Aircraft actuator cylinder spring installation tool

Abstract

The utility model relates to aircraft maintenance equipment technical field especially relates to a kind of aircraft actuating cylinder spring installation tooling. Including adjusting lever, shell fixed end and spring pressure cover;The shell fixed end is equipped with first threaded hole;The spring pressure cover is equipped with second threaded hole;The screw rod end of the adjusting lever is threaded through the first threaded hole, and with this first threaded hole threaded cooperation forms the transmission pair that can relatively rotate;The screw rod end of the adjusting lever is fastened connection with the second threaded hole, forms the rigid whole without relative rotation;By rotating the adjusting lever, drive the rigid whole axial movement of the adjusting lever and spring pressure cover, to compress the spring inside actuating cylinder. To solve the technical problem that traditional actuating cylinder assembly process is low in efficiency, poor in accuracy, big in artificial error and lack of special tooling equipment, realize the technical effect of improving aircraft actuating cylinder spring installation efficiency and quality.

Description

Technical Field

[0001] This utility model relates to the field of aircraft maintenance equipment technology, and in particular to an aircraft actuator spring installation fixture. Background Technology

[0002] Aircraft actuators are crucial components in aircraft control systems, primarily used to convert hydraulic or pneumatic energy into mechanical motion, enabling the operation of various aircraft control surfaces. Within the actuator structure, the spring is a key component, providing the necessary return force or preload to ensure proper functioning. However, due to the typically high stiffness of the springs within aircraft actuators, compression installation is required during maintenance or assembly, a process that presents certain technical challenges.

[0003] Regarding actuator assembly and disassembly tools, Chinese patent CN207564409U discloses an actuator assembly and disassembly tool for an aircraft wheel axle jack. This tool has a rod-shaped handle and a collar in the middle, which is locked into a groove on the outer wall of the actuator by a locking bolt, enabling quick assembly and disassembly. Chinese patent CN116551615A discloses an assembly and method for assembling and disassembling an inner spoiler actuator spring seat. This assembly uses the synchronous rotation of a positioning rod and a spring top seat to apply a follow-up load of the same magnitude as the spring force using a balance spring, thereby canceling out the spring force and facilitating the assembly and disassembly of the spring top seat.

[0004] However, existing technologies still have the following problems: First, traditional actuator assembly processes mostly rely on manual assembly, which is not only inefficient but also difficult to guarantee accuracy, and suffers from problems such as large human error and high process difficulty. Second, although aircraft maintenance manuals provide special tool part numbers, these tools are often not available for special procurement, resulting in maintenance personnel lacking suitable tools. Furthermore, existing actuator spring installation tools are complex in structure and inconvenient to operate, failing to meet the needs of efficient and precise maintenance. Especially when it is necessary to compress and install the springs inside the actuator, there is a lack of a dedicated tooling that is simple in structure, easy to operate, and capable of precisely controlling the compression force, which seriously affects the efficiency and quality of actuator maintenance.

[0005] Therefore, there is an urgent need to develop a tooling specifically for installing aircraft actuator springs, in order to solve the problems existing in the current technology and improve the efficiency and quality of actuator maintenance. Utility Model Content

[0006] In order to solve the technical problems of low efficiency, poor precision, large human error and lack of special tooling equipment in the traditional actuator assembly process, and to achieve the technical effect of improving the installation efficiency and quality of aircraft actuator springs.

[0007] To achieve the above objectives, the present invention adopts the following technical solution:

[0008] A mounting fixture for an aircraft actuator spring is provided, comprising an adjusting rod, a housing fixing end, and a spring compression sleeve; the housing fixing end is provided with a first threaded hole; the spring compression sleeve is provided with a second threaded hole; the lead end of the adjusting rod passes through the first threaded hole and is threadedly engaged with the first threaded hole to form a rotatable transmission pair; the lead end of the adjusting rod is fastened to the second threaded hole to form a rigid whole without relative rotation; by rotating the adjusting rod, the rigid whole of the adjusting rod and the spring compression sleeve is driven to move axially to compress the spring inside the actuator.

