An aircraft wing-to-fuselage assembly aid system

Abstract

The present application relates to a kind of aircraft wing fuselage assembly auxiliary system, belong to the technical field of aircraft assembly, solve the problem of low assembly efficiency in the process of aircraft assembly, installation position is difficult to accurately determine.The system of the present application includes bracket support component, visual guidance component, industrial control center and carrying assembly;Visual guidance component is installed on fuselage installation assembly;Bracket support component includes flexible support assembly and bracket assembly;Two ends of bracket assembly are connected with flexible support assembly;Wing installation assembly is clamped on flexible support assembly;Carrying assembly includes carrying unit and support frame adjustment unit;The lower end of support frame adjustment unit is connected with the carrying unit, and the upper end of support frame adjustment unit is connected with the lower end of bracket assembly;Industrial control center can receive the signal transmitted by visual guidance component and bracket support component, control carrying assembly and bracket support component to make displacement adjustment.The system of the present application is suitable for the butt joint assembly of large component hole system prone to deformation, and is widely used.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft assembly, in particular to an aircraft wing and fuselage assembly auxiliary system. BACKGROUND

[0002] In the assembly process of the late stage of aircraft manufacturing, due to the huge volume of the parts to be assembled, simultaneous assembly and connection at multiple positions of these parts are usually required to ensure reasonable assembly stress and stable structure of the whole aircraft. Multi-point position support is required during the installation process to assist the assembly in the correct position.

[0003] Taking the assembly process of the wing to the fuselage as an example, the wing is usually composed of spars, stringers, beams, ribs and skins. The basic load-bearing components of the wing include longitudinal (along the wing span direction) skeleton, transverse (perpendicular to the wing beam direction along the airflow direction) skeleton and skin. The longitudinal skeleton includes spars, stringers and beams, and the transverse skeleton includes ordinary ribs and reinforced ribs.

[0004] During the wing installation process, due to the characteristics of large weight, large volume, large length span and asymmetric shape of the wing, the auxiliary tooling for wing butt joint installation often cannot withstand the huge gravity of the wing, and due to the offset of the center of gravity of the wing, the bracket stress deformation will also affect the assembly effect, and the locking structure for fixing the wing is complex and difficult to operate.

[0005] Currently, during the process of assembling the wing to the fuselage, the following problems usually exist:

[0006] (1) Large volume, easy to deform, and anisotropic deformation;

[0007] (2) The center of mass and the structural center of gravity are not coincident, causing the uniform support distribution facing the structure and the support distribution facing the mass homogeneity to be unable to be satisfied at the same time;

[0008] (3) The wing is connected with the assembly auxiliary unit, and the connection force will cause secondary structural deformation of the wing;

[0009] (4) The assembly interfaces are difficult to align at the same time, and the installation of each interface will cause anisotropic assembly stress of different parts of the aircraft, causing structural safety hazards under flight stress.

[0010] As a result, the multi-point installation structure shape of the large parts such as the wing and the fuselage in the assembly process does not conform to the theoretical value, which causes the installation interface position of the assembled workpiece to be unable to be quickly and accurately aligned with all the installation interface positions of the assembly workpiece; at the same time, there is anisotropic assembly stress, which poses a hidden danger to the later flight safety.

[0011] Therefore, how to quickly obtain the installation interface position of each assembled workpiece becomes a problem to be solved by those skilled in the art, which provides a basis for scientifically implementing fast and accurate aircraft large piece consistency assembly. SUMMARY

[0012] In view of the above analysis, the present application aims to provide an aircraft wing fuselage assembly auxiliary system and an assembly control method to solve the technical problems of slow alignment of installation position and low assembly efficiency in the existing aircraft large piece assembly process.

