Hydraulic cylinder sealing element for aviation space shuttle

Abstract

The utility model relates to the technical field of hydraulic cylinder sealing pieces, in particular to a hydraulic cylinder sealing piece for an aviation space shuttle, which comprises a sleeving piece, a matching core sleeve and a mounting component, the mounting assembly comprises a driving plate, a sliding stop block, a driving screw rod, a driving component and a limiting component; the driving plate is slidably connected with the sleeving piece and located on one side of the sleeving piece, the sliding check block is fixedly connected with the driving plate and slidably installed on the side, close to the matched core sleeve, of the sleeving piece, the driving screw is in threaded connection with the driving plate and rotatably installed on one side of the sleeving piece, the driving component is connected with the driving screw, and the limiting component is connected with the sleeving piece. The replacement part used by the sealing part can be quickly disassembled and assembled through the arranged components, and the sealing part is more convenient to use in the actual using process.

Description

Technical Field

[0001] The utility model relates to the technical field of hydraulic cylinder sealing components, in particular to a hydraulic cylinder sealing component for an aerospace aircraft. Background Art

[0002] The hydraulic cylinder is an actuator that mainly converts hydraulic energy into mechanical energy. When the hydraulic cylinder is working, it is generally necessary to use seals to ensure the overall sealing of the hydraulic cylinder to avoid internal leakage that causes the system volumetric efficiency to be too low and the oil temperature to rise too high, so that the system cannot work normally. However, in actual use, the existing seals are easy to wear out on the outer ring after long-term operation due to their simple structure. Once part of the seal is worn out, it cannot be used normally and needs to be replaced as a whole, which increases the cost of use.

[0003] The existing authorized patent CN217129986U discloses a wear-resistant seal for a hydraulic cylinder. The corresponding core ring is installed through a provided groove. When wear occurs during operation, the outer side of the core ring is worn. When it is replaced later, only the core ring needs to be replaced, thereby reducing the practical cost of the entire seal.

[0004] However, when the above method is used to limit the installation of the core ring through the groove, if the groove depth is set too deep, it will cause difficulty in installing and removing the core ring. If the groove depth is set too shallow, it cannot ensure that the core ring is installed stably, which makes it very inconvenient in actual use. Utility Model Content

[0005] The utility model aims to provide a hydraulic cylinder seal for an aerospace aircraft, which can quickly disassemble and install a replacement part used for the seal through a provided component, making it more convenient in actual use.

[0006] To achieve the above-mentioned purpose, the utility model provides a hydraulic cylinder seal for an aerospace aircraft, including a sleeve member and a matching core sleeve, and also includes a mounting assembly;

[0007] The mounting assembly includes a driving plate, a sliding stopper, a driving screw, a driving member and a limiting member; the driving plate is slidably connected to the sleeve and is located on one side of the sleeve, the sliding stopper is fixedly connected to the driving plate and is slidably installed on a side of the sleeve close to the matching core sleeve, the driving screw is threadedly connected to the driving plate and is rotatably installed on one side of the sleeve, the driving member is connected to the driving screw, and the limiting member is connected to the sleeve.

[0008] Among them, the driving component includes a connecting bevel gear, a torque and a rotating bevel gear, the connecting bevel gear is fixedly connected to the driving screw and is located on one side of the driving screw; the torque is rotationally connected to the sleeve and is located on one side of the sleeve; the rotating bevel gear is meshed with the connecting bevel gear and is fixedly installed on one side of the torque.

[0009] The turning knob has a connecting truncated cone and a toggling boss, wherein the connecting truncated cone is located on a side of the turning knob close to the rotating bevel gear; and the toggling boss is located on one side of the turning knob.

[0010] Wherein, the limiting component includes a matching cover and a limiting rubber pad, the matching cover is connected to the sleeve and is located on a side of the sleeve close to the twist; the limiting rubber pad is fixedly connected to the sleeve and is located on a side of the sleeve close to the matching cover.

[0011] Among them, the matching cover has a limiting boss, a matching groove and a snap groove, the limiting boss is located on one side of the matching cover and passes through the twist knob and the sleeve; the matching groove is located on one side of the matching cover close to the twist knob; the snap groove is located on one side of the matching cover.

