Operation tool for disassembling articulated shaft at position of aircraft landing gear actuator cylinder
By designing the C-shaped clamp workpiece and limit ring structure, combined with the gravity hammer and the sealing plate, the problem of difficulty in disassembling the articulated shaft of the small aircraft landing gear is solved, and the articulated shaft removal effect is achieved with convenient operation and labor-saving.
Patent Information
- Application Number
- CN202420984785.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-09
- Publication Date
- 2024-12-20
- Estimated Expiration
- Not applicable · inactive patent
AI Technical Summary
During the maintenance process, the articulated shaft of the landing gear of the small aircraft is small and lacks special disassembly work equipment, which makes it difficult to disassemble, troublesome and time-consuming.
A clamp workpiece with a C-shaped structure is designed, equipped with a operating rod and a gravity hammer. Through the push-pressing force-bearing part and limit ring structure of the clamp, it is embedded in a narrow space to surround the articulation shaft and apply it by a gravity hammer. The impact force causes the hinge shaft to exit the hinge shaft hole on the hinge seat, and combines a removable sealing plate to prevent falling off.
It realizes easy disassembly of the articulated shaft at the landing gear actuator of the small aircraft, which is convenient to operate, low difficulty, time and effort, and reduces the risk of damage to the articulated shaft during the disassembly.
Smart Images
Figure CN222200388U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to an operating tool for aircraft maintenance, in particular to an operating tool for disassembling an articulated shaft at an actuating cylinder of a landing gear of a small aircraft. Background Art
[0002] The Cernas aircraft is a common training aircraft or business aircraft. The landing gear actuator cylinder is hinged to the support frame through an articulated seat, that is, the landing gear actuator cylinder is connected to an articulated seat, and the articulated seat is articulated with the bottom end of the support frame through an articulated shaft. Since the distance between the articulated seat and the actuator cylinder is relatively close, the articulated shaft passes through the articulated seat and the support frame from the side away from the actuator cylinder. In order to avoid failure of the articulated structure, the articulated shaft is a special-shaped structure with an approximate L-shaped bend, and its bend end is away from the side of the actuator cylinder.
[0003] When the landing gear of a small aircraft is repaired, the articulated shaft is disassembled, and the disassembly is performed by applying force on the side close to the actuator to make the articulated shaft withdraw from the articulated shaft hole on the articulated seat.
[0004] However, due to the narrow space between the articulated seat and the actuator, it is impossible to form a large-scale structure arrangement, nor is it possible to form an open space for applying force. Due to the current lack of targeted special disassembly tooling, the disassembly of the articulated shaft at the articulated seat of the actuator is relatively difficult, resulting in technical problems such as cumbersome operation, time-consuming and labor-intensive. Utility Model Content
[0005] The technical purpose of the utility model is to provide an operating tool that can effectively adapt to the hinge structure at the actuator cylinder of the landing gear of the small aircraft and can easily realize the disassembly operation of the hinge shaft in view of the particularity of the hinge structure at the actuator cylinder of the landing gear of the small aircraft and the shortcomings of the existing technology.
[0006] The technical purpose of the utility model is achieved by the following technical scheme: an operating tool for disassembling an articulated shaft at an actuating cylinder of an aircraft landing gear, the operating tool having a C-shaped caliper body, an operating rod fixedly connected to one side of the open structure of the caliper body, and a gravity hammer sleeved on the operating rod;
[0007] One end of the operating rod away from the pliers body is connected to a force ring, and the force ring and the pliers body limit the movable stroke of the gravity hammer on the operating rod;
[0008] The end of the caliper body away from the operating rod is a pushing force-bearing part corresponding to the end of the pushing and disassembling hinge shaft, and the thickness of the pushing force-bearing part of the caliper body is less than the minimum matching clearance between the hinge shaft and the actuator cylinder;
[0009] When the hinge shaft at the actuating cylinder of the aircraft landing gear is disassembled, the caliper body axially surrounds the hinge shaft at the actuating cylinder with an open structure, the operating rod extends on the side away from the actuating cylinder, the gravity hammer exerts an impact force on the force-bearing ring on the operating rod, and the pushing force-bearing part of the caliper body pushes the corresponding end of the hinge shaft to make the hinge shaft retreat in and out of the installation hole.