[0013] The specific technical solutions are as follows:

[0014] An aircraft wing fuselage assembly auxiliary system is used for assembling a wing installation assembly to a fuselage installation assembly; comprising a bracket support component, a visual guidance component, an industrial control center and a carrying assembly; the visual guidance component is installed on the fuselage installation assembly; the bracket support component comprises a flexible support assembly and a bracket assembly; the bracket assembly is connected with one flexible support assembly at each end; the wing installation assembly is clamped on the flexible support assembly; the carrying assembly comprises a carrying unit and a support frame adjustment unit; the support frame adjustment unit is connected with the carrying unit at the lower end, and connected with the lower end of the bracket assembly at the upper end; the industrial control center can receive signals transmitted by the visual guidance component and the bracket support component, and control displacement adjustment of the carrying assembly and the bracket support component.

[0015] Further, the wing installation assembly is adjustably connected to the bracket support component; further, the bracket assembly is a truss structure.

[0016] Further, the welding structure of the bracket assembly comprises a bracket side plate, a bracket cross beam, a bracket installation unit and a bracket connection unit; the flexible support assembly is connected to the bracket connection unit.

[0017] Further, a plurality of bracket cross beams are evenly distributed between the two bracket side plates to form a bracket main body; the bracket main body is connected with the bracket connection unit at each end; a plurality of flexible adjustment assemblies are arranged in the middle of the bracket main body; the flexible adjustment assemblies are connected to the bracket cross beams.

[0018] Further, the flexible support assembly comprises an upper support part, a lower support part, a support locking unit and a flexible support installation part.

[0019] Further, the support locking unit is hinged to the upper support part and locked on the lower support part; the wing installation assembly is clamped between the upper support part and the lower support part.

[0020] Further, the support locking unit first end is hinged on the upper support part; the support locking unit second end can be adjustably locked on the lower support part; the flexible support mounting part upper part is connected with the lower support part, and the flexible support mounting part outer side is clamped and connected with the bracket connecting unit.

[0021] Further, the flexible support assembly further comprises a flexible support pressure sensor.

[0022] Further, the flexible support sensing unit comprises a flexible support position sensor and a flexible support pressure sensor; the flexible support position sensor is arranged on the upper support part, and can collect a planar coordinate position signal for positioning when the upper support part is mounted on the lower support part; and the flexible support pressure sensor is arranged on the support locking unit.

[0023] Further, the flexible support position sensor can collect a planar coordinate position signal for positioning when the upper support part is mounted on the lower support part; and the flexible support pressure sensor is used for collecting a locking pressure signal to control the locking force.

[0024] Further, the flexible adjustment assembly comprises a flexible adjustment support unit, a flexible adjustment positioning unit and a flexible adjustment support pressure sensor; the flexible adjustment support unit is connected on the upper end of the flexible adjustment positioning unit; the flexible adjustment support pressure sensor is arranged on the flexible adjustment support unit; and the flexible adjustment support unit is provided with a flexible adjustment positioning position sensor.

[0025] Further, the flexible adjustment support unit comprises a flexible adjustment support body and a flexible adjustment support flexible layer; the flexible adjustment support flexible layer is connected on the upper surface of the flexible adjustment support body; and the lower end of the flexible adjustment support body is connected with the upper end of the flexible adjustment positioning unit.

[0026] Further, the flexible adjustment positioning unit comprises a vertical positioning body, a horizontal positioning body and a longitudinal positioning body; the upper end of the vertical positioning body is connected with the flexible adjustment support body; the lower end side of the vertical positioning body is movably connected with the side end of the middle part of the longitudinal positioning body; the lower end of the longitudinal positioning body is movably connected with the upper end surface of the horizontal positioning body; and the side end surface of the horizontal positioning body is connected with the bracket cross beam.

[0027] Further, the visual guiding part comprises a visual support assembly, a main visual unit and an auxiliary visual unit, a visual power unit and a visual signal transmission unit; the main visual unit comprises a main camera, and the auxiliary visual unit comprises an auxiliary camera.

[0028] Further, the auxiliary visual unit is vertically connected to the visual support assembly, and the main camera is movably connected to the visual support assembly.

[0029] Further, the visual support assembly is connected with a pushing unit and an assembly positioning unit.

[0030] Further, the industrial control center comprises a data processor and a position solver; the data processor can process image data collected by the visual guiding component and position / pressure data collected by the sensor, and the position solver calculates the result of the position / pressure data processor to generate control instruction information of starting / stopping / displacement of each execution element.