[0012] The utility model discloses a hydraulic cylinder seal for an aerospace aircraft, wherein the sleeve circular hole of the matching core sleeve is matched with the round table provided at the end of the sleeve part, and then the rotating bevel gear is driven to rotate by twisting the knob. When the rotating bevel gear rotates, the three connecting bevel gears can be driven by the rotating bevel gear to drive the three driving screws to rotate at the same time. When the corresponding driving screws rotate, the driving plate can drive the sliding block to move upward, and the side of the matching core sleeve can be limited by the upward movement of the sliding blocks at three places. The three sliding blocks are driven by the screw thread to move toward the inside of the sleeve part, thereby completing the storage of the three sliding blocks, so as to eliminate the limitation on the side of the mating core sleeve, so that the user can directly remove the mating core sleeve from the side cone of the sleeve part, thereby realizing the rapid disassembly and installation of the replacement parts used for the seal through the provided components, making it more convenient in actual use. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art are briefly introduced below.

[0014] Figure 1It is a schematic diagram of the overall structure of a hydraulic cylinder seal for an aerospace aircraft according to the first embodiment of the utility model.

[0015] Figure 2 It is a schematic structural diagram of the first embodiment of the utility model with the matching core sleeve removed.

[0016] Figure 3 It is a schematic diagram of the installation structure of the driving screw rod of the first embodiment of the utility model.

[0017] Figure 4 The first embodiment of the utility model Figure 3 Enlarged view of point A.

[0018] Figure 5 It is a schematic diagram of the overall structure of a hydraulic cylinder seal for an aerospace aircraft according to a second embodiment of the utility model.

[0019] Figure 6 It is a schematic structural diagram of the second embodiment of the utility model with the matching cover removed.

[0020] In the figure: 101-sleeve part, 102-matching core sleeve, 103-driving plate, 104-sliding block, 105-driving screw, 106-connecting bevel gear, 107-torque, 108-rotating bevel gear, 109-connecting round table, 110-sliding boss, 201-matching cover, 202-limiting rubber pad, 203-limiting boss, 204-matching groove, 205-clicking groove. DETAILED DESCRIPTION

[0021] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, but should not be understood as limiting the present invention.

[0022] The first embodiment of the present application is:

[0023] See also Figures 1 to 4 ,in Figure 1 This is a schematic diagram of the overall structure of hydraulic cylinder seals for aerospace aircraft. Figure 2 It is a schematic diagram of the structure with the core sleeve 102 removed. Figure 3 It is a schematic diagram of the structure with the core sleeve 102 removed. Figure 4 yes Figure 3 Enlarged view of point A.

[0024] The utility model provides a hydraulic cylinder seal for aerospace aircraft: it includes a sleeve 101, a matching core sleeve 102 and an installation component, the installation component includes a drive plate 103, a sliding block 104, a drive screw 105, a driving component and a limiting component, the driving component includes a connecting bevel gear 106, a twist 107 and a rotating bevel gear 108, the twist 107 has a connecting round table 109 and a toggle boss 110, and the above-mentioned scheme solves the problem that when the center ring is installed and limited by the groove, if the depth of the groove is set too deep, it will cause difficulty in installing and disassembling the center ring, and when the depth of the groove is set too shallow, it cannot be guaranteed that the center ring is not stable enough, which makes it very inconvenient in actual use.

[0025] In this embodiment, the sleeve 101 consists of a connecting truncated cone 109 and a limiting truncated cone on the back side. The truncated cone on the sleeve 101 matches the sleeve circular hole of the matching core sleeve 102, so that the user can directly install it on one side of the sleeve 101.

