A high-efficiency lightweight high-precision guide wheel system mounting structure and aircraft

Abstract

The application discloses a high-efficiency light-weight high-precision guide wheel system mounting structure and an aircraft. The guide wheel system mounting structure comprises an aircraft cabin body frame beam for accommodating a load, a plurality of annular frame beams being arranged in parallel along an axial direction of the guide wheel system mounting structure; a plurality of guide wheel system mounting bases, each of which is arranged along the axial direction and is uniformly fixed to the inner side of the plurality of annular frame beams; and a plurality of guide wheel system structures which are fixed on the plurality of guide wheel system mounting bases in one-to-one correspondence along the axial direction and are used for guiding the load. On the basis of ensuring the mounting precision of the guide wheel system, the structural load-bearing efficiency is improved, the structural weight is reduced, the process implementation of the corresponding high-precision connecting structure is enhanced, and the production efficiency is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aerospace structure design, and in particular to a high-efficiency, lightweight, and high-precision guide wheel system mounting structure and an aircraft. BACKGROUND

[0002] In some aerospace vehicles, a large-scale delivery payload needs to be installed inside, and the payload needs to be able to be separated from the aircraft along an axial direction to achieve load separation. During the separation process, the cabin needs to provide support and guidance for the separation path of the payload. The most commonly used separation support and guidance matching mechanism is a wheel-rail matching. For the scheme of setting a guide rail on the payload and setting a guide pulley system on the inner wall of the aircraft cabin, multiple sets of support pulley chains need to be set on the circumference of the aircraft cabin, and the flatness and parallelism of the pulley system after installation on the cabin are required to be high. In order to ensure the accuracy of the pulley mounting structure, the usual practice is to use a cast aluminum aircraft cabin, set a cast mounting boss at the pulley mounting position, and after the cabin is formed, the mounting boss surface and the corresponding connecting hole are machined in the whole cabin state. The main disadvantage of the corresponding scheme is that the cast cabin has a lot of redundant weight, and the whole cabin machining is limited by the machine tool level and the cabin segment machining process, and the production efficiency is often low and the realizability is poor. SUMMARY

[0003] Based on the above technical background, the present project proposes a high-efficiency, lightweight, and high-precision guide wheel system mounting structure based on riveting and screwing aluminum alloy cabin. The purpose of the present application is to improve the structure bearing efficiency, reduce the structure weight, and enhance the process realizability of the corresponding high-precision connection structure while ensuring the installation accuracy of the guide wheel system.

[0004] In a first aspect, a guide wheel system mounting structure is provided, comprising:

[0005] An aircraft cabin frame beam for accommodating a load, comprising a plurality of annular frame beams arranged in parallel and spaced apart along an axial direction of the guide wheel system mounting structure;

[0006] A plurality of guide wheel system mounting bases, each guide wheel system mounting base being arranged along the axial direction, and the plurality of guide wheel system mounting bases being uniformly fixed to the inner side of the plurality of annular frame beams;

[0007] A plurality of guide wheel system structures, each corresponding to one of the plurality of guide wheel system mounting bases along the axial direction, and each being fixed to the corresponding guide wheel system mounting base for guiding the load.

[0008] In some implementations of the first aspect, the right upper corner, the right lower corner, the left lower corner and the left upper corner of the guide wheel train mounting structure correspond to four quadrants respectively when viewed along the axial direction, and the number of the plurality of guide wheel train mounting bases and the plurality of guide wheel train structures is four, each guide wheel train mounting base and the corresponding guide wheel train structure are arranged at the boundary between two adjacent quadrants.

[0009] In some implementations of the first aspect, a pulley is arranged on the side of the guide wheel train structure facing the load, the number of pulleys on the target guide wheel train structure is greater than the number of pulleys on the other guide wheel train structures, and the target guide wheel train structure is located at the boundary between the quadrant of the right lower corner and the quadrant of the left lower corner.

