A product installation and adjustment platform for an aircraft control system

Abstract

This invention discloses a product installation and adjustment platform for an aircraft control system. A connecting bracket is vertically mounted on the upper surface of one side of the mounting platform, and a body mounting bracket is mounted on the lower surface of the other side. The upper surface of the bracket is fixedly connected to the support platform of a support assembly. A clutch is installed via mounting structures on both sides of the support assembly. One end of each of the two tie rod assemblies is hinged to the double-ear portion of a bracket assembly, and the other end is hinged to the double-ear structures at two corners of a triangular chain. The other corner of the triangular chain is hinged to the connecting bracket. The body mounting bracket of the mounting platform is fixedly connected to the internal structure of the aircraft. The two bracket assemblies are respectively attached to and fixedly connected to both sides of the aircraft's main beam via their mounting end faces. This invention solves the problems of existing clutch installation methods in aircraft, which are time-consuming and labor-intensive, prone to assembly stress leading to product malfunction, high failure rate, high maintenance costs, and seriously affect product reliability.

Description

Technical Field

[0001] This invention relates to, but is not limited to, the field of product testing technology, and particularly to a product installation and adjustment platform for aircraft control systems. Background Technology

[0002] In aircraft operating systems, a certain type of clutch is used to improve aircraft safety. However, due to the clutch's special structure, improper installation may cause functional failure, and installation problems are difficult to detect completely through initial ground inspections, leading to increased product inspection and maintenance costs.

[0003] Currently, the aforementioned clutch is installed in aircraft as follows: it connects to the aircraft's main beam II via a left bracket and to the aircraft's internal fuselage structure via a right bracket. In this installation method, adjusting the assembly clearance using shims is difficult due to space constraints, and the installation is time-consuming and labor-intensive. Furthermore, if there is a large assembly clearance between the side brackets and the fuselage, assembly stress frequently occurs when connecting the clutch to the fuselage with screws, leading to product malfunction, high failure rate, high maintenance costs, and severely impacting product reliability. 。 Summary of the Invention

[0004] The purpose of this invention is to solve the above-mentioned technical problems. This invention provides a product installation and adjustment platform for aircraft control systems, which solves the problems of existing clutch installation methods in aircraft, which are affected by onboard space, are time-consuming and labor-intensive to install, and are prone to product failure due to assembly stress, resulting in high failure rate, high maintenance cost, and seriously affecting product reliability.

[0005] The technical solution of the present invention: The present invention provides a product installation and adjustment platform for an aircraft control system, including: a support assembly a, two bracket assemblies 1, two tie rod assemblies 2, a triangular chain 3, and a mounting frame 11;

[0006] The mounting frame 11 is configured as a platform structure. A connecting bracket 11a is vertically arranged on the upper surface of one side of the platform, and an organic mounting frame 11b is arranged on the lower surface of the other side of the platform. The upper surface of the platform of the mounting frame 11 is fixedly connected to the support platform of the support assembly a, and the clutch is installed through the mounting structures arranged on both sides of the support assembly a.

[0007] One end of each of the two tie rod assemblies 2 is hinged to the double ear of one bracket assembly 1, and the other end is hinged to the double ear structure at two corners of the triangular chain disk 3. The other corner of the triangular chain disk 3 is hinged to the connecting bracket 11a on one side of the mounting platform 11. The fuselage mounting bracket 11b on the lower end face of the other side of the mounting platform 11 is fixedly connected to the internal fuselage structure of the aircraft. The two bracket assemblies 1 are respectively attached to and fixedly connected to both sides of the main beam of the aircraft II through their mounting end faces.

[0008] Optionally, in the product installation and adjustment platform for the aircraft control system as described above, the support assembly a includes: a first support a1, a second support a2, a cylindrical head screw a3, and a washer a4.

[0009] The first support a1 is configured as an integrated support platform. The first support a1 is provided with a set of support mounting holes and a set of platform mounting holes. The second support a2 includes a mounting base and a connecting body vertically arranged on the mounting base. The mounting base of the second support a2 is fixedly installed on the side of the first support a1 near the connecting bracket 11a through the support mounting holes, cylindrical head screws a3 and washers a4. The first support a1 is installed as a whole on the upper end face of the mounting platform 11 through the platform mounting holes and the matching connecting structure.