[0026] Among them, the driving plate 103 is slidably connected to the sleeve part 101 and is located on one side of the sleeve part 101, the sliding stopper 104 is fixedly connected to the driving plate 103 and slidably installed on the side of the sleeve part 101 close to the matching core sleeve 102, the driving screw 105 is threadedly connected to the driving plate 103 and rotatably installed on one side of the sleeve part 101, the driving member is connected to the driving screw 105, the limiting member is connected to the sleeve part 101, the driving plate 103 and the sliding stopper are provided with three groups in total, the driving plate 103 and the sliding stopper 104 match the sliding groove provided in the sleeve part 101, and the driving plate 103 is provided with a driving screw 105 The matching threaded holes enable the drive plate 103 to move under the drive of the drive screw 105 when the user drives the drive screw 105 to rotate through the corresponding mechanism, thereby facilitating the driving of the drive plate 103 and the sliding block 104, so as to control the limit of the side of the mating core sleeve 102 by driving the sliding block 104 up and down. When the sliding block 104 is completely moved down to the inside of the sliding groove provided on the sleeve 101, the mating core sleeve 102 can be directly taken down from the side where the sliding block 104 is installed, and when the sliding block 104 is moved up, the mating core sleeve 102 can be limited by the limiting cone on the side of the sleeve 101.

[0027] Secondly, the connecting bevel gear 106 is fixedly connected to the driving screw 105 and is located on one side of the driving screw 105; the turning knob 107 is rotationally connected to the sleeve 101 and is located on one side of the sleeve 101; the rotating bevel gear 108 is meshed with the connecting bevel gear 106 and is fixedly installed on one side of the turning knob 107, and the connecting frustum 109 is located on the side of the turning knob 107 close to the rotating bevel gear 108; the toggle boss 110 is located on one side of the turning knob 107, and the three ends of the driving screws 105 provided inside the sleeve 101 are fixedly installed with the connecting bevel gear 106. The connecting bevel gear 106 is meshed with the rotating bevel gear 108 at the same time. The rotating bevel gear 108 is fixed on the connecting circular table 109 on the inner side of the turning knob 107. The outer side of the turning knob 107 is provided with a rectangular toggle boss 110 so that the user can drive the turning knob 107 to rotate through the toggle boss 110 on the outer side of the turning knob 107. When the turning knob 107 is rotated, the rotating bevel gear 108 can be driven by the turning knob 107, thereby driving the three connecting bevel gears 106 and the driving screw 105 at the same time, so as to drive the three groups of driving plates 103 and the sliding block 104.

[0028] When the hydraulic cylinder seal for an aerospace aircraft of the present embodiment is in use, the sleeve circular hole of the matching core sleeve 102 is matched with the round table provided at the end of the sleeve part 101, and then the rotating bevel gear 108 is driven to rotate by twisting the knob 107. When the rotating bevel gear 108 rotates, the three connecting bevel gears 106 can be driven by the rotating bevel gear 108 to drive the three driving screws 105 to rotate at the same time. When the corresponding driving screw 105 rotates, the driving plate 103 can drive the sliding block 104 to move upward, and the matching core sleeve can be moved upward by moving the sliding blocks 104 at three places. The side of the mating core sleeve 102 is limited and clamped, thereby completing the installation of the mating core sleeve 102. When the mating core sleeve 102 needs to be disassembled, it is only necessary to reversely twist the knob 107 so that the three sliding blocks 104 can be driven by the above-mentioned mechanism to move toward the inside of the sleeve 101 to complete the storage of the three sliding blocks 104, so as to eliminate the limitation on the side of the mating core sleeve 102, so that the user can directly remove the mating core sleeve 102 from the side cone of the sleeve 101, thereby realizing the ability to quickly disassemble and install the replacement parts used for the seal through the provided components, making it more convenient in actual use.

[0029] Second embodiment:

[0030] See also Figure 5 and Figure 6 , Figure 5 This is a schematic diagram of the overall structure of a hydraulic cylinder seal for an aerospace aircraft according to a second embodiment. Figure 6 This is a schematic structural diagram of the second embodiment with the matching cover 201 removed. The limiting component provided by the utility model includes a matching cover 201 and a limiting rubber pad 202. The matching cover 201 has a limiting boss 203, a matching groove 204 and a buckling groove 205.

