Aircraft engine quick support positioning bracket

Abstract

The utility model is suitable for equipment storage and transportation device field provides a kind of aircraft engine quick support positioning bracket, including bracket body, two first support components and two second support components;First support component and second support component can be adjusted position in the top of bracket body, and the position of first support component and second support component can be fixed by bolt;Two first support components and two second support components are respectively arranged in the top of bracket body close to longitudinal direction both ends;The top of first support component is equipped with plug-in device;The top of first support component is equipped with roller seat, and pressure belt is installed between two roller seats.

Description

Technical Field

[0001] This utility model applies to the field of equipment support frames and provides a quick support and positioning bracket for aircraft engines. Background Technology

[0002] Due to the complexity and expense of aircraft engines, they require regular maintenance and repair during use. When an aircraft engine malfunctions or needs routine maintenance, it typically needs to be removed from the aircraft and stored properly. To ensure the engine's safety after removal, it must be placed on a special rack.

[0003] Specialized brackets provide necessary support and protection for engines, preventing damage during transportation and storage. Due to the wide variety of aircraft types, each aircraft's engine design, structure, and size differ, thus requiring different brackets for different types of engines.

[0004] In practical applications, multiple different types of racks are needed to meet the storage requirements of different aircraft engines. The use of these racks often involves frequent selection and transfer, especially when aircraft are under maintenance or multiple engines are used alternately. Due to the wide variety of rack types and the large size and weight of each rack, the allocation, transfer and storage of multiple racks often result in inconvenience and large space occupation. Utility Model Content

[0005] To address the aforementioned deficiencies, the present invention aims to provide a quick support and positioning bracket for aircraft engines, thereby solving the problems mentioned in the background art. The device includes a bracket body, two first support components, and two second support components. The positions of the first and second support components can be adjusted at the top of the bracket body, and their positions can be fixed by bolts.

[0006] Two first support components and two second support components are respectively disposed on the top of the bracket body near both ends in the longitudinal direction; a plug-in device is installed on the top of the first support component; a roller seat is installed on the top of the first support component, and a pressure bearing belt is installed between the two roller seats.

[0007] Furthermore, longitudinal slide rail assemblies are installed on both sides of the top of the bracket body, and longitudinal slide tables are installed on the top of each of the two longitudinal slide rail assemblies. Transverse slide rail assemblies are installed on the top of the longitudinal slide tables, and two transverse slide tables are slidably connected to the top of the transverse slide rail assemblies. The first support assembly and the second support assembly are respectively fixedly connected to the four transverse slide tables.

[0008] Furthermore, the transverse slide and the longitudinal slide are provided with screw holes, and the transverse slide rail assembly and the longitudinal slide rail assembly are provided with reserved holes. After the first support assembly or the second support assembly moves to the designated position, its position can be fixed by bolts.

[0009] Furthermore, the bracket body includes several transversely evenly arranged transverse support beams, the top of which is fixedly connected to a longitudinal support beam, and the longitudinal slide rail assembly is mounted on the longitudinal support beam.

[0010] Furthermore, several shims that provide support are installed at the bottom of the transverse support beam.

[0011] Furthermore, a support block is installed on the top of the transverse support beam, and the support block and the top of the longitudinal support beam are fixedly connected to the longitudinal slide rail assembly through a support plate.

[0012] Furthermore, the plug-in device includes a fixed base and a plug rod sleeved inside the fixed base; a plug is installed at the end of the plug rod away from the fixed base; the portion of the plug rod inside the fixed base is provided with an abutting part, and a compression spring is provided between the abutting part and the internal cavity of the fixed base.

[0013] Furthermore, the second support assembly is fixedly connected to the roller seat via a fixed base, and a pressure-bearing belt mounting roller is rotatably connected to the roller seat.

[0014] Furthermore, one end of the second support assembly away from the bracket body is hinged to one end of an adjusting screw, and the other end of the adjusting screw is hinged to a transverse slide.

[0015] Therefore, through the synergistic effect of the longitudinal and transverse slide rail assemblies, the device achieves multi-directional adjustability of the first and second support assemblies on the bracket body, enabling rapid adaptation to the length and width differences of different aircraft engines and significantly improving the versatility of the bracket. The precise docking design of the plug-in device and the mating plug allows for rapid positioning of the engine's first end during hoisting, eliminating the need for secondary manual calibration and greatly reducing labor costs and operational risks. The combined use of the pressure belt and roller seat effectively disperses the gravitational load on the engine's second end, and the reinforced structure formed by the adjusting screw significantly improves the overall stability and load-bearing capacity of the bracket. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the mounting structure of the aircraft engine on this device.