[0010] A clutch mounting structure is provided on the upper surface of the other side of the first support a1, and the clutch is mounted through the clutch mounting structure, the second support a2 and the rotating shaft used in cooperation.

[0011] Optionally, in the product installation and adjustment platform for the aircraft control system as described above, the bracket assembly 1 includes: bracket I12, bushing I6 and bushing II7; the bracket I12 includes a mounting base and two ears vertically disposed on the mounting base, with bushing I6 fitted into one ear hole of the two ears and bushing II7 fitted into the other ear hole.

[0012] Optionally, in the product installation and adjustment platform for the aircraft control system as described above, the pull rod assembly 2 includes: an external thread pull rod I 13, a hexagonal thick nut I 14, an internal thread pull rod 16, an external thread pull rod II 17, a hexagonal thick nut II 18, two spherical bearings 10, and two angular vertical single-ear stop washers 15.

[0013] The internal threaded tie rod 16 has internal threads at both ends. One end of the internal thread is screwed to the external threaded tie rod I13, and the other end of the internal thread is screwed to the external threaded tie rod II17. A hexagonal thick nut I14 is screwed between the external threaded tie rod I13 and the internal threaded tie rod 16, and a hexagonal thick nut II18 is screwed between the external threaded tie rod II17 and the internal threaded tie rod 16. Furthermore, a angular vertical single-ear locking washer 15 is provided between the hexagonal thick nut I14 and the internal threaded tie rod 16, and between the hexagonal thick nut II18 and the internal threaded tie rod 16, respectively, for preventing thread loosening.

[0014] Each end of the external threaded tie rod I13 and external threaded tie rod II17 is equipped with a spherical bearing 10 for connecting with the double ears of the bracket assembly 1.

[0015] Optionally, in the product installation and adjustment platform for aircraft control systems as described above,

[0016] In the pull rod assembly 2, the pitch of the external threaded pull rod I13 connected to the hexagonal thick nut I14 and the pitch of the external threaded pull rod II17 connected to the hexagonal thick nut II18 are different, one is used for coarse adjustment and the other is used for fine adjustment.

[0017] Optionally, in the product installation and adjustment platform for aircraft control systems as described above,

[0018] The triangular chain disk 3 is configured as an equilateral triangle structure, with two corners configured as double-ear structures and the other corner configured as a single-ear structure. The two corners of the triangular chain disk 3 are connected to the other ends of the two tie rod assemblies 2, and the double-ear structure at the other corner is hinged to the connecting bracket 11a of the mounting platform 11.

[0019] Among them, bushing I6 and bushing II7 are respectively fitted into the double ears of the connecting bracket 11a, and a joint bearing 10 is assembled in the single ear hole of the triangular chain disk 3 that is connected to the connecting bracket 11a.

[0020] Optionally, the product installation and adjustment platform for the aircraft control system described above also includes: hexagonal head bolts 4, washers 5, hexagonal slotted flat nuts 8, and cotter pins 9;

[0021] The bracket assembly 1 and the tie rod assembly 2 are connected by a hexagonal head bolt 4, a washer 5, a hexagonal groove flat nut 8, and a cotter pin 9.

[0022] The tie rod assembly 2 and the double-ear structure of the triangular chain disc 3 are connected by a hexagonal head bolt 4, a washer 5, a hexagonal groove flat nut 8 and a cotter pin 9.

[0023] The triangular chain disc 3 and the connecting bracket 11a of the mounting bracket 11 are connected by hexagonal head bolts 4, washers 5, hexagonal groove flat nuts 8 and cotter pins 9.

[0024] Optionally, in the product installation and adjustment platform for aircraft control systems as described above,

[0025] The fuselage mounting bracket 11b on the lower side of the mounting bracket 11 is configured as a trapezoidal frame structure. The four bottom feet of the trapezoidal frame are provided with mounting bosses, which are used to fit against the arc-shaped skin of the aircraft's internal fuselage structure through the four mounting bosses and are connected to the aircraft through bolts and nuts.

