Aircraft engine rammer device

Abstract

The utility model relates to the technical field of aircraft installation equipment, in particular to an aircraft engine rammer device which comprises a connecting part, a guide connecting structure, a rammer part and a limiting nut. A connecting part and a limiting nut are detachably installed at the two ends of the guiding connecting structure respectively, the guiding connecting structure is provided with a guiding section, and the rammer part is arranged on the guiding section in a sliding mode. And the loading and unloading efficiency of the aircraft engine is greatly improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft maintenance equipment, in particular to an aircraft engine striker device. Background Art

[0002] The engine is the heart of the aircraft, the largest finished part in the aircraft assembly process, and an extremely important part of the aircraft manufacturing process. In the aviation field, the manufacturing precision of the engine and its supporting parts is high, and they are high-value products. If they are improperly operated during the installation and disassembly process, it is easy to cause great losses.

[0003] When installing the engine, after the engine enters the cabin and reaches the predetermined position, the main thrust pin of the engine is inserted into the end face of the engine connection to connect and fix the engine, so as to realize the assembly of the engine in the cabin. When disassembling, the main thrust pin is pulled out from the engine to disassemble the engine.

[0004] The existing thrust pin has a narrow assembly and disassembly space, and the process of inserting and removing the thrust pin is difficult, which can easily cause damage to the thrust pin and the engine, resulting in huge economic losses.

[0005] Some existing aircraft models require that when loading and unloading the engine, the loading and unloading tools cannot be directly in contact with the aircraft body or cabin. There is also no fixed cabin panel at the aircraft engine installation cabin to provide connection and fixation for external disassembly and assembly tools to avoid damage to the aircraft during the engine disassembly process.

[0006] Prior art 201110253491.7, a tool for disassembling and assembling axle pins, comprising axle pin disassembling pliers and axle pin installing pliers, the axle pin disassembling pliers and axle pin installing pliers in the axle pin disassembling tool comprise a pliers body and a handle hinged to the pliers body, the head of the pliers body is provided with a through guide hole, the clearance in the guide hole is matched with a push rod, and one end of the push rod is hinged to the head of the handle; the head of the pliers body is provided with a through hole opening outward for inserting the shaft of the axle pin to be disassembled, and the outer end portion of the through hole is provided with two slots for the two protruding ends of the axle pin to be disassembled to be inserted into or extended out, the inner bottom walls of the two slots are flush with the inner wall of the guide hole, and when the handle of the push rod is in a fully pressed state, the free end face of the push rod is located on the outer side of the inner wall of the through hole away from the free end of the push rod or the free end face of the push rod is flush with the inner wall of the slot close to the free end of the push rod. This solution can reduce the difficulty of connection with the pin shaft and reduce the difficulty of disassembly and assembly, but the pin shaft assembly requires high precision and the pulling method is laborious, especially the thrust pin of the aircraft engine is more difficult to disassemble and assemble using this equipment.

[0007] Prior art 201410355455.5, a disassembly and assembly device for a pin shaft, improves the safety during the disassembly and assembly process of the pin shaft. The above-mentioned disassembly and assembly device includes: a positioning plate, a fixing device and a driving device, wherein: the positioning plate is provided with a limiting hole that runs through its thickness direction; when the disassembly and assembly device is in use, the fixing device fixes the positioning plate to the workpiece of the pin shaft to be disassembled, and the axis of the limiting hole of the positioning plate coincides with the axis of the mounting hole for mounting the pin shaft provided on the workpiece, and the driving device is located on one side of the positioning plate and is fixed relative to the positioning plate, and is used to drive the pin shaft to be disassembled to move along the axis direction of the limiting hole. This scheme provides a good disassembly and assembly scheme, but it does not take into account the small space and small operating space during the assembly and disassembly of the thrust pin of the aircraft engine, and it is impossible to configure more structures.

[0008] It is very necessary to provide a thrust pin disassembly and assembly tool for aircraft engines that is suitable for small operating spaces. Utility Model Content

[0009] To this end, the utility model provides an aircraft engine striker device, which can disassemble and assemble the thrust pin of the aircraft engine by striker means and is suitable for a small operating space.

[0010] In order to achieve the above-mentioned purpose, the utility model provides the following technical solutions: an aircraft engine striker device, comprising a connecting component, the connecting component can be detachably connected to the thrust pin, the striker device also includes a guide connection structure, a striker component and a limit nut, wherein:

[0011] The two ends of the guide connection structure are detachably mounted with connection components and limit nuts, and the guide connection structure has a guide section;

[0012] The hammer component is slidably arranged on the guide section.

[0013] Preferably, the limiting nut is installed on the end of the guiding connection structure by means of a cylindrical pin.

[0014] Preferably, the connecting component is a connecting head, and a hexagonal cone-end set screw is provided on the side of the connecting head.

[0015] Preferably, the guiding connection structure is a rod handle.

[0016] Preferably, the hammer component is a hammer head, and the hammer head is detachably connected with a handle.

