A cradle-type flexible adjustment device for aircraft engine mounting

Abstract

The present application discloses a kind of hanging basket type flexible adjusting device for aircraft engine installation, belong to including support frame, fine adjustment support component and a group of bearing beam, a group of bearing beam is arranged in parallel and interval below support frame, fine adjustment support component is arranged on bearing beam, bearing beam is fixed between through multiple connecting rods, and flexible adjusting mechanism is arranged between the both ends of bearing beam and support frame;Fine adjustment support component is used to fix engine and carry out multi-degree-of-freedom fine adjustment to engine;Flexible adjusting mechanism is used to make bearing beam adaptive deviation with the gravity center variation of fine adjustment support component;The present application connects support frame with fine adjustment support component by hanging basket type flexible adjusting mechanism, when fine adjustment support component fine adjustment to engine above it, bearing beam will adaptively follow the gravity center variation of engine and change, keep support frame uniform stress, to keep the stability of engine on fine adjustment support component.

Description

Technical Field

[0001] This invention relates to the field of aircraft engine assembly technology, and more specifically to a basket-type flexible adjustment device for aircraft engine installation. Background Technology

[0002] Aircraft engine assembly is a challenging task in the field of aircraft engineering. As performance requirements for aircraft increase, the clearance between the engine and the fuselage has decreased from 10-15mm to within 5-7mm. This necessitates higher precision requirements for engine assembly and the assembly equipment. Existing engine assembly equipment only achieves an adjustment precision of around 10mm, which is insufficient for aircraft with high precision demands. Furthermore, existing equipment requires overall alignment at the bottom of the aircraft before engine lifting and lowering, followed by manual fine-tuning. During fine-tuning, the rigid connection between the support bracket and the bottom support platform makes it difficult to adaptively adjust the center of gravity, easily leading to tilting of the bottom support platform or assembly accidents due to uneven stress. This also affects assembly progress. Additionally, poor assembly precision means that if the engine cannot be aligned within the fuselage, it must be removed entirely and re-lifted for installation, resulting in low assembly efficiency. Summary of the Invention

[0003] To address the problem in existing engine assembly equipment that cannot adaptively adjust the center of gravity during fine-tuning, which can easily lead to assembly safety accidents and affect assembly accuracy and efficiency, this invention proposes a basket-type flexible adjustment device for aircraft engine installation. By connecting the support frame to the fine-tuning support assembly, when the fine-tuning support assembly makes fine-tuning adjustments to the engine above it, the load-bearing beam can adaptively follow the changes in the engine's center of gravity, maintaining uniform stress on the support frame and ensuring the stability of the engine on the fine-tuning support assembly, thereby improving assembly safety and efficiency.

[0004] To achieve the above-mentioned objectives, the technical solution of the present invention is as follows:

[0005] A basket-type flexible adjustment device for aircraft engine installation includes a support frame, a fine-tuning support assembly, and a set of load-bearing beams. The load-bearing beams are arranged parallel and spaced apart below the support frame. The fine-tuning support assembly is mounted on the load-bearing beams, and the load-bearing beams are fixed together by multiple connecting rods. Flexible adjustment mechanisms are provided between the two ends of the load-bearing beams and the support frame. The fine-tuning support assembly is used to fix the engine and perform multi-degree-of-freedom fine-tuning of the engine. The flexible adjustment mechanisms are used to adjust the height of the load-bearing beams and allow the load-bearing beams to adaptively shift with the change of the center of gravity of the fine-tuning support assembly.

[0006] Preferably, the flexible adjustment mechanism includes a first flexible component, a connector, and a lead screw; the connector is disposed on the top of the support frame, the upper end of the lead screw is connected to the connector, the lower end passes through the support frame and is threadedly connected to the first flexible component, and the load-bearing beam is connected to the first flexible component.

[0007] Preferably, the first flexible component includes a bushing, an abutment, a limiting member, a connecting plate, and a fixing member; the bushing is threadedly connected to a lead screw, the limiting member and the abutment are both sleeved on the bushing, the limiting member is positioned above the abutment and abuts against the abutment; the connecting plate abuts against the bottom of the abutment and is connected to a load-bearing beam; the fixing member is positioned below the abutment and threadedly connected to the bushing, used to axially limit the limiting member and the abutment.