[0031] Compared with the prior art, the present application can achieve the following beneficial effects:

[0032] 1. The visual guiding component and the pressure sensor and the position sensor can collect and transmit installation position data of the fuselage installation assembly and the wing installation assembly to the industrial control center in real time, and the industrial control center can obtain execution instruction information of starting / stopping / displacement through the data processor and the displacement solver and send the information back to each execution unit in real time, so that the wing installation assembly can reach the correct position along the correct path, and the connection with the fuselage installation assembly can be completed, and the assembly precision and efficiency can be greatly improved.

[0033] 2. The aircraft wing fuselage assembly auxiliary system adopts multiple sensors and visual guiding, and can realize rapid and accurate assembly position alignment process between large deformation parts by using reasonable installation force, accurate jacking position, preliminary position adjustment and accurate position adjustment installation position alignment mode, and the aircraft wing fuselage assembly efficiency and assembly precision are greatly improved.

[0034] 3. The aircraft wing fuselage assembly auxiliary system adopts the assembly lug positioning body and the assembly lug positioning surface thereon and the assembly positioning unit in the visual guiding component to perform omnidirectional positioning on the fuselage installation assembly, so that the position stability of the fuselage installation assembly during assembly can be ensured, the image data collected by the visual unit can have real-time consistency, and the industrial control center can smoothly solve the correct control information.

[0035] Other features and advantages of the present application will be set forth in the following description, and in part will become apparent to those skilled in the art upon examination of the following or can be learned by practice of the present application. The objects and other advantages of the present application can be realized and attained by the structure particularly pointed out in the description and the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0036] The accompanying drawings are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the principles of the application. In the drawings:

[0037] Figure 1 Structure schematic diagram of aircraft assembly auxiliary system for embodiment of the present application Figure 1 ;

[0038] Figure 2 Structure schematic diagram of aircraft assembly auxiliary system for embodiment of the present application Figure 2 ;

[0039] Figure 3 Structure schematic diagram of wing mounting assembly for embodiment of the present application;

[0040] Figure 4 Structure schematic diagram of fuselage mounting assembly for embodiment of the present application;

[0041] Figure 5 Structure schematic diagram of wing mounting body for embodiment of the present application;

[0042] Figure 6 Structure schematic diagram of wing mounting body and fuselage mounting body after installation of visual guiding component for embodiment of the present application;

[0043] Figure 7 Structure schematic diagram of visual guiding component for embodiment of the present application;

[0044] Figure 8 Structure schematic diagram of visual guiding docking device for embodiment of the present application Figure 1 ;

[0045] Figure 9 Structure schematic diagram of visual guiding docking device for embodiment of the present application Figure 2 ;

[0046] Figure 10 Structure schematic diagram of wing mounting adjusting component for embodiment of the present application;

[0047] Figure 11 Structure schematic diagram of bracket supporting component for embodiment of the present application;

[0048] Figure 12 Structure schematic diagram of flexible supporting assembly and bracket assembly installation for embodiment of the present application;

[0049] Figure 13 Structure schematic diagram of flexible supporting assembly for embodiment of the present application;

[0050] Figure 14 Structure schematic diagram of flexible adjusting assembly for embodiment of the present application.

[0051] Reference signs:

[0052] 1. Wing mounting assembly; 11. Wing mounting body; 111. Wing mounting body seat; 112. Wing mounting body lug; 113. Wing mounting body lug hole; 12. Wing body; 121. Wing intermediate body; 122. Wing fuselage; 2. Fuselage mounting assembly; 21-1. First fuselage mounting body; 21-2. Second fuselage mounting body; 21-3. Third fuselage mounting body; 211. Fuselage mounting body seat; 212. Fuselage mounting body lug; 213. Fuselage mounting body lug hole; 22. Fuselage mounting structure; 3. Flexible support assembly; 31. Upper support part; 311. Upper support body; 312. Upper support flexible layer; 32. Lower support part; 321. Lower support body; 3211. Lower support body connecting site; 322. Lower support flexible layer; 33. Support locking unit; 34. Flexible support mounting part; 4. Visual guidance part; 41. Visual support assembly; 411. Support frame; 4111. Pushing unit mounting site; 4112. Guide rail mounting groove; 4113. Auxiliary camera mounting part; 41131. Auxiliary camera mounting site; 4114. Main light source mounting part; 4115. Auxiliary light source mounting site; 4116. Assembly lug positioning body; 41161. Assembly lug positioning surface; 412. Guide rail unit; 4121. Movable guide rail; 4122. Fixed guide rail; 413. Pushing unit; 42. Main visual unit; 421. Main camera; 422. Main camera positioning cylinder; 423. Main light source unit; 4231. Main light source housing; 4232. Main light source light emitter; 4233. Main light source switch; 4234. Main light source fastener; 424. Assembly body positioning unit; 4241. Positioning body mounting part; 4242. Positioning body centering part; 4243. Positioning body main light source light passing hole; 4244. Positioning body pressure sensor; 43. Auxiliary visual unit; 431. Auxiliary camera; 432. Auxiliary camera protection housing; 433. Auxiliary camera light source; 44. Visual power unit; 45. Visual signal transmission unit; 451. Router; 452. Antenna; 46. Mounting housing unit; 5. Flexible adjustment assembly; 51. Flexible adjustment support unit; 511. Flexible adjustment support body; 512. Flexible adjustment support flexible layer; 52. Flexible adjustment positioning unit; 521. Vertical positioning body; 522. Horizontal positioning body; 523. Longitudinal positioning body; 6. Bracket assembly; 61. Bracket side support plate; 62. Bracket cross beam; 63. Bracket mounting unit; 631. Bracket mounting beam; 632. Bracket mounting seat; 64. Bracket connecting unit; 641. Bracket connecting slot; 7. Industrial control center; 8. Carrying assembly; 81. Carrying unit; 82. Support frame adjustment unit. DETAILED DESCRIPTION

[0053] The accompanying drawings, which are incorporated herein by reference, wherein: Figures 1-14The technical solution of the present invention will be described in detail below. The accompanying drawings constitute a part of the present invention and, together with the embodiments of the present invention, are used to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0054] This embodiment is configured as follows:

[0055] (1) The carrier unit 8 runs on the ground, with the ground defining the up and down directions; and the lens of the auxiliary camera is downward.

[0056] (2) The long axis of the bracket assembly 6 is longitudinal and the short axis is transverse.

[0057] This embodiment illustrates an aircraft wing-fuselage assembly assistance system for assembling wing mounting assembly 1 onto fuselage mounting assembly 2.

[0058] The wing mounting assembly 1 includes a wing body 12; the wing body 12 includes a central wing intermediate body 121 and two wingspan portions on both sides, the wingspan portions being wing fuselages 122. The wing intermediate body 121 is used for assembly and fastening, and the wing fuselages 122 are used for assembly and installation. The wing mounting assembly 1 also includes a wing mounting body 11.

[0059] like Figure 3 As shown, wing mounting components 11 are provided at the positions where they are assembled and connected to fuselage mounting components 2. Multiple wing mounting components 11 are installed at the wing intermediate body 121.

[0060] like Figure 5 As shown, the wing mount 11 is provided with a wing mount seat 111, and the wing mount seat 111 is connected to a wing mount lug 112; the wing mount lug 112 is provided with a wing mount lug hole 113 for assembly and fastening.

[0061] The fuselage mounting component 2 includes the fuselage mounting body.

[0062] Figure 4 The fuselage mounting assembly 2 shown represents a portion of the fuselage structure, specifically the portion used to substantially connect the wing mounting assembly 1. Corresponding to the wing mounting base 111, fuselage mounting bodies are provided at the locations where the fuselage mounting assembly 2 and the wing mounting assembly 1 are assembled and connected. Multiple fuselage mounting bodies are distributed and connected to the fuselage mounting structure 22.

[0063] The fuselage mounting body is provided with a fuselage mounting body seat 211, and the fuselage mounting body seat 211 is connected to a fuselage mounting body ear plate 212; the fuselage mounting body ear plate 212 is provided with a fuselage mounting body ear hole 213 for assembly and fastening.