[0010] The above technical measures are aimed at the particularity of the hinged structure at the actuator cylinder of the landing gear of the above-mentioned small aircraft. The clamp body with a C-shaped structure can be effectively embedded in the narrow space at the end of the hinge seat at the actuator cylinder, forming a surround for the hinge shaft installed on the hinge seat and pulling the force under the action of the operating rod. The gravity hammer connected to the operating rod can push the hinge shaft through the clamp body to make it withdraw from the hinge shaft hole on the hinge seat under the impact. Therefore, the above technical measures have reliable adaptability to the hinged structure at the actuator cylinder of the landing gear of the small aircraft, forming a special tool with strong pertinence, which can easily realize the disassembly operation of the hinge shaft at the actuator cylinder, and has the technical characteristics of convenient operation, low difficulty, time saving and labor saving.
[0011] The hinge shaft at the actuating cylinder is a bent structure, and in the connection structure with the actuating cylinder, the bent end of the hinge shaft is away from the actuating cylinder;
[0012] Correspondingly, a limit ring is fixedly connected in the caliper body, and the limit ring is close to the operating rod in the caliper body;
[0013] The end of the limiting ring close to the operating rod is provided with an avoidance hole for the bent end of the hinge shaft to pass through.
[0014] The above technical measures are aimed at the particularity of the hinged structure at the actuator cylinder of the landing gear of the above-mentioned small aircraft. The hinged shaft of the special-shaped structure with an approximate L-shaped bend is limited by a limiting ring in the embedded body. On the one hand, the disassembly tooling is limited to reduce the displacement of the tooling during the disassembly operation. On the other hand, it can effectively reduce the damage of the hinged shaft of the special-shaped structure with an approximate L-shaped bend due to external force impact during disassembly.
[0015] The avoidance hole is a long strip structure, formed on the circumference of the limit ring near one end of the operating rod;
[0016] The avoidance hole is formed at a position on the limit ring to avoid the clamp body. This technical measure is aimed at the particularity of the approximately L-shaped articulated shaft. A long strip-shaped limit hole is provided on the limit ring to avoid the clamp body. When the articulated shaft is disassembled, the articulated shaft can be easily inserted into the limit hole, and the operation is simple.
[0017] The opening of the clamp body is provided with a limiting flange with an inwardly folded structure in the opening direction;
[0018] The width of the open structure formed by the limiting flange is greater than the width of the hinge shaft installation position at the actuator.
[0019] The above-mentioned technical measures are reliably adaptable to the articulated structure at the actuator cylinder of the landing gear of small aircraft, forming a special tooling with strong pertinence, which can easily realize the disassembly operation of the articulated shaft at the actuator cylinder, and has the technical characteristics of convenient operation, low difficulty, time saving and labor saving.
[0020] A sealing plate is detachably connected to the outside of the open structure of the clamp body by a screw connection structure;
[0021] When the hinged shaft at the actuating cylinder of the aircraft landing gear is disassembled, the caliper body surrounds the hinged shaft at the actuating cylinder in the axial direction with an open structure, and a detachably connected sealing plate seals the open structure of the caliper body. The sealing plate cooperates with the caliper body to form a circumferential surround of the hinged shaft at the actuating cylinder in the axial direction.
[0022] The articulated shaft disassembly tool of the above-mentioned technical measure is provided with a removable sealing plate at the open part, and the sealing plate cooperates with the pliers body to form a circumferential surround of the articulated shaft at the actuator cylinder in the axial direction, further preventing the articulated shaft from falling off during the disassembly process or the articulated shaft disassembly position from falling off. It is targeted at the disassembly of the articulated shaft of the above-mentioned aircraft, and has good protection for the articulated shaft. It has reliable adaptability to the articulated structure at the actuator cylinder of the landing gear of small aircraft, forming a highly targeted special tool.