[0008] Preferably, the load-bearing beam is provided with a mounting hole, and the load-bearing beam is sleeved with the bushing through the mounting hole. The diameter of the mounting hole is larger than the diameter of the bushing. Below the mounting hole, there is a mounting groove that cooperates with a limiting member, and the limiting member is embedded in the mounting groove.

[0009] Preferably, the abutting member is provided with an abutting surface, which is a curved surface structure inclined towards its own edge; the limiting member is provided with a mating surface, which is a chamfered structure recessed towards its own center, and the mating surface mates with the abutting surface.

[0010] Preferably, the edge of the limiting member is provided with a set of limiting surfaces, the limiting surfaces are inclined surfaces, and the sidewall of the mounting groove on the bearing beam cooperates with the limiting surfaces of the edge of the limiting member.

[0011] Preferably, the bushing is provided with an insertion part and a limiting part, the diameter of the limiting part is larger than the diameter of the insertion part, and the limiting part is used to limit the abutment; the abutment and the fixing part are both provided on the insertion part.

[0012] Preferably, the gap between the limiting part of the bushing and the side wall of the mounting hole of the bearing beam is 5-7mm.

[0013] Preferably, the flexible adjustment mechanism further includes at least two sets of second flexible components, which are disposed on the support frame and located on the same side of the support frame; the second flexible component includes a connecting shaft, a set of fixing plates and a set of support members; the fixing plates are respectively located on both sides of the connector and fix the connector, and support members are provided on the outer side of both fixing plates; the connecting shaft passes through the fixing plates and the connector and is hinged to the two support members respectively.

[0014] Preferably, the bottom of the connector is spaced apart from the surface of the support frame, and the gap between the bottom of the connector and the upper surface of the support frame is 5-7mm.

[0015] Preferably, the lead screw and the support frame are spaced apart, and the gap between the lead screw and the support frame is 5-7mm.

[0016] In summary, the present invention has the following advantages:

[0017] 1) In this invention, the support frame is connected to the fine-tuning support component by a basket-type flexible adjustment mechanism. When the fine-tuning support component makes a fine adjustment to the engine above it, the load-bearing beam will adapt to the change of the engine's center of gravity, keeping the support frame under uniform force, so as to maintain the stability of the engine on the fine-tuning support component.

[0018] 2) In this invention, four sets of first flexible components are provided below the support frame, and two sets of second flexible components are provided on the same side above the support frame. The load-bearing beam is connected to the first flexible components. When the fine-tuning support components adjust the angle of the engine, the load-bearing beam moves with the adaptive deformation of the first flexible components. At the same time, the second flexible components at the top of the support frame can make the connector and the lead screw tilt synchronously to ensure the stability of the engine on the fine-tuning support components and the support frame. Attached Figure Description

[0019] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments, wherein:

[0020] Figure 1 This is a schematic diagram of the basket-type flexible adjustment device for aircraft engine installation according to the present invention.

[0021] Figure 2 This is a schematic diagram of the connection structure between the first flexible component and the lead screw in this invention;

[0022] Figure 3 This is a cross-sectional view of the connection structure between the first flexible component and the lead screw in this invention;

[0023] Figure 4 This is a schematic diagram of the structure of the abutment member in this invention;

[0024] Figure 5 This is a schematic diagram of the limiting component in this invention;

[0025] Figure 6 for Figure 1 Schematic diagram of the structure at point A in the middle;

[0026] Figure 7 This is a schematic diagram of the internal structure of the first flexible component and the load-bearing beam in this invention.