[0026] The beneficial effects of the present invention: The embodiments of the present invention provide a product installation and adjustment platform for an aircraft control system. A connecting bracket 11a is vertically arranged on the upper surface of one side of the mounting platform 11, and an airframe mounting bracket 11b is arranged on the lower surface of the other side of the platform. The upper surface of the mounting platform 11 is fixedly connected to the support platform of the support assembly a, and a clutch is installed through the installation structures arranged on both sides of the support assembly a. One end of each of the two tie rod assemblies 2 is hinged to the double-ear portion of one bracket assembly 1, and the other end is hinged to the double-ear structure at two corners of the triangular chain disc 3. The other corner of the triangular chain disc 3 is hinged to the connecting bracket 11a on one side of the mounting platform 11. This product installation and adjustment platform is fixedly connected to the arc-shaped skin of the aircraft's internal airframe structure through the airframe mounting bracket 11b of the mounting platform 11, and is also fixedly connected to both sides of the aircraft's main beam through the mounting end faces of the two bracket assemblies 1. The product installation and adjustment platform provided by the embodiments of the present invention has the following beneficial effects:

[0027] First, the bracket assembly 1 and the mounting platform 11 bear external loads, thereby improving the ability to resist external interference.

[0028] Secondly, by using the product installation and adjustment platform of the aircraft control system, the product support component a can be directly fixedly installed on the mounting frame 11. Compared with the original product installation structure using two side supports, it significantly reduces the design and processing difficulty of the product mounting frame, effectively reduces the installation difficulty of the product, and effectively reduces the disassembly and assembly time of the product.

[0029] Third, the tie rod assembly 2 uses two threads with different pitches, one for coarse adjustment and the other for fine adjustment, to achieve fine adjustment of the length of the tie rod assembly 2.

[0030] Fourth, by using two bracket assemblies 1, two tie rod assemblies 2, a triangular chain disc 3, and five spherical bearings 10 together, multiple installation interfaces and adjustments in multiple directions can be achieved, which can effectively prevent the occurrence of product malfunctions due to improper installation.

[0031] The product installation and adjustment platform for aircraft control systems provided by the embodiments of the present invention solves the problem of large assembly tolerances in two different parts of the aircraft, reduces the difficulty of installing and debugging a certain type of clutch on the aircraft, solves the frequent failures caused by improper assembly of the product, and improves the aircraft's resistance to external interference and its reliability. Attached Figure Description

[0032] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

[0033] Figure 1 This is a schematic diagram of the installation structure of a certain type of clutch.

[0034] Figure 2 for Figure 1 The diagram shows a certain type of clutch installed in an aircraft structure.

[0035] Figure 3 A schematic diagram of the overall structure of a product installation and adjustment platform for an aircraft control system provided in an embodiment of the present invention;

[0036] Figure 4 for Figure 3 The illustrated embodiment provides a front view of a product installation and adjustment platform for an aircraft control system.

[0037] Figure 5 for Figure 3 A side view of a product installation and adjustment platform for an aircraft control system provided in the illustrated embodiment;

[0038] Figure 6 A front view of the support assembly in a product installation and adjustment platform for an aircraft control system provided in an embodiment of the present invention;

[0039] Figure 7 for Figure 6 A top view of the support assembly provided in the illustrated embodiment;

[0040] Figure 8 A schematic diagram of the structure of the product installation and adjustment platform for an aircraft control system after the clutch is installed, as provided in an embodiment of the present invention.

[0041] Figure 9 A three-dimensional structural diagram of the product installation and adjustment platform for an aircraft control system after the clutch is installed, as provided in an embodiment of the present invention.

[0042] Figure 10 This is a front view of the tie rod assembly in a product installation and adjustment platform for an aircraft control system provided in an embodiment of the present invention;

[0043] Figure 11 The diagram shows the structure of the tie rod assembly in the product installation and adjustment platform for an aircraft control system provided in the embodiment of the present invention. Figure a is the main view and Figure b is a cross-sectional view along AA in Figure a.

[0044] Figure 12This is a schematic diagram of the overall structure of the product installation and adjustment platform for an aircraft control system provided in an embodiment of the present invention, without the support assembly installed.

[0045] Figure 13 for Figure 12 The illustrated embodiment provides a front view of a product installation and adjustment platform for an aircraft control system without the support assembly installed.

