Engine rear hanging device under spatial constraint

Abstract

The utility model belongs to the technical field of airplane design, and relates to an engine rear suspension device under space constraint, which comprises a first joint bearing, an airplane support arranged outside an outer ring of the first joint bearing, a bearing end cover arranged at the top of the outer ring of the first joint bearing, and after the airplane support is connected with the bearing end cover, the outer ring of the first joint bearing is fixed on an airplane. A sleeve is arranged in an inner ring of the first knuckle bearing, a sleeve nut is arranged on an outer cylinder at the bottom of the sleeve and makes contact with the bottom of the inner ring of the first knuckle bearing, a pull rod is arranged in the sleeve and is in threaded connection with the inner wall face of the sleeve, and a second knuckle bearing is arranged at the bottom end of the pull rod and connected with an engine installation base. By means of the characteristics of the knuckle bearing, the engine installation feasibility under spatial constraint is guaranteed, and the requirement for the movement clearance of the engine is also guaranteed. The requirement for installation and adjustment of the engine is met by designing a thread movement assembly, and meanwhile the reliability of the system is guaranteed through a locking snap ring mechanism.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft design technology and relates to an engine rear-mounted device under space constraints. Background Technology

[0002] Due to differences in engine type and overall aircraft power plant layout, the installation location of engines varies on aircraft, resulting in diverse installation methods. Even the same type of engine installed on different aircraft will have different, sometimes drastically, installation methods. Engines installed within the fuselage mostly adopt a supported mounting method. The engine consists of a main mounting section and auxiliary tie rods (or struts) fixed to the aircraft's reinforcing frame, and is fixed in the engine nacelle or nacelle. The main mounting section bears forces and moments in the x, y, and z directions, while the auxiliary tie rods (or struts) only bear forces and moments in the y direction. The joints or lugs at both ends of the tie rods (or struts) can be length adjusted. The joints or lugs are made in the form of hinges or ball joints that can move freely along the x-axis (or z-axis).

[0003] During the iterative design process, the combination of aircraft mission requirements, internal space, and engine development status may lead to space requirements for engine installation. Common auxiliary struts (or braces) designed to meet engine installation requirements include ball joints, strut connectors, and length adjustment mechanisms. For example, a strut designed for a 2500 kgf thrust engine has a length of approximately 130 mm. When internal space is insufficient, especially for engines with higher thrust requiring larger struts, common auxiliary strut mechanisms are no longer adequate. To address the extremely demanding space requirements for engine installation auxiliary struts, a space-constrained engine auxiliary installation device needs to be proposed that can both meet engine installation requirements and facilitate maintenance. Utility Model Content

[0004] The purpose of this invention is to provide an engine auxiliary installation device that meets engine installation requirements, has high reliability, is easy to maintain, and can solve space constraints.

[0005] The technical solution of this utility model:

[0006] A space-constrained engine rear mounting device includes a first spherical bearing, an aircraft support mounted on the outer ring of the first spherical bearing, a bearing end cap mounted on the top of the outer ring of the first spherical bearing, and the connection between the aircraft support and the bearing end cap to fix the outer ring of the first spherical bearing onto the aircraft. A sleeve is disposed in the inner ring of the first spherical bearing, and a sleeve nut is disposed on the outer cylinder at the bottom of the sleeve, the sleeve nut contacting the bottom of the inner ring of the first spherical bearing. A pull rod is disposed inside the sleeve and threadedly connected to the inner wall of the sleeve. A second spherical bearing is disposed at the bottom end of the pull rod and is connected to the engine mounting base.

[0007] Furthermore, the aircraft support and bearing end cap are used to fix the outer ring of the spherical plain bearing onto the aircraft via threaded connections.

[0008] Furthermore, a stop washer mounting groove is provided at the top of the pull rod, and a stop washer is installed in the stop washer mounting groove, with the stop washer engaging with the internal thread of the inner wall of the sleeve.

[0009] Furthermore, a lock nut is installed on the tie rod, which is located at the top of the sleeve and in contact with the lock nut.

[0010] Furthermore, safety holes are provided on the bearing end cover, aircraft support, sleeve, sleeve nut, lock nut, and tie rod. A fuse is installed between the safety holes of the bearing end cover and the aircraft support, between the safety holes of the sleeve and the sleeve nut, and between the safety hole of the lock nut and the tie rod.

[0011] Furthermore, a tool groove is provided on the upper surface of the bearing end cover along the circumferential direction, and a tool can be inserted into the tool groove to rotate the bearing end cover.

[0012] Furthermore, the bottom of the pull rod has a lifting ring structure, and the second joint bearing is embedded in the lifting ring structure.

[0013] Furthermore, the internal cavity of the sleeve includes an upper smooth rod section and a lower threaded section. The inner diameter of the smooth rod section is larger than that of the threaded section. The locking washer is clearance-fitted with the cavity of the smooth rod section, allowing it to move up and down within the cavity. The locking washer is threaded with the inner wall of the threaded section, restricting the up and down movement of the pull rod.

[0014] Beneficial effects of this utility model

[0015] This utility model proposes an engine rear-mounted device under spatial constraints.