[0027] Wherein: 1-support frame, 2-fine-tuning support assembly, 3-bearing beam, 31-connecting rod, 4-first flexible assembly, 41-shoulder sleeve, 411-insertion part, 412-limiting part, 42-limiting component, 421-mating surface, 43-abutting component, 431-abutting surface, 44-connecting plate, 45-fixing component, 5-connector, 6-lead screw, 7-second flexible assembly, 71-fixing plate, 72-support component, 73-connecting shaft. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0029] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0030] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0031] In the description of this invention, it should be noted that the terms "upper," "lower," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this invention is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are used only for the convenience of describing this invention 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 invention. In addition, the terms "first," "second," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0032] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," and "connect" 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; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0033] Example 1:

[0034] like Figure 1 As shown: A basket-type flexible adjustment device for aircraft engine installation includes a support frame 1, a fine-tuning support component 2 and a set of load-bearing beams 3. The set of load-bearing beams 3 are arranged parallel and spaced apart below the support frame 1. The fine-tuning support component 2 is arranged on the load-bearing beams 3. The load-bearing beams 3 are fixed together by multiple connecting rods 31. A flexible adjustment mechanism is provided between the two ends of the load-bearing beams 3 and the support frame 1.

[0035] In this design, the fine-tuning support assembly 2 is used to connect and fix the engine, and can also adjust the engine in multiple degrees of freedom, including forward, backward, left, right, and roll, so that the engine can be smoothly installed into the fuselage. It is primarily responsible for the fine-tuning steps of the engine entering the fuselage. The support frame 1 provides a support platform for the fine-tuning support assembly 2, and can be raised and lowered to adjust the overall height of the fine-tuning support assembly 2 and the engine. The flexible adjustment mechanism is used to adjust the height of the load-bearing beam 3 and to adaptively shift the load-bearing beam 3 as the center of gravity of the fine-tuning support assembly 2 changes. For example, when the front end of the engine is adjusted to the right and the rear end to the left, the center of gravity of the front and rear sections of the fine-tuning support assembly 2 will also change accordingly. At this time, the load-bearing beam 3 can adaptively follow the fine-tuning adjustment through the flexible adjustment mechanism to adapt to the change in the engine's center of gravity, thereby maintaining the stability of the engine on the fine-tuning support assembly 2 at all times.

[0036] Example 2

[0037] Based on Example 1, this example describes the structure of the flexible adjustment mechanism.

[0038] In this scheme, the flexible adjustment mechanism includes four basket-type structures set between the support frame 1 and the load-bearing beam 3. These four basket-type structures are located at the four corner points of a set of load-bearing beams 3.

[0039] like Figure 2 and Figure 3The diagram shows the specific structure of the flexible adjustment mechanism. In this design, the flexible adjustment mechanism includes a connector 5, a lead screw 6, and a first flexible component 4. The connector 5 is mounted on the support frame 1, the upper end of the lead screw 6 is connected to the connector 5 and can adaptively deflect following the connector 5, and the lower end of the lead screw 6 is connected to the first flexible component 4, which is also connected to the load-bearing beam 3.

[0040] In this design, the first flexible component 4 includes a bushing 41, an abutment 43, a limiting component 42, a connecting plate 44, and two fixing components 45. The bushing 41 is threadedly connected to the lead screw 6. Both the limiting component 42 and the abutment 43 are fitted onto the bushing 41, with the limiting component 42 positioned above and abutting against the abutment 43. The two fixing components 45 are positioned below the abutment 43 and threadedly connected to the bushing 41, used to axially limit the limiting component 42 and the abutment 43, preventing the abutment 43 from loosening on the bushing 41. Specifically, as shown... Figure 3 As shown, the bushing 41 is provided with an insertion part 411 and a limiting part 412. The diameter of the limiting part 412 is larger than the diameter of the insertion part 411. An abutment member 43 and a fixing member 45 are both provided on the insertion part 411. The limiting part 412 is used to limit the abutment member 43, which moves with the bushing 41 as it moves up and down. The insertion part 411 is provided with threads, and the fixing member 45 is threadedly connected to the insertion part 411 on the bushing 41. Figure 7 As shown, the load-bearing beam 3 is provided with mounting holes and is fitted with the bushing 41 through the mounting holes. At the same time, the diameter of the mounting holes is larger than the diameter of the bushing 41, so that the load-bearing beam 3 has sufficient adaptive displacement margin. The load-bearing beam 3 is provided with a mounting groove below the mounting holes. The mounting groove cooperates with the limiting member 42. The limiting member 42 is embedded in the mounting groove. When the center of gravity of the engine shifts, the load-bearing beam 3 drives the limiting member 42 to adaptively fine adjust on the abutment member 43.