[0046] Figure 14 for Figure 12 The side view of the product installation and adjustment platform for an aircraft control system provided in the illustrated embodiment, without the support assembly installed;

[0047] Figure 15 for Figure 13 The illustrated embodiment provides a cross-sectional view along EE in a product installation and adjustment platform for an aircraft control system. Detailed Implementation

[0048] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

[0049] As explained in the background section above, aircraft safety can be improved by installing a model clutch in the aircraft operating system. Figure 1 This is a schematic diagram of the installation structure of a certain type of clutch. Figure 2 for Figure 1 The diagram shows a schematic of a certain type of clutch installed in an aircraft structure. Figure 1 As shown, a certain type of clutch is connected to the machine body via a left bracket and a right bracket, respectively. The left and right brackets are mainly connected by a tube shaft, on which the remaining components of the product are mounted. Figure 2 As shown, a certain type of clutch is installed on the left side of the center wing II spars of frame 30 in the forward direction of the aircraft. The left support (nearly square) of the clutch is fixed by two T-shaped angle brackets at the rear of the center wing II spars. The right support (nearly triangular) is connected to frame 31 of the fuselage by two bolts on the left and two on the right. There are deviations in the manufacturing and assembly of the center wing and the fuselage. When this type of clutch is connected to the aircraft II spars via the left support and to the internal fuselage structure via the right support, the assembly clearance is adjusted by adding adjusting shims. Due to the limited space on the aircraft, adding adjusting shims is difficult to operate and time-consuming. If there is a large assembly clearance between the two supports and the fuselage, the assembly stress often occurs when connecting to the fuselage with screws, leading to product failure, high failure rate, high maintenance cost, and seriously affecting the reliability of the product.

[0050] This invention provides a product installation and adjustment platform for an aircraft control system. To address the installation structure of the bracket used for clutch installation and the internal fuselage structure, the original bracket is structurally modified by dividing it into two parts: one part is installed on the fuselage structure, and the other part is installed on the platform along with the clutch.

[0051] The present invention provides the following specific embodiments, which can be combined with each other. For the same or similar concepts or processes, they may not be described again in some embodiments.

[0052] Figure 3 This is a schematic diagram of the overall structure of a product installation and adjustment platform for an aircraft control system provided in an embodiment of the present invention. Figure 4 for Figure 3 The illustrated embodiment provides a front view of a product installation and adjustment platform for an aircraft control system. Figure 5 for Figure 3 The illustrated embodiment provides a side view of a product installation and adjustment platform for an aircraft control system.

[0053] Reference Figures 3 to 5 As shown, there are support assembly a, two bracket assemblies 1, two tie rod assemblies 2, triangular chain disc 3, and mounting platform 11.

[0054] In this embodiment of the invention, the mounting frame 11 is configured as a platform structure, for example, an integrated platform. A connecting bracket 11a is vertically arranged on the upper surface of one side of the platform, and an organic mounting frame 11b is arranged on the lower surface of the other side of the platform. The upper surface of the platform of the mounting frame 11 is fixedly connected to the support platform of the support assembly a, and the clutch is installed through the mounting structures arranged on both sides of the support assembly a.

[0055] In this embodiment of the invention, one end of each of the two pull rod assemblies 2 is hinged to the double ear portion of one bracket assembly 1, and the other end is hinged to the double ear structure at two corners of the triangular chain disk 3. The other corner of the triangular chain disk 3 is hinged to the connecting bracket 11a on one side of the mounting platform 11. The fuselage mounting bracket 11b on the lower end face of the other side of the mounting platform 11 is fixedly connected to the internal fuselage structure of the aircraft. The two bracket assemblies 1 are respectively attached to and fixedly connected to both sides of the aircraft II main beam through their mounting end faces.

[0056] In this embodiment of the invention, the support assembly a is the main structure for mounting the clutch in the product installation and adjustment platform. In one implementation of this embodiment, the support assembly a includes: a first support a1, a second support a2, a cylindrical head screw a3, and a washer a4. Figure 6 This is a front view of the support assembly in the product installation and adjustment platform for an aircraft control system provided in an embodiment of the present invention. Figure 7 for Figure 6 A top view of the support assembly provided in the illustrated embodiment.