[0016] This invention utilizes the characteristics of spherical bearings to ensure both the feasibility of engine installation under space constraints and the required clearance for engine movement. The design of a threaded motion component fulfills the engine installation and adjustment needs, while a retaining circlip mechanism ensures the system's reliability.

[0017] This invention realizes the design of an engine auxiliary device under space constraints, meets all the requirements of engine auxiliary installation devices, and has the following advantages compared with common auxiliary installation devices:

[0018] 1) Extremely low space requirements;

[0019] 2) The anti-detachment device is simple and effective, improving the safety of engine installation and fixing; it can quickly adjust the engine installation, improving engine maintainability. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the device structure of this utility model;

[0021] Figure 2 This is a schematic diagram of the bearing end cover of the device of this utility model. Figure 1 ;

[0022] Figure 3 This is a schematic diagram of the bearing end cover of the device of this utility model. Figure 2 ;

[0023] Figure 4 This is a schematic diagram of the sleeve of the utility model device. Figure 1 ;

[0024] Figure 5 This is a schematic diagram of the sleeve of the utility model device. Figure 2 ;

[0025] Figure 6 This is a schematic diagram of the pull rod of the utility model device. Figure 1 ;

[0026] Figure 7 This is a schematic diagram of the pull rod of the utility model device. Figure 2 ;

[0027] Figure 8 This is a schematic diagram of the swinging lever of the device of this utility model. Figure 1 ;

[0028] Figure 9 This is a schematic diagram of the swinging lever of the device of this utility model. Figure 2 ;

[0029] Figure 10 This is a flowchart of the assembly and installation process of the device of this utility model;

[0030] Among them, 1-Aircraft support; 2-Spherical plain bearing; 3-Bearing end cap; 4-Sleeve; 5-Sleeve nut; 6-Tie rod; 7-Spherical plain bearing; 8-Locking nut; 9-Stabilizing ring; 10-Engine support; 11-Safety hole; 12-Tool slot; 13-External thread; 14-Internal thread; 15-Stabilizing washer slot. Detailed Implementation

[0031] One embodiment of this utility model is an auxiliary installation device, which consists of an aircraft support, an engine support, a spherical bearing, a tie rod, and a threaded assembly.

[0032] The aircraft support 1 and bearing end cap 3 are threaded together to secure the outer ring of the spherical plain bearing 2 to the aircraft. The sleeve 4 passes through the inner ring of the spherical plain bearing 2, and its bottom is fixed to the inner ring of the spherical plain bearing 2 by the sleeve nut 5. The pull rod 6, which has a locking washer groove 15 with a locking washer 9 at the top, is threaded together with the sleeve 4. The other end of the pull rod 6 is embedded in the spherical plain bearing 7 and mates with the engine mounting bracket 10. After the engine is installed in place, the lock nut 8 and all safety devices are tightened.

[0033] Among them, the spherical plain bearing 2 mainly bears axial overload, and the spherical plain bearing 7 mainly bears radial overload.

[0034] By turning the socket 4 with a wrench, the threaded rod 6 is adjusted vertically to achieve the purpose of installing and adjusting the engine. Figure 2-3 .

[0035] The safety holes between the bearing end cover 3 and the aircraft support 1, the sleeve 4 and the sleeve nut 5, and the anti-loosening nut 8 and the engine mounting base 10 are secured with fuses to effectively prevent the threaded parts from loosening. The design of the common tie rod with lifting ring is optimized, and a locking washer 9 is added to the end for mounting groove (see 4). It is assembled with the sleeve 4 to prevent the risk of engine falling off due to loose threaded connection.

[0036] The tie rod 6, sleeve 4, sleeve nut 5, and inner ring of the spherical plain bearing 2 utilize the mobility of the spherical plain bearing to meet the deformation and unloading requirements during engine installation and operation. (See attached diagram.) Figure 8-9 .

[0037] This invention cleverly utilizes the characteristics of spherical bearings to ensure both the feasibility of engine installation under space constraints and the required clearance for engine movement. The design of a threaded motion component fulfills the engine installation and adjustment needs, while a retaining circlip mechanism ensures system reliability.

[0038] The second embodiment of this utility model is a proposed engine auxiliary installation scheme under spatial constraints, consisting of an aircraft support 1, a spherical bearing 2, a sleeve 4, a sleeve nut 5, and a tie rod 6, etc., see... Figure 1 .

[0039] Based on the overload design of the engine auxiliary mounting point, the specifications of spherical bearing 2 and spherical bearing 7 are selected. The aircraft support 1 and bearing end cap 3 are designed according to spherical bearing 2 to fix spherical bearing 2. The aircraft support 1 is designed according to the aircraft support structure and the connection method with the aircraft. The bearing end cap 3 is reserved with a safety hole to achieve safety with the aircraft support 1. The bottom of the aircraft support 1 is reserved with a peripheral clearance when the inner ring of spherical bearing 2 moves.

[0040] Sleeve 4 is embedded in the inner ring of spherical plain bearing 2, and the outer ring of sleeve 4 is connected to the inner ring of spherical plain bearing 2. The bottom of the outer ring of sleeve 4 is threaded for connecting sleeve nut 5, which is then assembled with the inner ring of spherical plain bearing 2. A safety connection is required between sleeve 4 and sleeve nut 5.