[0041] Preferably, the gap between the limiting part 412 of the bushing 41 and the side wall of the mounting hole of the bearing beam 3 is 5mm.

[0042] The connecting plate 44 abuts against the bottom of the abutment member 43 and is connected to the bearing beam 3. The connecting plate 44 is welded to the bottom of the bearing beam 3, and together with the bearing beam 3, clamps and fixes the limiting member 42. At the same time, the connecting plate 44 and the fixing member 45 are on the same horizontal plane, and the connecting plate 44 and the fixing member 45 are spaced apart. When the bearing beam 3 moves, it drives the connecting plate 44 and the limiting member 42 to move simultaneously.

[0043] Example 3:

[0044] Based on Example 2, this example further describes the structure of the abutment member 43.

[0045] like Figure 4The diagram shows the structure of the abutting member 43 in this invention. The abutting member 43 is provided with an abutting surface 431, which is a curved surface structure inclined towards its own edge. The limiting member 42 is provided with a mating surface 421, which is a chamfered structure recessed towards its own center. The mating surface 421 and the abutting surface 431 are mated together, so that the limiting member 42 can slide on the surface of the abutting member 43 to adapt to deformation in multiple directions.

[0046] like Figure 5 The diagram shows the structure of the limiting member 42. The limiting member 42 has a set of limiting surfaces on its edge, which are arranged opposite to each other on the edge of the limiting member 42. The limiting surfaces are inclined structures. The side wall of the mounting groove on the load-bearing beam 3 cooperates with the limiting surfaces on the edge of the limiting member 42, and the load-bearing beam 3 and the limiting member 42 are kept stable by the connecting plate 44 at the bottom.

[0047] The working principle of this invention is as follows: When the center of gravity of the engine changes due to fine-tuning, the center of gravity of the front and rear sections of the fine-tuning support assembly 2 also changes accordingly. At this time, under the action of the flexible adjustment mechanism, the bearing beam 3 drives the limiting member 42 to slide along the abutment surface 431 of the abutment member 43 on the abutment member 43, thereby realizing flexible adjustment.

[0048] Example 4:

[0049] Based on Embodiment 1, a second flexible component 7 is further provided, such as... Figure 1 and Figure 6 As shown, the flexible adjustment mechanism also includes two sets of second flexible components 7. These two sets of second flexible components 7 are located on the same side of the support frame 1. Two connectors 5 on the opposite side of the support frame 1 that do not have second flexible components 7 are fixedly connected to the support frame 1.

[0050] In this embodiment, the second flexible component 7 includes a connecting shaft 73, a set of fixing plates 71, and a set of support members 72. The fixing plates 71 have a C-shaped structure and fix both sides of the connector 5 with screws. Support members 72 are provided on the outer sides of both fixing plates 71. The support members 72 have an L-shaped structure. The connecting shaft 73 passes through the fixing plates 71 and the connector 5 and is hinged to the two support members 72 respectively, so that the connector 5 can rotate slightly along the connecting shaft 73 on the support members 72. When the engine is fine-tuned, the load-bearing beam 3 adaptively adjusts under the action of the first flexible component 4, and at the same time can pull the lead screw 6 and drive the connector 5 to make adaptive offset to adapt to the change of the engine's center of gravity.

[0051] In this design, the bottom of connector 5 is spaced apart from the surface of support frame 1. Preferably, the gap between the bottom of connector 5 and support frame 1 is 5mm.

[0052] In this design, the support frame 1 has a through hole that allows the lead screw 6 to pass through. Preferably, the gap between the lead screw 6 and the through hole on the support frame 1 is 5-7 mm.

[0053] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention in any way. Any simple modifications or equivalent changes made to the above embodiments based on the technical essence of the present invention shall fall within the protection scope of the present invention.