[0057] See Figure 6 and Figure 7 As shown, the first support a1 is configured as an integrated support platform, and a set of support mounting holes are provided on the first support a1. Figure 7 Taking four as an example, and a set of platform mounting holes, the second support a2 includes a mounting base and a connecting body vertically set on the mounting base. The mounting base of the second support a2 is placed on the first support a1 near the side of the connecting bracket 11a. After the mounting holes of the second support a2 are aligned with the mounting holes of the support, they are fixedly connected by four cylindrical head screws a3 with safety locks and washers a4. In addition, the first support a1 is installed as a whole on the upper surface of the mounting platform 11 through the platform mounting holes and the matching connecting structure.

[0058] In this embodiment of the invention, a clutch mounting structure is provided on the upper surface of the other side of the first support a1. The clutch is mounted through the clutch mounting structure, the second support a2, and the cooperating rotating shaft. Figure 8 The diagram shown is a structural schematic of the product installation and adjustment platform for an aircraft control system after the clutch is installed, as provided in an embodiment of the present invention. Figure 9 The figure shown is a three-dimensional structural diagram of the product installation and adjustment platform for an aircraft control system provided in an embodiment of the present invention after the clutch is installed.

[0059] In this embodiment of the invention, the two bracket assemblies 1 are attached and fixedly connected to both sides of the aircraft II main beam via their mounting end faces. For example... Figure 10 The image shown is a front view of the tie rod assembly in the product installation and adjustment platform for an aircraft control system provided in an embodiment of the present invention. The bracket assembly 1 includes: bracket I12, bushing I6, and bushing II7; bracket I12 includes a mounting base and two ears vertically disposed on the mounting base, bushing I6 is fitted into one ear hole of the two ears, and bushing II7 is fitted into the other ear hole.

[0060] Reference Figures 3 to 5 As shown, the flat end of the mounting base of bracket I12 in bracket assembly 1 is its mounting end face with the main beam of aircraft II, and it is connected to the tie rod assembly 2 through the double ears and the bushings I6 and II7 inserted therein.

[0061] In one implementation of this invention, the pull rod assembly 2 includes: an external thread pull rod I 13, a hexagonal thick nut I 14, an internal thread pull rod 16, an external thread pull rod II 17, a hexagonal thick nut II 18, two spherical bearings 10, and two angular vertical single-ear stop washers 15. Figure 11 The diagram shows the structure of the tie rod assembly in the product installation and adjustment platform for an aircraft control system provided in an embodiment of the present invention. Figure a is the main view, and Figure b is a cross-sectional view along AA in Figure a.

[0062] In this implementation, the internal threaded tie rod 16 has internal threads at both ends. One end is threaded and fixed to the external threaded tie rod I 13, and the other end is threaded and fixed to the external threaded tie rod II 17. A hexagonal thick nut I 14 is threaded between the external threaded tie rod I 13 and the internal threaded tie rod 16, and a hexagonal thick nut II 18 is threaded between the external threaded tie rod II 17 and the internal threaded tie rod 16. A angular vertical single-ear locking washer 15 is provided between the hexagonal thick nut I 14 and the internal threaded tie rod 16, and between the hexagonal thick nut II 18 and the internal threaded tie rod 16, respectively, to prevent thread loosening. Additionally, a spherical bearing 10 is installed at the end of each external threaded tie rod I 13 and external threaded tie rod II 17. After engaging with the double-ear portion of the bracket assembly 1, the hinged portion of each tie rod assembly 2 and the bracket assembly 1 can rotate flexibly.

[0063] In this implementation, the two angular vertical single-ear stop washers 15 are used to prevent thread loosening, and are respectively used to limit the relative movement between the hexagonal thick nut I 14 and the external threaded tie rod I 13, and between the hexagonal thick nut II 18 and the external threaded tie rod II 17.

[0064] It should be noted that in the tie rod assembly 2, the pitch of the external thread tie rod I13 connected to the hexagonal thick nut I14 is different from the pitch of the external thread tie rod II17 connected to the hexagonal thick nut II18. One is used for coarse adjustment and the other for fine adjustment.