[0064] The positions and structures of the multiple fuselage mounting lugs 213 and the multiple wing mounting lugs 113 correspond one-to-one.

[0065] In order to meet the requirement of installation space, the fuselage mounting body ear hole 213 and the wing mounting body ear hole 113 are one-to-one corresponding in position and structure, and the wing mounting body 11 and the fuselage mounting body can have various structural forms.

[0066] As shown in Figure 4 , the fuselage mounting body has three structural forms matched with the wing mounting body 11. The three fuselage mounting bodies are a first fuselage mounting body 21-1, a second fuselage mounting body 21-2 and a third fuselage mounting body 21-3.

[0067] The fuselage mounting assembly 2 needs to be fixed on the assembly tool; the parts above the carrying unit 8 including the wing mounting assembly 1 need to be hoisted in order by the hoisting machine to the carrying unit 8 and installed in place.

[0068] Next, the technical scheme of the aircraft wing fuselage assembly auxiliary system of the embodiment of the application will be introduced in detail in combination with Figures 1-14 .

[0069] The aircraft wing fuselage assembly auxiliary system includes a bracket supporting component, a visual guidance component 4, an industrial control center 7 and a carrying assembly 8; the bracket supporting component includes a flexible supporting assembly 3 and a bracket assembly 6.

[0070] As shown in Figure 1 , the carrying assembly 8 is one of the actuators controlled by the industrial control center 7, including a carrying unit 81 and a support frame adjustment unit 82. The lower end of the support frame adjustment unit 82 is connected to the carrying unit 81, and the upper end of the support frame adjustment unit 82 is connected to the lower end of the bracket assembly 6.

[0071] As shown in Figure 1 and Figure 2 , specifically, the carrying unit 81 of the embodiment can be a vehicle body capable of plane linear displacement and plane rotary displacement, which can drive the device carried thereon, including the wing mounting assembly 1, to move in the plane. The support frame adjustment unit 82 can drive the bracket assembly 6 to adjust the posture in height and space angle.

[0072] Preferably, the carrying unit 81 of the embodiment is an automatic guided vehicle, and the carrying unit 81 is provided with a carrying unit position sensor for sending the plane position information of the carrying unit 81 to the industrial control center 7, and the industrial control center 7 controls the carrying unit power device to start / stop / displacement, drives the wing mounting assembly 1 to reach the accurate target position at variable speed. The displacement includes linear motion and plane rotary motion.

[0073] Preferably, the support frame adjusting unit 82 of the embodiment comprises a plurality of electric push rods, the lower ends of the electric push rods are fixedly connected to the upper end face of the carrying unit 81, and the lower ends of the electric push rods are connected to the lower end of the bracket assembly 6 through lockable spherical hinges. The industrial control center 7 controls the linkage of the plurality of electric push rods to adjust the pose of the bracket assembly 6.

[0074] As shown in Figure 1 , the industrial control center 7 is integrated in the carrying assembly 8, so that the overall structure is compact.

[0075] As shown in Figure 11 , the bracket assembly 6 is a truss structure, which is movably connected to the support frame adjusting unit 82 downward and holds the wing mounting assembly 1 upward.

[0076] The bracket assembly 6 comprises bracket side support plates 61, bracket cross beams 62, bracket mounting units 63 and bracket connecting units 64.

[0077] A plurality of bracket cross beams 62 are evenly distributed between the two bracket side support plates 61 to form a truss structure bracket main body.

[0078] The embodiment comprises two bracket mounting units 63, which are separately arranged on both sides of the bracket main body. The bracket mounting unit 63 is a square tube structure, comprising a bracket mounting beam 631 and a bracket mounting seat 632.

[0079] The bracket mounting beam 631 is symmetrically and fixedly connected to the two bracket side support plates 61; the lower side of the two ends of the bracket mounting beam 631 is respectively provided with a bracket mounting seat 632. The lower end of the bracket mounting seat 632 is connected to the upper end of the support frame adjusting unit 82 through a self-locking spherical hinge.