[0010] In some implementations of the first aspect, the number of the plurality of ring-shaped frame beams is four, the target guide wheel train structure spans the four ring-shaped frame beams, and the other guide wheel train structures span three ring-shaped frame beams, and the three ring-shaped frame beams are arranged close to the direction of load extraction among the four ring-shaped frame beams.

[0011] In some implementations of the first aspect, the aircraft cabin frame further comprises four strip-shaped frame beams, the four strip-shaped frame beams are arranged in the four quadrants respectively, and the strip-shaped frame beams and the ring-shaped frame beams are riveted and fixed.

[0012] In some implementations of the first aspect, a mounting protrusion is arranged on the ring-shaped frame beam, and the base bottom surface of the guide wheel train mounting base is fixed on the mounting protrusion.

[0013] A plurality of guide wheel train mounting holes are arranged on the base top surface of the guide wheel train mounting base, and the guide wheel train structures are screwed and fixed.

[0014] In some implementations of the first aspect, the mounting protrusion has an opening facing the direction of load extraction.

[0015] In some implementations of the first aspect, a transverse web and a longitudinal web are arranged between the base bottom surface and the base top surface.

[0016] In some implementations of the first aspect, a plurality of transverse webs are arranged between the base bottom surface and the base top surface, two longitudinal webs are arranged between the base bottom surface and the base top surface and between two adjacent transverse webs, the two longitudinal webs are parallel to each other and extend along the axial direction, and the two adjacent transverse webs and the two longitudinal webs form a cavity, and the guide wheel train mounting holes are arranged on both sides of the cavity.

[0017] In a second aspect, an aircraft is provided, characterized in that the aircraft includes a guide wheel system mounting structure as described in any of the implementations of the first aspect above.

[0018] Compared with the prior art, the solution provided in this application has at least the following beneficial technical effects:

[0019] (1) It can fit the characteristics of riveting and bolting the frame beams of the aircraft cabin. The guide wheel system mounting base beam is directly mounted on the platform surface of the ring frame integrally formed. The ring frame only protrudes at the part where it is connected to the base beam, saving materials and weight. The base beam and the cabin ring frame mounting structure are both I-shaped or C-shaped sections with high load-bearing efficiency. They can effectively utilize the main load-bearing structure of the cabin, improve the overall load-bearing efficiency of the structure, and effectively reduce the weight of the structure.

[0020] (2) The connection and positioning between the guide wheel system mounting base beam and the cabin body are ensured by riveting and bolting frame tooling. At the same time, the guide wheel system and the mounting base beam are positioned by pin hole engagement for pulley installation. Relying on the conventional positioning pin structure, the corresponding connection scheme can effectively ensure the flatness, parallelism and other dimensional accuracy of the wheel system mounting structure, while having good process feasibility.

[0021] (3) The corresponding wheel system installation structure can adapt to large-scale delivery loads and various types of irregular cross-section cabins, and has strong versatility.

[0022] (4) Depending on the different load conditions in different directions of the aircraft, the number and arrangement of pulleys in the four quadrants can be designed accordingly. Usually, the aircraft is subjected to the greatest load along the direction of gravity, so the number of pulleys can be increased only in one quadrant, thereby reducing the weight of pulleys in other quadrants. Attached Figure Description

[0023] Figure 1 A schematic diagram of the structure for mounting the guide wheel system.

[0024] Figure 2 This is a structural diagram of the wheel system base installation based on an integrally formed ring frame.

[0025] Figure 3 This is a structural diagram of the wheel system base installation based on an integrally formed ring frame.

[0026] Figure 4 This is a schematic diagram of a C-shaped cross-section ring frame.

[0027] Figure 5 Diagram of the mounting base structure for the guide wheel system.

[0028] Figure 6 A schematic diagram of the cross-section of the mounting base for the guide wheel system.