[0065] like Figure 12 This is a schematic diagram of the overall structure of the product installation and adjustment platform for an aircraft control system provided in an embodiment of the present invention, without the support assembly installed. Figure 13 for Figure 12 The illustrated embodiment provides a front view of the product installation and adjustment platform for an aircraft control system without the support assembly installed. Figure 14 for Figure 12 The illustrated embodiment shows a side view of the product installation and adjustment platform for an aircraft control system without the support assembly installed. Figure 15 for Figure 13 The illustrated embodiment provides a cross-sectional view along EE in a product installation and adjustment platform for an aircraft control system.

[0066] In one implementation of this invention, the triangular chain disk 3 is configured as an equilateral triangle structure, with two corners configured as double-ear structures and the other corner configured as a single-ear structure. The double-ear structures at the two corners of the triangular chain disk 3 are connected to the other ends of the two pull rod assemblies 2, and the double-ear structure at the other corner is hinged to the connecting bracket 11a of the mounting platform 11.

[0067] Similar to the connection structure between the bracket assembly 1 and the pull rod assembly 2, bushing I6 and bushing II7 are respectively fitted into the double ears of the connecting bracket 11a, and a spherical bearing 10 is assembled in the single ear hole of the triangular chain disc 3 that connects to the connecting bracket 11a.

[0068] It should be noted that, in this embodiment of the invention, the two bracket assemblies 1 used to connect with the main beam of the aircraft II are connected to the mounting platform 11 in sequence through the tie rod assembly 2, the triangular chain 3, and the connecting bracket 11a. The connecting bracket 11a and the mounting platform 11 are an integral structure. The entire product installation and adjustment platform bears the external load through the bracket I 12 in the bracket assembly 1 and the mounting platform 11, which effectively improves the ability to resist external interference.

[0069] In one embodiment of the present invention, the fuselage mounting bracket 11b on the lower side of the mounting bracket 11 is configured as a trapezoidal frame structure. The four bases of the trapezoidal frame are provided with mounting bosses, which are used to fit against the arc-shaped skin of the aircraft's internal fuselage structure and are connected to the aircraft via bolts and nuts. It should be noted that the mounting bosses on both sides of the bottom of the fuselage mounting bracket 11b form an arc-shaped structure, and this arc-shaped structure is configured to have a radius equal to that of the fuselage structure.

[0070] like Figures 3 to 15 As shown, the product installation and adjustment platform for aircraft control systems provided in this embodiment of the invention further includes: hexagonal head bolts 4, washers 5, hexagonal groove flat nuts 8, and cotter pins 9.

[0071] In specific implementation, the bracket assembly 1 and the tie rod assembly 2 are connected by hexagonal head bolts 4, washers 5, hexagonal groove flat nuts 8 and cotter pins 9;

[0072] The pull rod assembly 2 and the double-ear structure of the triangular chain 3 are connected by hexagonal head bolts 4, washers 5, hexagonal slotted flat nuts 8 and cotter pins 9;

[0073] The triangular chain disc 3 and the connecting bracket 11a of the mounting bracket 11 are connected by hexagonal head bolts 4, washers 5, hexagonal groove flat nuts 8 and cotter pins 9.

[0074] The product installation and adjustment platform for aircraft control systems provided in this embodiment of the invention has the following beneficial effects:

[0075] First, the bracket assembly 1 and the mounting platform 11 bear external loads, thereby improving the ability to resist external interference.

[0076] Secondly, by using the product installation and adjustment platform of the aircraft control system, the product support component a can be directly fixedly installed on the mounting frame 11. Compared with the original product installation structure using two side supports, it significantly reduces the design and processing difficulty of the product mounting frame, effectively reduces the installation difficulty of the product, and effectively reduces the disassembly and assembly time of the product.

[0077] Third, the tie rod assembly 2 uses two threads with different pitches, one for coarse adjustment and the other for fine adjustment, to achieve fine adjustment of the length of the tie rod assembly 2.