[0080] The four bracket mounting seats 632 of the embodiment are respectively connected to the output ends of the four electric push rods of the support frame adjusting unit 82, and the industrial control center 7 can control the plurality of electric push rods to produce the same / different displacement to adjust the real-time attitude of the bracket assembly 6 and the wing mounting assembly 1 connected thereto.

[0081] Two bracket connecting units 64 are separately arranged at the two ends of the bracket main body.

[0082] As shown in Figure 11 and Figure 12 , the bracket connecting unit 64 is an open frame support structure composed of a plate member, and the bracket connecting unit 64 is connected to the two ends of the bracket main body at an outwardly upwardly inclined angle, so that the upwardly connected wing mounting assembly 1 can be higher than the body of the adjusting bracket assembly 6, avoiding structural interference in the butt joint assembly process of the wing mounting assembly 1 and the wing mounting assembly 1.

[0083] The bracket connecting unit 64 is provided with a bracket connecting notch 641 on the outwardly extending side face, which is used for clamping a fixed position and connecting a flexible support assembly 3.

[0084] As shown in Figure 1 and Figure 2 Two flexible support assemblies 3 of the embodiment are symmetrically connected at both ends of the bracket assembly 6. The flexible support assembly 3 in the wing mounting assembly 1 is connected to the bracket assembly 6 through the bracket connecting unit 64.

[0085] As shown in Figure 10 The flexible support assembly 3 is specifically connected at the bracket connecting slot 641 of the bracket connecting unit 64.

[0086] As shown in Figure 13 The flexible support assembly 3 includes an upper support part 31, a lower support part 32, a support locking unit 33, and a flexible support mounting part 34. The upper support part 31 and the lower support part 32 are oppositely arranged, and the wing body 122 of the wing mounting assembly 1 is clamped between the upper support part 31 and the lower support part 32.

[0087] Specifically, the first end of the support locking unit 33 is hinged to the upper support part 31; the second end of the support locking unit 33 is adjustably locked to the lower support part 32; the inner side of the flexible support mounting part 34 is connected to the lower support part 32, and the outer side of the flexible support mounting part 34 is connected to the bracket connecting unit 64.

[0088] Specifically, the upper support part 31 includes an upper support body 311 and an upper support flexible layer 312; the lower support part 32 includes a lower support body 321 and a lower support flexible layer 322. The upper support body 311 and the lower support body 321 are rigid arc-shaped support clamping plates, and the upper support flexible layer 312 is an arc-shaped clamping plate of the lower support flexible layer 322. The lower end surface of the lower support body 321 is a plane.

[0089] Preferably, the arc-shaped clamping plate is a soft fixed structure made of non-woven fabric and felt process, the transverse curvature and longitudinal cross-sectional shape of the arc-shaped clamping plate are consistent with the corresponding position curved surface of the wing body 122, and the outer surface of the arc-shaped clamping plate is a working surface that closely contacts the wing body 122.

[0090] The arc-shaped clamping plate being a soft fixed structure can ensure that the clamping process of the flexible support assembly 3 does not damage the wing mounting assembly 1, and can overcome the inconsistent clamping stress at different positions caused by the manufacturing error that makes the clamping surface and the wing mounting assembly 1 not completely matched through flexible contact, thereby avoiding unnecessary damage or stress deformation of the wing mounting assembly 1.

[0091] The lower support body 321 is provided with lower support body connecting ears at the transverse ends of the bottom surface, and the lower support body connecting ears are provided with lower support body connecting positions 3211. In the embodiment, the lower support body connecting positions 3211 are open slots.

[0092] The flexible support assembly 3 further includes a flexible support sensing unit. The flexible support sensing unit includes a flexible support position sensor and a flexible support pressure sensor.

[0093] When the wing installation assembly 1 is placed on the lower support part 32 and adjusted to the position, the upper support part 31 needs to be hoisted to the position, clamped to the wing installation assembly 1, and locked with the lower support part 32 through the support locking unit 33.

[0094] The set position of the upper support part 31 of the embodiment is provided with a flexible support position sensor.