[0023] The pliers body is used as the pushing force bearing part of the corresponding end of the pushing articulated shaft, and is a flat plate structure, and the width of the pushing force bearing part is greater than the diameter of the corresponding end of the articulated shaft. This technical measure makes the bottom of the articulated shaft and the pushing force bearing part fit more closely during the disassembly of the articulated shaft, reducing the possibility of impact damage to the articulated shaft during disassembly.
[0024] The stress ring is a nut connected to the operating rod by a threaded structure or a welded structure;
[0025] The outer diameter of the nut is greater than the inner diameter of the gravity hammer;
[0026] The gravity hammer is freely installed on the operating rod through the inner hole with a movable clearance fitting structure.
[0027] The articulated shaft disassembly tooling of the above technical measures is convenient to assemble, has a simple structure, is easy to form, and has low cost.
[0028] The aircraft is a Cyrus trainer aircraft or a business jet.
[0029] The beneficial technical effect of the utility model is that the utility model has reliable adaptability to the hinged structure of the actuator cylinder of the landing gear of small aircraft, forming a special tool with strong pertinence, and the disassembly operation of the hinged shaft at the actuator cylinder can be easily realized, and it has the technical characteristics of convenient operation, low difficulty, time saving and labor saving. BRIEF DESCRIPTION OF THE DRAWINGS
[0030] Figure 1 It is a structural schematic diagram of the utility model.
[0031] Figure 2 It is the left view of the utility model.
[0032] Figure 3 This is a cross-sectional view of the working principle of the utility model.
[0033] The meaning of the codes in the figure are: 1—clamp body; 11—pushing force-bearing part; 12—flange; 2—operating rod; 3—gravity hammer; 4—force ring; 5—hinge shaft; 6—limiting ring; 61—avoidance hole; 7—sealing plate. DETAILED DESCRIPTION
[0034] The utility model relates to an operating tool for aircraft maintenance, specifically an operating tool for disassembling a hinged shaft at an actuating cylinder of a landing gear of a small aircraft. Figure 1 , Figure 2 and Figure 3 The technical solution of the utility model is clearly and in detail explained.
[0035] It should be noted that the drawings of the present invention are schematic, and unnecessary details have been simplified to clarify the technical purpose of the present invention, so as to avoid blurring the technical solution of the present invention in the prior art. In addition, the expressions "approximately" and "substantially" in the following text regarding quantity or matching relationship mean that reasonable assembly errors and processing errors in the industry are allowed to exist, and do not literally express absolute quantity or matching relationship.
[0036] See also Figure 1 , Figure 2 and Figure 3 As shown, a work tool for disassembling the hinge shaft at the actuator cylinder of a small aircraft landing gear includes a caliper body 1, an operating rod 2, a gravity hammer 3 and a force ring 4.
[0037] Specifically, the tooling has a pliers body 1 with an approximately C-shaped structure; the opening of the pliers body 1 with the C-shaped structure has a limiting flange 12 with an inward folding structure in the opening direction, and the width of the opening structure formed by the limiting flange 12 is larger than the width of the installation position of the hinge shaft 5 at the actuator cylinder; the limiting flange 12 has a connecting hole for connecting a detachable sealing plate 7, and the detachable sealing plate 7 is connected by screws.
[0038] When disassembling the articulated shaft 5 at the actuator cylinder of the landing gear of a small aircraft (such as a Cyrus trainer or business jet), the caliper body 1 axially surrounds the articulated shaft 5 at the actuator cylinder with an open structure, and the detachably connected sealing plate 7 seals the open structure of the caliper body 1. The sealing plate 7 cooperates with the caliper body 1 to form a circumferential surround of the articulated shaft 5 at the actuator cylinder in the axial direction, which has reliable adaptability to the articulated structure at the actuator cylinder of the landing gear of the small aircraft and reduces the technical difficulty of the disassembly operation of the articulated shaft 5 at the actuator cylinder.