Claims

1. A basket-type flexible adjustment device for aircraft engine installation, characterized in that, The system includes a support frame (1), a fine-tuning support assembly (2), and a set of load-bearing beams (3). The set of load-bearing beams (3) are arranged parallel and spaced apart below the support frame (1). The fine-tuning support assembly (2) is set on the load-bearing beams (3). The load-bearing beams (3) are fixed together by multiple connecting rods (31). A flexible adjustment mechanism is provided between the two ends of the load-bearing beams and the support frame (1). The fine-tuning support assembly (2) is used to fix the engine and perform multi-degree-of-freedom fine-tuning of the engine. The flexible adjustment mechanism is used to adjust the height of the load-bearing beams and make the load-bearing beams (3) adaptively shift with the change of the center of gravity of the fine-tuning support assembly (2). The flexible adjustment mechanism includes a first flexible component (4), a connector (5) and a lead screw (6); the connector (5) is set on the top of the support frame (1), the upper end of the lead screw (6) is connected to the connector (5), and the lower end passes through the support frame (1) and is threadedly connected to the first flexible component (4); the load-bearing beam (3) is connected to the first flexible component (4). The first flexible component (4) includes a bushing (41), an abutment (43), a limiting member (42), a connecting plate (44), and a fixing member (45); the bushing (41) is threadedly connected to the lead screw (6), the limiting member (42) and the abutment (43) are both sleeved on the bushing (41), the limiting member (42) is located above the abutment (43) and abuts against the abutment (43); the connecting plate (44) abuts against the bottom of the abutment (43) and is connected to the bearing beam (3); the fixing member (45) is located below the abutment (43), threadedly connected to the bushing (41), and is used to axially limit the limiting member (42) and the abutment (43); The flexible adjustment mechanism further includes at least two sets of second flexible components (7), the two sets of second flexible components (7) are arranged on the support frame (1) and located on the same side of the support frame (1); the second flexible component (7) includes a connecting shaft (73), a set of fixing plates (71) and a set of support members (72); the fixing plates (71) are respectively located on both sides of the connector (5) and fix the connector (5), and support members (72) are provided on the outer side of both fixing plates (71), the connecting shaft (73) passes through the fixing plate (71) and the connector (5) and is hinged to the two support members (72) respectively.

2. The basket-type flexible adjustment device for aircraft engine installation as described in claim 1, characterized in that, The bearing beam (3) is provided with an installation hole, and the bearing beam (3) is sleeved with the bushing (41) through the installation hole. The diameter of the installation hole is larger than the diameter of the bushing (41). Below the installation hole is an installation groove that cooperates with the limiting member (42), and the limiting member (42) is embedded in the installation groove.

3. The basket-type flexible adjustment device for aircraft engine installation as described in claim 1, characterized in that, The abutting member (43) is provided with an abutting surface (431), and the abutting surface (431) of the abutting member (43) is a curved surface structure that is inclined towards its own edge; the limiting member (42) is provided with a mating surface (421), and the mating surface (421) of the limiting member (42) is a chamfered structure that is recessed towards its own center, and the mating surface (421) and the abutting surface (431) are mated.

4. A basket-type flexible adjustment device for aircraft engine installation as described in claim 2, characterized in that, The edge of the limiting member (42) is provided with a set of limiting surfaces, which are inclined surfaces. The side wall of the mounting groove on the bearing beam (3) cooperates with the limiting surface of the edge of the limiting member (42).

5. A basket-type flexible adjustment device for aircraft engine installation as described in claim 1, characterized in that, The bushing (41) is provided with a plug-in part (411) and a limiting part (412). The diameter of the limiting part (412) is larger than the diameter of the plug-in part (411). The limiting part (412) is used to limit the abutment (43). The abutment (43) and the fixing part (45) are both provided on the plug-in part (411).

6. A basket-type flexible adjustment device for aircraft engine installation as described in claim 5, characterized in that, The gap between the limiting part (412) of the bushing (41) and the side wall of the mounting hole of the bearing beam (3) is 5-7mm.

7. A basket-type flexible adjustment device for aircraft engine installation as described in claim 1, characterized in that, The bottom of the connector (5) is spaced apart from the surface of the support frame (1), and the gap between the bottom of the connector (5) and the upper surface of the support frame (1) is 5-7mm.

8. A basket-type flexible adjustment device for aircraft engine installation as described in claim 1, characterized in that, The lead screw (6) and the support frame (1) are spaced apart, and the gap between the lead screw (6) and the support frame (1) is 5-7mm.

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