[0017] Figure 2 This is a schematic diagram of the device structure;

[0018] Figure 3 for Figure 2Enlarged view of the A-section structure;

[0019] Figure 4 for Figure 2 Enlarged view of the structure of section B;

[0020] Figure 5 This is a schematic diagram of the top structure of the first support component;

[0021] Figure 6 This is a cross-sectional view of the top structure of the first support component;

[0022] Figure 7 This is a schematic diagram of the top structure of the second support component;

[0023] In the diagram: 01-Engine first position end; 011-Matching insert block; 02-Engine second position end; 03-Hanger; 1-Bracket body; 11-Transverse support beam; 111-Shim; 112-Support block; 113-Support plate; 12-Longitudinal support beam; 2-First support assembly; 21-Fixed seat; 210-Compression spring; 211-Insertion rod; 2110-Abutting part; 212-Plug; 3-Second support assembly; 30-Adjusting screw; 31-Roller seat; 32-Pressure belt mounting roller; 4-Longitudinal slide rail assembly; 41-Longitudinal slide table; 5-Transverse slide rail assembly; 51-Transverse slide table. Detailed Implementation

[0024] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present utility model. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0025] It should be noted that, in the description of this utility model, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front end," "rear end," "head," "tail," etc., indicate the orientation or positional relationship 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. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0026] Furthermore, in the description of this utility model, unless otherwise explicitly specified and limited, the terms "connected" and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0027] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the scope of the present utility model.

[0028] This invention provides a positioning bracket fixture that enables rapid positioning of the engine on the bracket. It can be quickly adjusted and is applicable to different types of aircraft engine equipment, thereby significantly reducing labor costs. Furthermore, it greatly reduces the precision requirements when manufacturing the bracket, has strong versatility, and further reduces production costs.

[0029] See appendix Figure 1 For aircraft engines, including engine position 01 and engine position 02, a special gantry crane 03 is required for lifting operations during the transportation of the disassembled engine, so as to lift the aircraft engine onto a special bracket.

[0030] See Figure 1-7 The purpose of this utility model is to provide a quick-support positioning bracket for an aircraft engine, including a bracket body 1 located at the bottom and movable first support components 2 and second support components 3 on the bracket. The bracket body 1 is divided into a longitudinal direction and a transverse direction. The longitudinal direction is the length direction of the aircraft engine, and the transverse direction is the width direction of the aircraft engine. Two first support components 2 and two second support components 3 are each provided at the top of the bracket body 1. Two first support components 2 are arranged as a group and are located at the top of the bracket body 1 near the longitudinal direction; two second support components 3 are arranged as a group and are located at the other end of the top of the bracket body 1 near the longitudinal direction; the first support components 2 and the second support components 3 are respectively used to support the first engine end 01 and the second engine end 02 of the aircraft engine.

[0031] See appendix Figure 1 For the jack 03 used for lifting aircraft engines, the jack 03 includes an annular sling and a lifting link. The annular sling is fitted near the engine's second end 02 and supports the aircraft engine. The lifting link is hinged to a mating block 011 on the aircraft engine. See the appendix for details. Figure 5 and attached Figure 6The mating block 011 has a hinge at the top and an insertion hole on the side of the mating block 011 away from the aircraft engine. During hoisting, the workers can use the hinge on the mating block 011 to install and lift the engine's first end 2.

[0032] After the aircraft engine is lifted to the designated location using a hoisting device, the engine is secured using the quick-support positioning bracket for the aircraft engine placed at the designated location.

[0033] The top of the first support assembly 2 is fixedly connected with a plug-in device corresponding to the mating plug 011, and the plug-in device can be inserted into the plug hole of the mating plug 011; the top of the first support assembly 2 is fixedly connected with a roller seat 31, and a pressure belt for supporting the second end 02 of the engine is installed on the roller seat 31.

[0034] In actual use, the first support assembly 2 and the second support assembly 3 can be adjusted in position at the top of the bracket body 1, and their positions can be fixed by bolts. For details, please refer to the appendix. Figure 2 and attached Figure 3 Taking the first support component 2 as an example: Longitudinal slide rail assemblies 4 are fixedly connected to both sides of the top of the bracket body 1. Each of the two longitudinal slide rail assemblies 4 has a longitudinal slide table 41 mounted on its top. A transverse slide rail assembly 5 is mounted on the top of each longitudinal slide table 41. Two transverse slide tables 51 are slidably connected to the top of each transverse slide rail assembly 5. The two first support components 2 are respectively fixedly connected to the two transverse slide tables 51. Thus, the longitudinal slide tables 41 can drive the two first support components 2 to move along the longitudinal direction of the bracket body 1. The transverse slide tables 51 and longitudinal slide tables 41 are provided with screw holes, and the transverse slide rail assemblies 5 and longitudinal slide rail assemblies 4 are provided with reserved holes. Therefore, after the first support component 2 moves to the designated position, its position can be fixed by bolts. The movement and fixing method of the second support component 3 is the same as that of the first support component 2, and will not be described in detail here.