[0017] The beneficial effects of the utility model are:

[0018] Compared with the prior art, the utility model has the following advantages: through a simple and practical structural device, the original loading and unloading difficulties caused by the small installation space are solved, the operation is simple, and it is easy to carry, which greatly improves the loading and unloading efficiency of the aircraft engine. The solution of this application has great practical value, and is used to solve the difficulties and problems existing in the plug-in and unplug-in loading and unloading process of the thrust pin of the existing aircraft engine. It ensures that during the disassembly and assembly of the aircraft engine in the cabin, the external plug-in and unplug tools can be plugged in and out without contacting the fuselage or cabin. It is precise and controllable, easy to operate and practical, and it also solves the installation difficulty caused by the small installation space. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is an appearance diagram of the engine hammer device provided by the utility model;

[0020] Figure 2 This is a right side view of the engine hammer device structure provided by the utility model.

[0021] Figure 3 This is a top view structure of the engine hammer device provided by the utility model.

[0022] Figure 4 This is a front view of the engine hammer device structure provided by the utility model.

[0023] Figure 5 This is a rear view structure of the engine hammer device structure provided by the utility model.

[0024] In the figure: 1-connector, 2-handle, 3-hammer head, 4-hexagon socket cone end set screw, 5-handle, 6-limit nut, 7-cylindrical pin. DETAILED DESCRIPTION

[0025] The preferred embodiments of the present invention are described below in conjunction with the accompanying drawings. It should be understood that the preferred embodiments described herein are only used to illustrate and explain the present invention, and are not used to limit the present invention.

[0026] Referring to the accompanying drawings, the utility model provides an aircraft engine hammer device, comprising

[0027] A connecting component for connecting to a thrust pin of an aircraft engine, the connecting component is used to be detachably connected to the end of the thrust pin, and is not limited to a specific structure. The solution provided in this embodiment is that the connecting component is a connecting head, the connecting head is provided with a cavity for accommodating the end of the thrust pin, a screw hole is provided through one side of the connecting head, and a hexagonal cone-end set screw is connected to the inner thread of the screw hole to limit the end of the thrust pin;

[0028] The guide connection structure used to connect with the connection part has a guide section, which is not limited to a specific structure rod. The guide connection structure is a rod, which is one or more rods, and is a linear or special-shaped structure. In this embodiment, it is a linear one, which can better meet the requirements of the small operating space for the size of the equipment. Multiple rods can improve the stability of the structure, and the special-shaped structure can meet the situation of complex operating space. The guide connection structure has a guide section parallel to the axis of the thrust pin, the surface of the guide section is smooth, and the length is designed according to the needs.

[0029] The hammer component provides impact force. In this embodiment, the hammer component is a hammer head, and its surface has a protective layer to prevent collision with other structures of the aircraft. It has weight itself to improve the hammer effect. A handle is provided at the bottom of the hammer head for easy holding.

[0030] The limit nut is installed on the other end of the handle using a cylindrical pin.

[0031] In this embodiment, the diameters of the connecting head and the limiting nut are both larger than the diameter of the rod handle. After the hammer head slides on the guide section of the rod handle, it hits the connecting head and the limiting nut to achieve hammering and impact.

[0032] One end of the rod handle is connected to the connecting head through a thread, and the other end of the rod handle is connected to the limit nut through a thread. The inside of the hammer head is a hollow cylinder, and the inner diameter of the hoe is larger than the outer diameter of the rod handle. There is a certain gap between the hoe and the rod handle so that the hoe can slide on the rod handle. A corresponding threaded hole is processed in the center of the outer surface of the hoe, and the handle is assembled with the hoe through a threaded connection.

[0033] Brief description of working principle: The loading and unloading maintenance personnel connect the connector and the thrust pin through threaded assembly, and then repeatedly hit the connector head or limit nut with the hammer handle, thereby driving the thrust pin of the aircraft engine to move along the axial direction to realize loading and unloading and plugging and unplugging.

[0034] The above is only a preferred embodiment of the utility model. Any person skilled in the art may modify the utility model by using the above technical solution or modify it into an equivalent technical solution. Therefore, any simple modification or equivalent replacement based on the technical solution of the utility model shall fall within the scope of protection claimed by the utility model.

Claims

1. An aircraft engine striker device, comprising a connecting member, the connecting member being detachably connected to a thrust pin, characterized in that: The hammer device further comprises a guide connection structure, a hammer component and a limit nut, wherein: The two ends of the guide connection structure are detachably mounted with connection components and limit nuts, and the guide connection structure has a guide section; The hammer component is slidably arranged on the guide section.

2. An aircraft engine striker device according to claim 1, characterized in that: The limiting nut is installed on the end of the guide connection structure by using a cylindrical pin.

3. The aircraft engine striker device according to claim 1, characterized in that: The connecting component is a connecting head, and a hexagonal cone-end set screw is arranged on the side of the connecting head.

4. The aircraft engine striker device according to claim 1, characterized in that: The guiding connection structure is a rod handle.

5. The aircraft engine striker device according to claim 1, characterized in that: The hammer component is a hammer head, and the hammer head is detachably connected with a handle.

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