassembly, assembly, and maintenance of the aircraft hydraulic pump in this case utilizes a high-reduction-ratio reducer to tilt the pump body adapter, thereby tilting and locking the hydraulic pump. This effectively improves the efficiency of hydraulic pump disassembly and assembly, avoids damage to components, and enhances the safety of hydraulic pump disassembly and assembly operations.

[0043] The embodiments described above are merely examples of several implementations of this utility model, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these modifications and improvements all fall within the protection scope of this utility model.

Claims

1. An auxiliary turnover device for aircraft hydraulic pump off-site disassembly and maintenance, characterized in that: it comprises a reducer (1) fixed on a maintenance table and a pump body adapter seat (3) installed on the output shaft (2) of the reducer (1); the reducer (1) drives the output shaft (2) through the hand wheel (11) connected to the input shaft (12); the output shaft (2) is connected to the reducer (1) through spline; one end of the output shaft (2) connected with the pump body adapter seat (3) is provided with a U-shaped fork (21); the pump body adapter seat (3) comprises a seat ring (31) and a seat handle (32) fixedly connected as a whole; the seat handle (32) is in butt joint with the U-shaped fork (21). A first fastening hole is formed in the U-shaped fork (21), and the pump body adapter seat (3) is fixedly installed on the output shaft (2) of the reducer (1) through cooperation of the first fastening hole and the first fastening piece (22). A plurality of second fastening holes (311) are arranged on the seat ring (31), the second fastening holes (311) correspond to positioning screw holes on the hydraulic pump, and the hydraulic pump is screw-fixed on the pump body adapter seat (3) through cooperation of the second fastening holes (311) and the second fastening piece. A plurality of third fastening holes are arranged on the seat handle (32), the third fastening holes correspond to the first fastening screw holes formed in the U-shaped fork (21) of the output shaft (2) of the reducer (1), and the pump body adapter seat (3) is fixedly installed on the output shaft (2) of the reducer (1) through cooperation of the first fastening hole, the third fastening hole and the first fastening piece (22). The first fastening piece (22) and the second fastening piece are both 12.9-grade high-strength bolts.

2. The auxiliary turnover device for dismounting and repairing the hydraulic pump of an airplane when it is off position according to claim 1, characterized in that: The spline is 50mm long, 10mm wide and 4mm thick.

3. The auxiliary turnover device for dismounting and repairing the hydraulic pump of an airplane when it is off position according to claim 2, characterized in that: The pump body adapter seat (3) is a detachable part.

4. The auxiliary turnover device for dismounting and repairing the hydraulic pump of an airplane when it is off position according to claim 3, characterized in that: The reduction ratio of the reducer (1) is 1:

50.

5. The auxiliary turnover device for dismounting and repairing the hydraulic pump of an airplane when it is off its position according to claim 4, characterized in that: ​ 6. The auxiliary turnover device for dismounting and repairing the hydraulic pump of an airplane when it is off its position according to claim 1, characterized in that: ​ 7. The auxiliary turnover device for dismounting and repairing the hydraulic pump of an airplane when it is off its position according to claim 1, characterized in that: ​ 8. The auxiliary turnover device for dismounting and repairing the hydraulic pump of an airplane when it is off its position according to claim 1, characterized in that: ​

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