[0035] Preferably, the bracket body 1 includes a plurality of transversely evenly arranged transverse support beams 11, and a longitudinal support beam 12 is fixedly connected to the top of the transverse support beams 11. The longitudinal slide rail assembly 4 is mounted on the longitudinal support beam 12 to provide better support for the longitudinal slide rail assembly 4.

[0036] Preferably, the bottom of the transverse support beam 11 is equipped with a plurality of support pads 111. The pads 111 are rigid foot pads, providing stronger friction.

[0037] Preferably, a support block 112 is fixedly connected to the top of the transverse support beam 11, and the top surface of the support block 112 is flush with the top surface of the longitudinal support beam 12. The tops of the support block 112 and the longitudinal support beam 12 are fixedly connected to the longitudinal slide rail assembly 4 through a support plate 113. Thus, the cooperation between the support block 112 and the support plate 113 can enhance the support of the longitudinal slide rail assembly 4 and prevent the transverse support beam 11 at the bottom from deforming under stress.

[0038] See appendix Figure 5 and attached Figure 6 Preferably, the insertion device at the top of the first support assembly 2 includes a fixed base 21 and an insertion rod 211 sleeved inside the fixed base 21. A plug 212 is fixedly connected to the end of the insertion rod 211 away from the fixed base 21; a contact portion 2110 is fixedly connected to the portion of the insertion rod 211 inside the fixed base 21, and a compression spring 210 is provided between the contact portion 2110 and the internal cavity of the fixed base 21. The compression spring 210 allows the insertion rod 211 to move and reset towards the mating insertion block 011. Specifically, the end of the insertion rod 211 away from the plug 212 protrudes from the fixed base 21. This end can be fitted with a gripping structure for personnel to operate the insertion rod 211 to retract, or it can be fitted with a hydraulic rod or other equipment to electrically control the retraction or extension of the insertion rod 211.

[0039] See appendix Figure 7 Preferably, the second support component 3 is fixedly connected to the roller seat 31 via the fixed seat 21, and the roller seat 31 is rotatably connected to the pressure belt mounting roller 32, on which one end of the pressure belt 32 can be installed.

[0040] See appendix Figure 2 Preferably, the end of the second support component 3 furthest from the bracket body 1 is hinged to one end of the adjusting screw 30, and the other end of the adjusting screw 30 is hinged to the transverse slide table 51. Thus, workers can assemble the second support component 3 on the transverse slide rail assembly 5 themselves, and by adjusting the length of the adjusting screw 30, the adjusting screw 30 forms a "supporting triangular reinforcement structure." When the bearing band is under stress, the second support component 3 experiences an inward component force. At this time, the adjusting screw 30 can provide tensile force, making the structure of the second support component 3 more stable and preventing structural deformation caused by prolonged support.

[0041] In summary, during actual use, first place the aircraft engine quick support positioning bracket in the designated parking area of ​​the aircraft engine, ensuring that the longitudinal direction of the bracket body 1 is consistent with the length direction of the aircraft engine; then, adjust the positions of the first support component 2 and the second support component 3 respectively through the longitudinal slide rail assembly 4 and the transverse slide rail assembly 5, so that they correspond to the first engine end 01 and the second engine end 02 of the aircraft engine to be supported; after the position adjustment is completed, use bolts to pass through the screw holes on the longitudinal slide table 41 and the transverse slide table 51, and lock them in the reserved holes of the longitudinal slide rail assembly 4 and the transverse slide rail assembly 5, thereby fixing the positions of the first support component 2 and the second support component 3; the above position adjustment steps only need to be adjusted once, and no further adjustments are required in subsequent uses. Next, using a specialized jack 03, the aircraft engine is hoisted onto the support frame and slowly lowered. The mating block 011 of the engine's first end 01 aligns with the insertion device on the top of the first support assembly 2. The insertion rod 211 automatically extends under the action of the compression spring 210, and the plug 212 inserts into the insertion hole of the mating block 011, achieving rapid positioning and fixation of the engine's first end 01. Simultaneously, the engine's second end 02 is pressed down onto the pressure belt supported by two roller seats 31 on the top of the second support assembly 3. The pressure belt 32 on the mounting roller 32 provides stable support for the engine's second end 02. This completes the rapid support and positioning process for the aircraft engine.