[0029] Reference numerals are explained as follows: 1, aircraft cabin frame beam, 2, guide wheel system mounting base, 3, guide wheel system structure, 1-1, annular frame beam, 1-2, mounting protrusion, 2-1, base bottom surface, 2-2, longitudinal web, 2-3, guide wheel system mounting hole, 2-4, transverse web, 2-5, base top surface. DETAILED DESCRIPTION

[0030] The application will be further described below in conjunction with the drawings and specific embodiments.

[0031] The present application relates to a guide wheel system mounting structure, which can be an aluminum alloy riveting and screwing aircraft cabin based guide wheel system mounting structure arranged in an aircraft. As shown in the drawings, Figure 1 The aircraft can include an aircraft cabin frame beam 1, a plurality of guide wheel system mounting bases 2 and a plurality of guide wheel system structures 3, which constitute the guide wheel system mounting structure.

[0032] The guide wheel system mounting base 2 is fixed axially on the inner side of the aircraft cabin frame beam 1. The plurality of guide wheel system mounting bases 2 and the plurality of guide wheel system structures 3 can correspond one by one. The guide wheel system structure 3 is fixed (for example by screwing) on the corresponding guide wheel system mounting base 2. That is, the plurality of guide wheel system structures 3 are fixed circumferentially on the inner side of the aircraft cabin frame beam 1. The side of the guide wheel system structure 3 away from the guide wheel system mounting base 2 is provided with a pulley, which cooperates with the load in the aircraft to guide the load. When the load is unloaded from the aircraft cabin frame beam 1, the pulley on the guide wheel system structure 3 can facilitate the smooth unloading of the load along the axial direction.

[0033] In the embodiment shown in Figure 1 When the aircraft cabin frame beam 1 is viewed axially, the aircraft cabin frame beam 1 can be divided into four parts, corresponding to four quadrants. Starting from the upper right corner of the aircraft cabin frame beam 1, passing through the lower right corner, the lower left corner and the upper left corner of the aircraft cabin frame beam 1 in turn in a counterclockwise direction, the four quadrants can be quadrant I, quadrant II, quadrant III and quadrant VI respectively.

[0034] The aircraft cabin frame beam 1 can include a plurality of annular frame beams 1-1 and a plurality of strip frame beams. In the embodiment shown in Figure 1 and Figure 2 The number of the plurality of annular frame beams 1-1 can be four, and the number of the plurality of strip frame beams can be four. The plurality of annular frame beams 1-1 can be arranged in parallel with each other. The strip frame beams can be riveted on the outer side of the plurality of annular frame beams 1-1. The plurality of strip frame beams can be symmetrically arranged. For example, the four strip frame beams can be arranged in quadrant I, quadrant II, quadrant III and quadrant VI respectively.

[0035] The guide wheel system mounting base 2 is distributed in an axial direction and crosses the annular frame beam 1-1, which can effectively utilize the main load-bearing structure of the aircraft cabin frame beam 1, thereby effectively improving the load-bearing efficiency of the wheel system mounting structure.

[0036] The number of the plurality of guide wheel system mounting bases 2 can be four, which are respectively arranged at the junctions of adjacent quadrants. The plurality of guide wheel system structures 3 can be arranged in a "cross" shape, thereby providing axial positioning and guiding for the in-flight loading of the aircraft in four directions. In each guide wheel system structure 3, the pulleys can be arranged in a chain shape, thereby achieving axial positioning and guiding for the in-flight loading of the aircraft.

[0037] According to different load conditions of the aircraft in different directions, the number and arrangement position of the pulleys in the four quadrants can be designed accordingly. In the present case, the aircraft cabin frame beam 1 has a higher load requirement at the junction of the II quadrant and the III quadrant, and therefore four pulleys are arranged at the guide wheel system structure 3 at this position. The load at other positions is relatively small, and therefore two pulleys are arranged at the guide wheel system structure 3 at the other positions, thereby reducing the weight of the system.