[0039] The corresponding end of the caliper body 1 used for pushing the articulated shaft 5 is provided with a push-up force-bearing part 11 of a flat plate structure, the width of the push-up force-bearing part 11 is greater than the diameter of the corresponding end of the articulated shaft 5, and the thickness of the push-up force-bearing part 11 is less than the minimum matching clearance between the articulated shaft 5 and the actuator cylinder. When the caliper body 1 of a C-shaped structure is embedded in the articulated seat at the actuator cylinder of the landing gear of a small aircraft, the bottom end of the articulated shaft 5 can fit with the push-up force-bearing part 11 of the flat plate structure in the caliper body 1, reducing the risk of damage to the articulated shaft 5 due to uneven force during disassembly.
[0040] A limit ring 6 is fixedly connected inside the pliers body 1, and the limit ring 6 is close to the operating rod 2 inside the pliers body 1; at the end of the limit ring 6 close to the operating rod 2, an avoidance hole 61 of a long strip structure formed in the limit ring 6 close to one end of the operating rod 2 is avoided from the pliers body 1 for the installation of the bent end of the articulated shaft 5. This facilitates the installation of the articulated shaft 5 on the limit ring 6 of the disassembly tool during disassembly and assembly, and can not only limit the working area of the disassembly tool, but also protect the bent part of the articulated shaft 5 from damage due to external force impact.
[0041] An operating rod 2 and a gravity hammer 3 mounted on the operating rod 2 are fixed to one side of the open structure of the pliers body 1; the gravity hammer 3 is cylindrical and is freely installed on the operating rod 2 through an inner hole with a movable clearance fit structure, and the end of the operating rod 2 away from the pliers body 1 is connected to a force ring 4 connected with a threaded structure or a welding structure; the force ring 4 is a nut on the operating rod 2, and the outer diameter of the nut of the force ring 4 is larger than the inner diameter of the gravity hammer 3; the force ring 4 and the pliers body 1 limit the movable stroke of the gravity hammer 3 on the operating rod 2.
[0042] When disassembling the hinge shaft at the actuator cylinder of the landing gear of a small aircraft, the caliper body 1 surrounds the hinge shaft 5 at the actuator cylinder in the axial direction with an open structure, and the bottom end of the hinge shaft 5 fits the push force-bearing part 11 of the flat plate structure inside the caliper body 1. The gravity hammer 3 on the operating rod 2 applies an impact force to the force ring 4 in the axial direction of the operating rod 2, and the push force-bearing part 11 of the caliper body 1 pushes the corresponding end of the hinge shaft 5, so that the hinge shaft 5 retreats in and out of the installation hole.
[0043] The hinge shaft 5 at the actuating cylinder is a bent structure. In the connection structure with the actuating cylinder, the bent end of the hinge shaft 5 is away from the actuating cylinder.
[0044] The above-mentioned aircraft are Cyrus trainer aircraft or business jets.
[0045] The above specific technical solutions are only used to illustrate the present invention, rather than to limit it.
[0046] Although the present invention has been described in detail with reference to the above-mentioned specific technical solutions, those skilled in the art should understand that they can still modify the above-mentioned specific technical solutions, or make equivalent replacements for some of the technical features therein; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the present invention.