[0078] Fourth, through the coordinated use of two bracket assemblies 1, two tie rod assemblies 2, a triangular chain disc 3, and five spherical bearings 10, multiple installation interfaces and adjustments in multiple directions can be achieved, effectively preventing product malfunctions caused by improper installation. This is specifically reflected in the following aspects:

[0079] On the one hand, in order to ensure that the two bracket assemblies 1 can adapt to the horizontal distance between the two T-shaped angle members on the II main beam of the aircraft center wing, the horizontal distance between the mounting end faces of the two bracket assemblies 1 can be adjusted by changing the length and included angle of the tie rod assembly 2; the original adjusting shim between the left bracket and the II main beam can be eliminated, making adjustment convenient;

[0080] On the other hand, in order to ensure the installation gap between the overall mounting platform 11 and the arc-shaped skin of the aircraft's internal structure, the present invention can adjust the vertical distance between the two bracket assemblies 1 and the upper surface of the mounting platform 11 by changing the length and included angle of the two tie rod assemblies 2, thereby changing the installation gap between the bottom mounting boss of the mounting platform 11 and the arc-shaped skin of the aircraft structure; thus eliminating the need for the original adjusting washers between the bottom sides of the right bracket and the aircraft structure.

[0081] On the other hand, since the body structure connected to the mounting frame 11 is an arc-shaped skin, there is a wedge-shaped gap between the original right bracket and the body after assembly, and the two cannot fit together. To address this problem, the present invention designs the bottom boss of the mounting frame 11 as an arc shape with the same radius as the body structure, and drives the triangular chain disk 3 to rotate adaptively by changing the angle of the tie rod assembly 2, so that the mounting frame 11 can rotate along the hinge point, thereby ensuring that the bottom boss of the mounting frame 11 fits with the body structure.

[0082] On the other hand, since the spherical bearing 10 can achieve adaptive wobble, and with the combined use of the five spherical bearings, the adjustment gap of the adjustment platform is very large, and the tolerance for product manufacturing differences is relatively high.

[0083] The product installation and adjustment platform for aircraft control systems provided by the embodiments of the present invention solves the problem of large assembly tolerances in two different parts of the aircraft, reduces the difficulty of installing and debugging a certain type of clutch on the aircraft, solves the frequent failures caused by improper assembly of the product, and improves the aircraft's resistance to external interference and its reliability.

[0084] The product installation and adjustment platform for aircraft control systems provided in this invention has been verified in use, effectively improving the reliability of a certain type of clutch in the aircraft control line system, reducing product failure rate, decreasing maintenance cycle and costs, and significantly enhancing aircraft safety. It is projected that this installation and adjustment platform will be installed on over 200 aircraft within the next 10 years, demonstrating significant economic benefits and practical value.

[0085] While the embodiments disclosed in this invention are as described above, they are merely illustrative of the embodiments to facilitate understanding of the invention and are not intended to limit the invention. Any person skilled in the art to which this invention pertains may make any modifications and variations in the form and details of the implementation without departing from the spirit and scope disclosed herein; however, the scope of patent protection for this invention shall still be determined by the scope defined in the appended claims.

Claims

1. A product installation and adjustment platform for an aircraft control system, characterized in that, include: Support assembly (a), two bracket assemblies (1), two tie rod assemblies (2), triangular chain disc (3), and mounting platform (11); The mounting frame (11) is configured as a platform structure. A connecting bracket (11a) is vertically arranged on the upper surface of one side of the platform, and an organic mounting frame (11b) is arranged on the lower surface of the other side of the platform. The upper surface of the platform of the mounting frame (11) is fixedly connected to the support platform of the support assembly (a), and the clutch is installed through the mounting structures arranged on both sides of the support assembly (a). One end of each of the two tie rod assemblies (2) is hinged to the double ear of one bracket assembly (1), and the other end is hinged to the double ear structure at the two corners of the triangular chain disk (3). The other corner of the triangular chain disk (3) is hinged to the connecting bracket (11a) on one side of the mounting platform (11). The fuselage mounting bracket (11b) on the lower end face of the other side of the mounting platform (11) is fixedly connected to the internal fuselage structure of the aircraft. The two bracket assemblies (1) are respectively attached to and fixedly connected to both sides of the aircraft II beam through their mounting end faces.

2. The product installation and adjustment platform for an aircraft control system according to claim 1, characterized in that, The support assembly (a) includes: a first support (a1), a second support (a2), a cylindrical head screw (a3), and a washer (a4); The first support (a1) is configured as an integrated support platform. The first support (a1) is provided with a set of support mounting holes and a set of platform mounting holes. The second support (a2) includes a mounting base and a connecting body vertically arranged on the mounting base. The mounting base of the second support (a2) is fixedly installed on the side of the first support (a1) near the connecting bracket (11a) through the support mounting holes, cylindrical head screws (a3) ​​and washers (a4). The first support (a1) is installed as a whole on the upper surface of the mounting frame (11) through the platform mounting holes and the connecting structure used in conjunction. A clutch mounting structure is provided on the upper surface of the other side of the first support (a1), and the clutch is mounted through the clutch mounting structure, the second support (a2), and the rotating shaft used in conjunction.