[0031] Among them, the matching cover 201 is connected to the sleeve 101 and is located on a side of the sleeve 101 close to the twist 107; the limiting rubber pad 202 is fixedly connected to the sleeve 101 and is located on a side of the sleeve 101 close to the matching cover 201, the limiting boss 203 is located on one side of the matching cover 201 and passes through the twist 107 and the sleeve 101; the matching groove 204 is located on a side of the matching cover 201 close to the twist 107; the buckling groove 205 is located on one side of the matching cover 201, the matching groove 204 provided on the matching cover 201 matches the shape of the dialing boss 110 on the outer side of the twist 107, and two limiting bosses 203 are also provided on the inner side of the matching cover 201, and the twist 107 and the sleeve 101 are installed. The inner side of the groove of the twist 107 is provided with a through hole matching the limiting boss 203, When the through hole of the knob 107 coincides with the through hole in the groove of the knob 107, the user can fix the knob 107 on one side of the sleeve 101 by installing the matching cover 201, and then limit the knob 107 accordingly. At the same time, the outer side of the matching cover 201 is also provided with a corresponding buckling groove 205, so that the user can drive the entire matching cover 201 through the buckling groove 205. In order to limit the installation position of the matching cover 201, the limiting rubber pad 202 is fixed to the outer end of the matching groove 204 where the matching cover 201 is installed, and then the end of the matching cover 201 after installation can be limited by the limiting rubber pad 202. When the matching cover 201 needs to be removed, it is only necessary to drive the matching cover 201 outward, and then the matching cover 201 is disassembled by squeezing the limiting rubber pad 202 to deform.

[0032] When using a hydraulic cylinder seal for an aerospace aircraft according to the present embodiment, the turning knob 107 can be sleeved and matched by the matching cover 201, and then the turning knob 107 can be limited by the matching of the limiting boss 203 with the sleeve 101 and the through hole of the turning knob 107, and the matching groove 204 with the toggle boss 110 at the outer end of the turning knob 107, thereby ensuring the stability of the position of the sliding stopper 104 when clamping and fixing the matching core sleeve 102, and the stability of the matching position of the matching cover 201 can also be ensured by the limiting rubber pad 202, thereby greatly enhancing the practicality of the entire device.

[0033] What is disclosed above is only one or more preferred embodiments of the present application, and cannot be used to limit the scope of rights of the present application. Ordinary technicians in this field can understand that all or part of the processes of implementing the above embodiments and equivalent changes made according to the claims of the present application are still within the scope covered by the present application.

Claims

1. A hydraulic cylinder seal for an aerospace aircraft, comprising a sleeve and a matching core sleeve, characterized in that: Also included are mounting components; The mounting assembly includes a driving plate, a sliding stopper, a driving screw, a driving member and a limiting member; the driving plate is slidably connected to the sleeve and is located on one side of the sleeve, the sliding stopper is fixedly connected to the driving plate and is slidably installed on a side of the sleeve close to the matching core sleeve, the driving screw is threadedly connected to the driving plate and is rotatably installed on one side of the sleeve, the driving member is connected to the driving screw, and the limiting member is connected to the sleeve.

2. The hydraulic cylinder seal for an aerospace aircraft according to claim 1, characterized in that: The driving component includes a connecting bevel gear, a torque and a rotating bevel gear. The connecting bevel gear is fixedly connected to the driving screw and is located on one side of the driving screw; the torque is rotationally connected to the sleeve and is located on one side of the sleeve; the rotating bevel gear is meshed with the connecting bevel gear and is fixedly installed on one side of the torque.

3. The hydraulic cylinder seal for an aerospace aircraft according to claim 2, characterized in that: The turning knob has a connecting truncated cone and a toggling boss. The connecting truncated cone is located on a side of the turning knob close to the rotating bevel gear; and the toggling boss is located on one side of the turning knob.

4. The hydraulic cylinder seal for an aerospace aircraft according to claim 2, characterized in that: The limiting component includes a matching cover and a limiting rubber pad. The matching cover is connected to the sleeve and is located on a side of the sleeve close to the twisting wheel. The limiting rubber pad is fixedly connected to the sleeve and is located on a side of the sleeve close to the matching cover.

5. The hydraulic cylinder seal for an aerospace aircraft according to claim 4, characterized in that: The matching cover has a limiting boss, a matching groove and a snap groove. The limiting boss is located on one side of the matching cover and passes through the twist knob and the sleeve. The matching groove is located on one side of the matching cover close to the twist knob. The snap groove is located on one side of the matching cover.

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