[0041] The dimensions of the tie rod 6 lifting ring are designed according to the dimensions of the spherical bearing 7. The rod part is provided with external threads to achieve threaded connection with the inner ring of the sleeve 4. The length of the threaded connection is determined according to the load requirements.

[0042] A retaining washer 9 is installed between the sleeve 4 and the tie rod 6. A groove is provided at the end of the tie rod 6. The inner ring of the sleeve 4 is divided into a smooth section and a threaded section. The minimum diameter of the threaded section must be smaller than the minimum diameter of the smooth section, and larger than the maximum outer diameter of the retaining washer 9. The tie rod 6 with the retaining washer 9 is screwed into the cavity of the threaded section of the sleeve 4. The retaining washer 9 contacts the threaded portion of the inner ring of the sleeve 4 and no longer moves, ensuring the safety of the engine installation. When adjusting the engine, only the top of the sleeve 4 needs to be turned. At this time, the tie rod 6 connected to the engine support 10 cannot rotate. The thread between the sleeve 4 and the tie rod 6 converts the circumferential motion of the sleeve 4 into the longitudinal adjustment of the tie rod 6, thereby achieving engine adjustment.

[0043] Once the engine is in place, tighten the locking nut 8 to ensure that the threads of the sleeve 4 and the tie rod 6 are in close contact and the force is optimal when they are screwed together.

[0044] Finally, a safety device is installed between the locking nut 8 and the pull rod 6. These safety devices ensure the entire device is secure and prevents loosening, thus forming a reliable lifting device. For even higher reliability, a safety device can also be installed between the locking nut 8 and the sleeve nut 5.

[0045] The assembly process for the engine auxiliary installation solution is shown in the image. Figure 10 .

[0046] As can be seen from the design of the engine auxiliary installation scheme, the feature of this utility model lies in utilizing the characteristics of spherical bearings and threads to establish a reliable engine auxiliary installation method, realizing engine installation and fixation under certain space constraints. This solution is characterized by low space requirements, simple mechanism, reliability, and high maintainability.

Claims

1. A rear-mounted engine device under spatial constraints, characterized in that, The system includes a spherical bearing (2), an aircraft support (1) is provided on the outer ring of the spherical bearing (2), a bearing end cap (3) is provided on the top of the outer ring of the spherical bearing (2), after the aircraft support (1) and the bearing end cap (3) are connected, the outer ring of the spherical bearing (2) is fixed on the aircraft, a sleeve (4) is provided in the inner ring of the spherical bearing (2), a sleeve nut (5) is provided on the outer cylinder at the bottom of the sleeve (4), the sleeve nut (5) contacts the bottom of the inner ring of the spherical bearing (2), a pull rod (6) is provided inside the sleeve (4) and is threaded to the inner wall of the sleeve (4), a second spherical bearing (7) is provided at the bottom of the pull rod, and the second spherical bearing (7) is connected to the engine mounting base (10).

2. The engine rear-mounted device under spatial constraints according to claim 1, characterized in that, The outer ring of the spherical bearing (2) is fixed to the aircraft by means of a threaded connection between the aircraft support (1) and the bearing end cap (3).

3. The engine rear-mounted device under spatial constraints according to claim 1, characterized in that, A stop washer groove is provided at the top of the pull rod (6), and a stop washer (9) is provided in the stop washer groove (15). The stop washer (9) is engaged with the internal thread of the inner wall of the sleeve (4).

4. The engine rear-mounted device under spatial constraints according to claim 1, characterized in that, A locking nut (8) is provided on the pull rod (6). The locking nut (8) is located on the top of the sleeve (4) and is in contact with the locking nut (8).

5. The engine rear-mounted device under spatial constraints according to claim 1, characterized in that, Safety holes are provided on the bearing end cap (3), aircraft support (1), sleeve (4), sleeve nut (5), anti-loosening nut (8), and pull rod (6). A safety wire is provided between the safety holes of the bearing end cap (3) and the aircraft support (1), between the safety holes of the sleeve (4) and the sleeve nut (5), and between the safety holes of the anti-loosening nut (8) and the pull rod (6).

6. The engine rear-mounted device under spatial constraints according to claim 1, characterized in that, The bearing end cover has a tool groove along the circumferential direction on its upper surface, and a tool can be inserted into the tool groove to rotate the bearing end cover.

7. The engine rear-mounted device under spatial constraints according to claim 1, characterized in that, The bottom of the pull rod is a lifting ring structure, and the second joint bearing (7) is embedded in the lifting ring structure.

8. The engine rear-mounted device under spatial constraints according to claim 1, characterized in that, The internal cavity of the sleeve (4) includes the upper smooth rod section and the lower threaded section. The inner diameter of the smooth rod section is larger than that of the threaded section. The stop washer (9) is clearance-fitted with the cavity of the smooth rod section and can move up and down in the cavity of the smooth rod section. The stop washer (9) is fitted with the internal thread of the inner wall of the threaded section and can restrict the up and down movement of the pull rod.

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