3. The product installation and adjustment platform for an aircraft control system according to claim 1, characterized in that, The bracket assembly (1) includes: bracket I (12), bushing I (6) and bushing II (7); the bracket I (12) includes a mounting base and a double ear portion vertically disposed on the mounting base, with bushing I (6) inserted into one ear hole of the double ear portion and bushing II (7) inserted into the other ear hole.

4. The product installation and adjustment platform for an aircraft control system according to claim 3, characterized in that, The pull rod assembly (2) includes: external thread pull rod I (13), hexagonal thick nut I (14), internal thread pull rod (16), external thread pull rod II (17), hexagonal thick nut II (18), two spherical bearings (10) and two angular vertical single-ear stop washers (15); The internal threaded tie rod (16) has internal threads at both ends. One end of the internal thread is screwed to the external threaded tie rod I (13), and the other end of the internal thread is screwed to the external threaded tie rod II (17). A hexagonal thick nut I (14) is screwed between the external threaded tie rod I (13) and the internal threaded tie rod (16), and a hexagonal thick nut II (18) is screwed between the external threaded tie rod II (17) and the internal threaded tie rod (16). A angular vertical single-ear stop washer (15) is provided between the hexagonal thick nut I (14) and the internal threaded tie rod (16), and between the hexagonal thick nut II (18) and the internal threaded tie rod (16), for thread loosening prevention. A spherical bearing (10) is installed at the end of each of the external threaded tie rod I (13) and external threaded tie rod II (17) for connecting with the double ears of the bracket assembly (1).

5. The product installation and adjustment platform for an aircraft control system according to claim 4, characterized in that, In the pull rod assembly (2), the pitch of the external thread pull rod I (13) connected to the hexagonal thick nut I (14) is different from the pitch of the external thread pull rod II (17) connected to the hexagonal thick nut II (18), one is used for coarse adjustment and the other for fine adjustment.

6. The product installation and adjustment platform for an aircraft control system according to claim 4, characterized in that, The triangular chain disk (3) is set as an equilateral triangle structure, with two corners set as double-ear structures and the other corner set as a single-ear structure. The two corners of the triangular chain disk (3) are connected to the other ends of the two tie rod assemblies (2) respectively, and the double-ear structure at one corner is hinged to the connecting bracket (11a) of the mounting frame (11). Among them, bushing I (6) and bushing II (7) are respectively fitted into the double ears of the connecting bracket (11a), and a joint bearing (10) is assembled in the single ear hole of the triangular chain disc (3) connected to the connecting bracket (11a).

7. The product installation and adjustment platform for an aircraft control system according to any one of claims 1 to 5, characterized in that, Also includes: Hex head bolts (4), washers (5), hexagonal slotted flat nuts (8), and cotter pins (9); The bracket assembly (1) and the tie rod assembly (2) are connected by a hexagonal head bolt (4), a washer (5), a hexagonal groove flat nut (8), and a cotter pin (9); The tie rod assembly (2) and the double-ear structure of the triangular chain disc (3) are connected by a hexagonal head bolt (4), a washer (5), a hexagonal groove flat nut (8) and a cotter pin (9); The triangular chain disc (3) is connected to the mounting bracket (11a) of the mounting bracket (11) by a hexagonal head bolt (4), a washer (5), a hexagonal groove flat nut (8), and a cotter pin (9).

8. The product installation and adjustment platform for an aircraft control system according to any one of claims 1 to 5, characterized in that, The fuselage mounting bracket (11b) on the lower side of the mounting bracket (11) is configured as a trapezoidal frame structure. The four bottom feet of the trapezoidal frame are provided with mounting bosses, which are used to fit against the arc-shaped skin of the aircraft's internal fuselage structure through the four mounting bosses and are connected to the aircraft through bolts and nuts. The ring formed by the protrusions on both sides is designed as an arc with the same radius as the body structure.

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