Claims
1. A tool for disassembling the hinge shaft at the actuating cylinder of an aircraft landing gear, characterized in that: The working tool comprises a pliers body (1) of a C-shaped structure, an operating rod (2) fixedly connected to one side of the open structure of the pliers body (1), and a gravity hammer (3) sleeved on the operating rod (2); One end of the operating rod (2) away from the pliers body (1) is connected to a force ring (4), and the force ring (4) and the pliers body (1) limit the movable stroke of the gravity hammer (3) on the operating rod (2); One end of the pliers body (1) away from the operating rod (2) is a push force receiving portion (11) corresponding to the end of the push-disassembly hinge shaft (5), and the thickness of the push force receiving portion (11) of the pliers body (1) is smaller than the minimum fitting clearance between the hinge shaft (5) and the actuator; When disassembling the hinge shaft at the actuating cylinder of an aircraft landing gear, the caliper body (1) surrounds the hinge shaft (5) at the actuating cylinder in the axial direction with an open structure, the operating rod (2) extends on a side away from the actuating cylinder, the gravity hammer (3) exerts an impact force on the force ring (4) on the operating rod (2), and the pushing force-bearing portion (11) of the caliper body (1) pushes the corresponding end of the hinge shaft (5) to cause the hinge shaft (5) to retreat inside and outside the installation hole.
2. The tooling for disassembling the hinge shaft at the actuating cylinder of an aircraft landing gear according to claim 1, characterized in that: The hinge shaft (5) at the actuating cylinder is a bent structure, and in the connection structure with the actuating cylinder, the bent end of the hinge shaft (5) is away from the actuating cylinder; Correspondingly, a limit ring (6) is fixedly connected inside the pliers body (1), and the limit ring (6) is located inside the pliers body (1) close to the operating rod (2); The end of the limiting ring (6) close to the operating rod (2) is provided with an avoidance hole (61) for the bent end of the hinge shaft (5) to pass through.
3. The tooling for disassembling the hinge shaft at the actuating cylinder of an aircraft landing gear according to claim 2, characterized in that: The avoidance hole (61) is a long strip structure, formed on the circumference of the limiting ring (6) close to one end of the operating rod (2); Furthermore, the avoidance hole (61) is formed at a position on the limiting ring (6) to avoid the clamp body (1).
4. The tooling for disassembling the hinge shaft at the aircraft landing gear actuator according to claim 1 or 2, characterized in that: The opening of the clamp body (1) is provided with a limiting flange (12) with an inwardly folded structure in the direction of the opening; The width of the open structure formed by the limiting flange (12) is greater than the width of the installation position of the hinge shaft (5) at the actuator.
5. The tooling for disassembling the hinge shaft at the actuating cylinder of an aircraft landing gear according to claim 4, characterized in that: A sealing plate (7) is detachably connected to the outside of the open structure of the clamp body (1) by means of a screw connection structure; When the hinged shaft (5) at the actuating cylinder of the aircraft landing gear is disassembled, the caliper body (1) surrounds the hinged shaft (5) at the actuating cylinder in the axial direction with an open structure, and a detachably connected sealing plate (7) seals the open structure of the caliper body (1), and the sealing plate (7) cooperates with the caliper body (1) to form a circumferential surround of the hinged shaft (5) at the actuating cylinder in the axial direction.
6. The tooling for disassembling the hinge shaft at the aircraft landing gear actuator according to claim 1, 2 or 5, characterized in that: The pliers body (1) is used as a pushing force-bearing portion (11) corresponding to the end of the pushing hinge shaft (5), and is a flat plate structure, and the width of the pushing force-bearing portion (11) is greater than the diameter of the corresponding end of the hinge shaft (5).
7. The tooling for disassembling the hinge shaft at the actuating cylinder of an aircraft landing gear according to claim 1, characterized in that: The stress ring (4) is a nut connected to the operating rod (2) by a threaded structure or a welded structure; The outer diameter of the nut is greater than the inner diameter of the gravity hammer (3); The gravity hammer (3) is freely mounted on the operating rod (2) through the inner hole with a movable clearance fit structure.
8. The tooling for disassembling the hinge shaft at the actuating cylinder of an aircraft landing gear according to claim 1, characterized in that: The aircraft is a Cyrus trainer aircraft or a business jet.