[0009] Optionally, the lead screw end of the adjusting rod is provided with a segmented thread structure, with the front thread engaging with the first threaded hole and the rear thread fixing with the second threaded hole.

[0010] Optionally, the lower end face of the fixed end of the housing is provided with a positioning groove that matches the shape of the actuator housing.

[0011] Optionally, the lower end face of the spring sleeve is provided with an annular flange for compressing the spring.

[0012] Optionally, the handle end surface of the adjusting rod is provided with an anti-slip knurled pattern.

[0013] Optionally, the axial movement of the spring sleeve drives the inner locking sleeve of the actuator cylinder to generate synchronous relative displacement with the outer handle.

[0014] Alternatively, the tooling can be a detachable, modular structure, with each component connected only by threads.

[0015] Optionally, the adjusting rod, the housing fixing end, and the spring sleeve are all made of hardened steel.

[0016] The advantages of this utility model are:

[0017] 1. This tooling has a simple structure, is easy to manufacture and process, has low cost, is convenient to use, and is safe and reliable. It can effectively replace the traditional manual assembly method and solve the problems of low efficiency, poor precision, and large human error in the traditional actuator assembly process.

[0018] 2. Through the precise fit between the fixed end of the housing and the actuator housing, and the bidirectional threaded transmission structure formed by the adjusting rod and the spring sleeve, precise compression control of the spring is achieved, improving the accuracy and quality of aircraft actuator spring installation.

[0019] 3. This tooling adopts a detachable split structure, with each component connected only by threads, which facilitates maintenance and replacement, extends the service life of the tooling, and improves its practicality.

[0020] 4. By placing the spring compression sleeve on the spring, and fixing the lower end face of the housing to the housing, the spring is compressed by rotating the adjusting rod. At this time, the locking sleeve inside the actuator and the external handle of the actuator will move relative to each other synchronously. The compressed spring is limited and fixed by the external handle, thereby realizing the spring installation of the aircraft actuator, meeting the needs of actuator maintenance, avoiding repetitive work, and improving market competitiveness. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the tooling structure described in this utility model;

[0023] Figure 2 This is a schematic diagram of the adjusting rod structure described in this utility model;

[0024] Figure 3 This is a schematic diagram of the housing fixing end structure described in this utility model;

[0025] Figure 4 This is a schematic diagram of the spring compression sleeve structure described in this utility model;

[0026] Figure 5 This is a schematic diagram of the tooling described in this utility model.

[0027] Figure 6 This utility model Figure 5 Schematic diagram of part A in the middle.

[0028] In the figure: 1. Adjusting rod; 2. Housing fixing end; 201. First threaded hole; 3. Spring sleeve; 301. Second threaded hole; 4. Spring; 5. Locking sleeve; 6. Handle; 7. Housing. Detailed Implementation

[0029] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0030] Example 1:

[0031] like Figures 1-6As shown, an aircraft actuator spring mounting fixture includes an adjusting rod 1, a housing fixing end 2, and a spring compression sleeve 3.

[0032] The housing fixed end 2 is provided with a first threaded hole 201, and the spring sleeve 3 is provided with a second threaded hole 301. The lead screw end of the adjusting rod 1 passes through the first threaded hole 201 and is threadedly engaged with the first threaded hole 201 to form a transmission pair that can rotate relative to each other; the end of the lead screw end of the adjusting rod 1 is fastened to the second threaded hole 301 to form a rigid whole without relative rotation; by rotating the adjusting rod 1, the rigid whole of the adjusting rod 1 and the spring sleeve 3 is driven to move axially to compress the spring 4 inside the actuating cylinder.

[0033] The lead screw end of the adjusting rod 1 is provided with a segmented thread structure. The front thread engages with the first threaded hole 201, and the rear thread is fixed with the second threaded hole 301. This segmented thread structure design ensures that rotating the adjusting rod 1 will only cause relative movement between the adjusting rod 1 and the fixed end 2 of the housing, avoiding relative movement between the adjusting rod 1 and the spring sleeve 3, thus achieving precise control of the axial movement distance of the spring sleeve 3.