[0038] As shown in Figure 2 and Figure 3 , the inner side of the aircraft cabin frame beam 1 can be provided with a mounting protrusion 1-2 for connecting the guide wheel system mounting bases 2 in the quadrants. Specifically, the mounting protrusion 1-2 can be arranged on the annular frame beam 1-1 and integrally formed with the main body of the annular frame beam 1-1 as a same part machined, which can effectively ensure the position accuracy of the mounting surface. The annular frame beam 1-1 is only protruded at the position connected with the guide wheel system mounting base 2, which is beneficial to saving materials and weight.

[0039] As shown in Figure 4 , the cross section of the aircraft cabin frame beam 1 at the mounting protrusion 1-2 can be in a "C" shape. The "C" shape can include three edges, two of which are located on the cross section of the mounting protrusion 1-2, and one of which is located on the cross section of the annular frame beam 1-1 of the aircraft cabin frame beam 1. That is, the mounting protrusion 1-2 can include four surfaces. The first surface of the mounting protrusion 1-2 can be the surface fixed with the guide wheel system mounting base 2. The second surface and the third surface of the mounting protrusion 1-2 can be connected between the first surface of the mounting protrusion 1-2 and the aircraft cabin frame beam 1, and the second surface and the third surface can be arranged in parallel with each other. The fourth surface of the mounting protrusion 1-2 can be connected between the first surface of the mounting protrusion 1-2 and the aircraft cabin frame beam 1, and the fourth surface can be arranged perpendicularly relative to the second surface or the third surface. The side of the mounting protrusion 1-2 away from the fourth surface can form an opening, and the opening can be directed to the direction of load release. The mounting protrusion 1-2 has a structure with a "C" shaped cross section, which is beneficial to saving materials and weight.

[0040] The structural design of a guide wheel system mounting base 2 provided by the present invention is described below. For example... Figure 5 , Figure 6 As shown, the guide wheel system mounting base 2 is generally elongated. The bottom surface 2-1 of the guide wheel system mounting base 2 is screwed to the mounting protrusion 1-2 on the annular frame beam 1-1 of the aircraft cabin frame beam 1. Several guide wheel system mounting holes 2-3 are provided on the top surface 2-5 of the guide wheel system mounting base 2 for mounting and fixing the guide wheel system structure 3.

[0041] In the direction perpendicular to the axial direction, the guide wheel system mounting base 2 is provided with multiple transverse webs 2-4, the two sides of which can be flush with the edges of the guide wheel system mounting base 2. Between two adjacent transverse webs 2-4, the guide wheel system mounting base 2 is provided with two longitudinal webs 2-2. The two longitudinal webs 2-2 can be arranged parallel to each other and extend axially. The bottom side of the longitudinal webs 2-2 is connected to the base bottom surface 2-1 of the guide wheel system mounting base 2, and the top side is connected to the base top surface 2-5 of the guide wheel system mounting base 2. Between two adjacent transverse webs 2-4, the two longitudinal webs 2-2 are arranged opposite each other, thereby forming a cavity. The opening of this cavity (located in the middle area of ​​the base top surface 2-5 of the guide wheel system mounting base 2) can be enclosed by the two longitudinal webs 2-2 and the two transverse webs 2-4. Guide wheel system mounting holes 2-3 can be provided on both sides of this opening.

[0042] After being connected to the hull, the guide wheel system mounting base 2 serves both as the mounting base for the pulley system and as a longitudinal beam to enhance the rigidity of the hull. The guide wheel system mounting base 2 is equipped with transverse and longitudinal webs to further enhance its own rigidity. The guide wheel system mounting holes 2-3 also serve as positioning holes for the hull riveting and bolting fixtures, facilitating the ensuring of the positional accuracy of the pulley mounting protrusions 1-2 and the mounting holes during the hull riveting and bolting process.

[0043] This project proposes a highly efficient, lightweight, and high-precision guide wheel system installation structure based on riveted and bolted aluminum alloy cabin hulls. This structure leverages the interlacing characteristics of the riveted and bolted aircraft cabin frame beam 1's ring frame and longitudinal ribs. An integrally formed pulley base mounting surface is provided on the ring frame. A pulley chain mounting base with an "I"-shaped cross-section is also designed, featuring positioning holes and connection holes for installing pulleys and ensuring installation accuracy. This structural solution effectively improves structural load-bearing capacity, reduces structural weight, and, due to the use of riveted and bolted frame assembly and positioning, ensures good pulley system installation accuracy. Furthermore, it offers good manufacturability and improves production efficiency.