[0095] The position sensor involved in the embodiment can have various forms, including but not limited to a position marker. The position marker can be recognized and position information can be collected by a visual sensor, and communicated with the industrial control center 7.

[0096] The flexible support position sensor can recognize the planar coordinate position of the upper support part 31 in real time, and transmit the collected planar coordinate position signal of the upper support part 31 to the industrial control center 7; the industrial control center 7 processes and generates hoisting equipment displacement information by receiving the signal of the visual sensor, and drives the upper support part 31 to adjust the position in the plane. The visual sensor can be installed on the hoisting equipment.

[0097] After the upper support part 31 is adjusted to the position, it is lowered to the upper surface of the wing installation assembly 1, and the support locking unit 33 is locked.

[0098] The flexible support pressure sensor is arranged on the support locking unit 33.

[0099] The flexible support pressure recognition device is arranged at the lower support body connecting position 3211 of the embodiment; the flexible support pressure recognition device can be a flexible support pressure sensor or a flexible support pressure gauge; wherein the flexible support pressure gauge can prompt whether the locking force reaches the rated value.

[0100] Preferably, the flexible support pressure recognition device is a flexible support pressure sensor. The flexible support pressure sensor can transmit the locking force of the support locking unit 33 to the industrial control center 7 in real time, and the industrial control center 7 issues a locking force standard warning sound when the pressure reaches the rated value.

[0101] The support locking unit 33 can be any structure unit hinged to the upper support part 31 and locked to the lower support part 32.

[0102] The support locking unit 33 of the embodiment adopts a hinged screw rod; the upper end of the movable rod of the hinged screw rod is connected to the end of the upper support part 31 through a hinge base, the lower end of the movable rod of the hinged screw rod is clamped into the open slot of the lower support body connecting position 3211, and is locked to the lower support body connecting lug through a fastener.

[0103] The flexible support mounting part 34 includes a side eccentric bracket 341 and a flexible support mounting fixed frame 342.

[0104] As Figure 13 shown, the side eccentric bracket 341 is a truss structure.

[0105] Because the wing span shape of the wing body 122 makes its own center of mass deviate from its structural center in the lateral direction, the side eccentric bracket 341 is designed as an eccentric truss so that in the lateral direction, the center of mass of the wing mounting assembly 1 falls on the section surface in the bracket assembly 6, ensuring that the wing mounting assembly 1 does not produce gravitational deflection during assembly and can be stably placed on the bracket assembly 6.

[0106] The flexible support mounting fixed frame 342 is fastened and connected at the bracket connecting slot 641. The flexible support assembly 3 is fixedly connected to the bracket connecting unit 64 through the flexible support mounting fixed frame 342.

[0107] Optionally, the bracket support part of the embodiment can also include a flexible adjustment assembly 5, which can assist the flexible support assembly 3 in adjusting the attitude of the wing mounting assembly 1 with a wing span during installation, so that the wing mounting assembly 1 with an elongated wing body 122 has a consistent overall attitude with the designed structure during assembly, ensuring that the installation position of the wing mounting assembly 1 is quickly and correctly matched with the installation position of the fuselage mounting assembly 2, and the assembly work is efficiently completed.

[0108] As Figure 10 and Figure 14 shown, the embodiment is provided with four flexible adjustment assemblies 5, which are symmetrically connected to the bracket cross beam 61 of the bracket assembly 6 in two groups, and the symmetric center is the center section of the wing intermediate body 121.

[0109] As Figure 14 shown, the flexible adjustment assembly 5 includes a flexible adjustment support unit 51 and a flexible adjustment positioning unit 52. The flexible adjustment support unit 51 is connected to the upper end of the flexible adjustment positioning unit 52. The flexible adjustment assembly 5 also includes a flexible adjustment support pressure sensor. The flexible adjustment support pressure sensor is arranged on the flexible adjustment support unit 51.