[0034] The lower end face of the housing fixing end 2 is provided with a positioning groove that matches the shape of the actuator housing 7. This positioning groove ensures that the actuator housing 7 maintains a stable position during installation, preventing displacement or rotation during the compression of the spring 4, thus improving installation accuracy and operational safety.

[0035] The lower end face of the spring sleeve 3 is provided with an annular flange edge for compressing the spring 4.

[0036] The handle 6 end of the adjusting rod 1 has an anti-slip knurled texture. This anti-slip design increases the friction between the operator's fingers and the adjusting rod 1, preventing the hand from slipping when a large torque is required to compress the spring 4, thus improving operating comfort and safety.

[0037] The axial movement of the spring sleeve 3 drives the internal locking sleeve 5 of the actuator cylinder and the external handle 6 to produce synchronous relative displacement. When the operator rotates the adjusting rod 1, the spring sleeve 3 moves downward, compressing the spring 4 and pushing the internal locking sleeve 5 of the actuator cylinder to move. At the same time, the external handle 6 also moves, so that the two produce a predetermined relative displacement, which facilitates the subsequent locking operation.

[0038] The tooling features a detachable, modular structure, with all components connected only by threads. This design facilitates the disassembly, storage, and transportation of the tooling, while also simplifying maintenance and replacement of worn parts, thus extending the tooling's service life.

[0039] The adjusting rod 1, the housing fixed end 2, and the spring sleeve 3 are all made of hardened steel. Hardened steel has high hardness, high strength, and good wear resistance, and can withstand mechanical stress and friction wear during repeated use, ensuring that the tooling maintains accuracy and functional stability during long-term use.

[0040] During operation, first place the actuator housing 7 in the positioning groove of the housing fixed end 2 and fix it in place; then rotate the adjusting rod 1 to drive the spring sleeve 3 to move downward along the axis, and the spring sleeve 3 compresses the spring 4; at the same time, the movement of the spring sleeve 3 causes the locking sleeve 5 inside the actuator cylinder to generate relative displacement with the external handle 6; after the spring 4 is compressed to the predetermined position and the installation is completed, rotate the adjusting rod 1 in the opposite direction to release the pressure of the spring 4, and finally take out the tooling assembly.

[0041] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.

Claims

1. A fixture for mounting aircraft actuator springs, characterized in that, Includes an adjusting rod, a fixed end of the housing, and a spring sleeve; The housing is provided with a first threaded hole at its fixed end; The spring sleeve is provided with a second threaded hole; The lead screw end of the adjusting rod passes through the first threaded hole and is threadedly engaged with the first threaded hole to form a transmission pair that can rotate relative to each other; The end of the lead screw of the adjusting rod is fastened to the second threaded hole, forming a rigid whole without relative rotation; By rotating the adjusting rod, the rigid assembly of the adjusting rod and the spring sleeve is driven to move axially, thereby compressing the spring inside the actuating cylinder.

2. The tooling according to claim 1, characterized in that, The lead screw end of the adjusting rod is provided with a segmented thread structure, with the front thread engaging with the first threaded hole and the rear thread fixing with the second threaded hole.

3. The tooling according to claim 1, characterized in that, The lower end face of the fixed end of the housing is provided with a positioning groove that matches the shape of the actuator housing.

4. The tooling according to claim 1, characterized in that, The lower end face of the spring sleeve is provided with an annular flange edge for compressing the spring.

5. The tooling according to claim 1, characterized in that, The handle end of the adjusting rod is provided with an anti-slip knurled pattern.

6. The tooling according to claim 1, characterized in that, The axial movement of the spring sleeve drives the internal locking sleeve of the actuator cylinder to generate synchronous relative displacement with the external handle.

7. The tooling according to claim 1, characterized in that, The tooling is a detachable, modular structure, with each component connected only by threads.

8. The tooling according to any one of claims 1-7, characterized in that, The adjusting rod, the fixed end of the housing, and the spring sleeve are all made of hardened steel.

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