[0044] Although the present application is disclosed with reference to the preferred embodiments above, it is not intended to limit the present application, and any person skilled in the art can make possible variations and modifications without departing from the spirit and scope of the present application. Therefore, the scope of protection of the present application should be defined by the scope of the claims.

Claims

1. A guide wheel train mounting structure characterized by comprising: The application relates to an aircraft cabin frame beam (1) for accommodating a load, comprising a plurality of annular frame beams (1-1) arranged in parallel along an axial direction of a guide wheel system mounting structure; a plurality of guide wheel system mounting bases (2) arranged along the axial direction, each of the guide wheel system mounting bases (2) being fixed to the inner side of the plurality of annular frame beams (1-1); and a plurality of guide wheel system structures (3) fixed to the plurality of guide wheel system mounting bases (2) in one-to-one correspondence along the axial direction, and used for guiding the load. The annular frame beam (1-1) is provided with a mounting protrusion (1-2), and the base bottom surface (2-1) of the guide wheel system mounting base (2) is fixed to the mounting protrusion (1-2). The base top surface (2-5) of the guide wheel system mounting base (2) is provided with a plurality of guide wheel system mounting holes (2-3) for screwing and fixing the guide wheel system structure (3). The base bottom surface (2-1) and the base top surface (2-5) are provided with transverse webs (2-4) and longitudinal webs (2-2). The base bottom surface (2-1) and the base top surface (2-5) are provided with a plurality of transverse webs (2-4), and two longitudinal webs (2-2) are arranged between the base bottom surface (2-1) and the base top surface (2-5) and between two adjacent transverse webs (2-4), the two longitudinal webs (2-2) are parallel to each other and extend along the axial direction, and the two adjacent transverse webs (2-4) and the two longitudinal webs (2-2) form a cavity, and the guide wheel system mounting hole (2-3) is arranged on both sides of the cavity. When observed along the axial direction, the upper right corner, the lower right corner, the lower left corner and the upper left corner of the guide wheel system mounting structure correspond to four quadrants respectively, the number of the plurality of guide wheel system mounting bases (2) and the plurality of guide wheel system structures (3) is four, and each guide wheel system mounting base (2) and the corresponding guide wheel system structure (3) are arranged at the boundary between two adjacent quadrants. The side of the guide wheel system structure (3) facing the load is provided with a plurality of pulleys, the number of pulleys on a target guide wheel system structure (3) is greater than that on other guide wheel system structures (3), and the target guide wheel system structure (3) is located at the boundary between the lower right quadrant and the lower left quadrant. The number of the plurality of annular frame beams (1-1) is four, the target guide wheel system structure (3) spans the four annular frame beams (1-1), the other guide wheel system structures (3) span three annular frame beams (1-1), and the three annular frame beams (1-1) are arranged close to the direction of load disengagement among the four annular frame beams (1-1).

2. The guide wheel train mounting structure according to claim 1, characterized by The aircraft cabin frame beam (1) further comprises four strip-shaped frame beams, the four strip-shaped frame beams are arranged in the four quadrants respectively, and the strip-shaped frame beams and the annular frame beams (1-1) are riveted and fixed.

3. The guide wheel train mounting structure according to claim 2, characterized by The mounting protrusion (1-2) has an opening facing the direction of load disengagement.

4. The guide wheel train mounting structure according to claim 3, characterized by The aircraft comprises the guide wheel system mounting structure according to any one of claims 1 to 6.

5. The guide wheel train mounting structure according to any one of claims 2 to 4, characterized by ​ 6. The guide wheel train mounting structure according to claim 1, characterized by ​ 7. An aircraft, characterized in that ​

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