[0042] Thus, through the synergistic effect of the longitudinal slide rail assembly 4 and the transverse slide rail assembly 5, the device achieves multi-directional adjustability of the first support assembly 2 and the second support assembly 3 on the bracket body 1, which can quickly adapt to the differences in length and width of different types of aircraft engines, significantly improving the versatility of the bracket; the precise docking design of the plug-in device and the mating plug 011 enables the engine's first end 01 to be quickly positioned during hoisting without the need for secondary manual calibration, greatly reducing labor costs and operational risks; the combined use of the pressure belt and the roller seat 31 effectively disperses the gravitational load of the engine's second end 02, and the reinforced structure formed by the adjusting screw 30 significantly improves the overall stability and load-bearing capacity of the bracket.

[0043] Furthermore, the modular design of the slide rails and slide tables reduces the precision requirements in the bracket manufacturing process, simplifies the production process, and further reduces production costs, thus possessing broad application prospects and promotional value.

[0044] Of course, there may be other embodiments of this utility model. Without departing from the spirit and essence of this utility model, those skilled in the art can make various corresponding changes and modifications based on this utility model, but these corresponding changes and modifications should all fall within the protection scope of the appended claims of this utility model.

Claims

1. A quick-support positioning bracket for an aircraft engine, characterized in that, It includes a bracket body (1), two first support components (2) and two second support components (3); the first support components (2) and the second support components (3) can be adjusted in position on the top of the bracket body (1), and the positions of the first support components (2) and the second support components (3) can be fixed by bolts; Two first support components (2) and two second support components (3) are respectively located on the top of the bracket body (1) near both ends in the longitudinal direction; a plug-in device is installed on the top of the first support component (2); a roller seat (31) is installed on the top of the first support component (2), and a pressure bearing belt is installed between the two roller seats (31).

2. The aircraft engine quick-support positioning bracket according to claim 1, characterized in that, The bracket body (1) is equipped with longitudinal slide rail assemblies (4) on both sides of the top. The top of each of the two longitudinal slide rail assemblies (4) is equipped with a longitudinal slide table (41). The top of the longitudinal slide table (41) is equipped with a transverse slide rail assembly (5). The top of the transverse slide rail assembly (5) is slidably connected to two transverse slide tables (51). The first support assembly (2) and the second support assembly (3) are respectively fixedly connected to the four transverse slide tables (51).

3. The aircraft engine quick-support positioning bracket according to claim 2, characterized in that, The transverse slide (51) and the longitudinal slide (41) are provided with screw holes, and the transverse slide rail assembly (5) and the longitudinal slide rail assembly (4) are provided with reserved holes. After the first support assembly (2) or the second support assembly (3) moves to the designated position, its position can be fixed by bolts.

4. The aircraft engine quick-support positioning bracket according to claim 2, characterized in that, The bracket body (1) includes several transverse support beams (11) arranged evenly in the transverse direction. The top of the transverse support beams (11) is fixedly connected to a longitudinal support beam (12). The longitudinal slide rail assembly (4) is installed on the longitudinal support beam (12).

5. The aircraft engine quick-support positioning bracket according to claim 4, characterized in that, The bottom of the transverse support beam (11) is equipped with several support pads (111).

6. The aircraft engine quick-support positioning bracket according to claim 4, characterized in that, A support block (112) is installed on the top of the transverse support beam (11), and the top of the support block (112) and the longitudinal support beam (12) are fixedly connected to the longitudinal slide rail assembly (4) by a support plate (113).

7. The aircraft engine quick support and positioning bracket according to claim 1, characterized in that, The plug-in device includes a fixed base (21) and a plug rod (211) sleeved inside the fixed base (21); a plug (212) is installed at the end of the plug rod (211) away from the fixed base (21); the part of the plug rod (211) inside the fixed base (21) is provided with an abutment part (2110), and a compression spring (210) is provided between the abutment part (2110) and the cavity inside the fixed base (21).

8. The aircraft engine quick-support positioning bracket according to claim 7, characterized in that, The second support assembly (3) is fixedly connected to the roller seat (31) via a fixed seat (21), and a pressure belt mounting roller (32) is rotatably connected to the roller seat (31).

9. The aircraft engine quick-support positioning bracket according to claim 2, characterized in that, The second support assembly (3) is hinged to one end of an adjusting screw (30) at the end away from the bracket body (1), and the other end of the adjusting screw (30) is hinged to a transverse slide (51).

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