[0110] Specifically, the flexible adjustment support unit 51 includes a flexible adjustment support body 511 and a flexible adjustment support flexible layer 512; the flexible adjustment support flexible layer 512 is connected to the upper surface of the flexible adjustment support body 511, and the lower end of the flexible adjustment support body 511 is connected to the upper end of the flexible adjustment positioning unit 52. The flexible adjustment support pressure sensor is arranged on the upper surface of the flexible adjustment support body 511 and in contact with the flexible adjustment support flexible layer 512.

[0111] The flexible adjustment support flexible layer 512 is a soft fixed structure with an arc-shaped upper surface and is made of a non-woven fabric plus felt process. The arc-shaped upper surface of the flexible adjustment support flexible layer 512 is a working surface and is designed to be shaped with the lower surface of the wing body 122 and closely fitted.

[0112] The arc-shaped upper surface of the flexible adjustment support flexible layer 512 of each flexible adjustment assembly 5 is designed in three-dimensional consistency with the position of the wing body 122 in contact upward.

[0113] Preferably, the flexible adjustment support pressure sensor is centrally arranged on the upper part of the flexible adjustment support body 511, and the flexible adjustment support pressure sensor can collect the pressure when the flexible adjustment positioning unit 52 lifts the flexible adjustment support body 511 to contact the lower surface of the wing body 122. The data collected by the flexible adjustment support pressure sensor is transmitted to the industrial control center 7 in real time.

[0114] The flexible adjustment positioning unit 52 includes a vertical positioning body 521, a horizontal positioning body 522 and a longitudinal positioning body 523 respectively provided with a respective servo motor; the start and stop of the servo motor are controlled by a relay, and the opening and closing of the relay are controlled by the industrial control center 7; the mounting surface of the horizontal positioning body 522 is connected to the bracket cross beam 62; the horizontal positioning body 522, the longitudinal positioning body 523 and the vertical positioning body 521 are connected in sequence; the upper end of the vertical positioning body 521 is connected to the flexible adjustment support body 511; the horizontal positioning body 522 and the longitudinal positioning body 523 are provided with sliding guide rails for driving load displacement, and the vertical positioning body 521 is provided with a guide rod for lifting the flexible adjustment support unit 51.

[0115] The industrial control center 7 controls the displacement of the flexible adjustment positioning unit 52, so that the flexible adjustment support unit 51 makes longitudinal displacement with the longitudinal positioning body 523 and horizontal displacement with the horizontal positioning body 522, so as to adjust the attitude of the flexible adjustment support flexible layer 512, so as to be consistent with the curved surface position of the wing body 122 at the position to be supported; then, the flexible adjustment support unit 51 makes up and down displacement with the vertical positioning body 521, so as to control the flexible adjustment support unit 51 to support the wing body 122.

[0116] Specifically, the flexible adjustment support position sensor includes vertical, horizontal and longitudinal position sensors, specifically adjustment support vertical position sensor, adjustment support horizontal position sensor and adjustment support longitudinal position sensor.

[0117] Preferably, in the embodiment, the adjustment support vertical position sensor is a servo motor encoder on the vertical positioning body 521; the adjustment support horizontal position sensor is a servo motor encoder on the horizontal positioning body 522, and the adjustment support longitudinal position sensor is a servo motor encoder on the longitudinal positioning body 523. Each servo motor encoder communicates with the industrial control center 7 in real time to obtain real-time position deviation.

[0118] The industrial control center 7 simultaneously controls multiple flexible adjustment assemblies 5 to adjust the attitude.

[0119] Specifically, the industrial control center 7 receives real-time data of the flexible adjustment support position sensor in each transverse adjustment body 522 and longitudinal adjustment body 523, calculates the flexible adjustment support transverse displacement information and the flexible adjustment support longitudinal displacement information, and the transverse adjustment body 522 and the longitudinal adjustment body 523 generate displacement accordingly to adjust the posture of the flexible adjustment support unit 51 relative to the corresponding lower surface of the wing body 122.

[0120] The industrial control center 7 receives real-time data of the flexible adjustment support position sensor in each vertical adjustment body 521, calculates the flexible adjustment support vertical displacement information, and adjusts the height information of the flexible adjustment support unit 51 relative to the corresponding lower surface of the wing body 122. The vertical adjustment body 521 generates displacement accordingly to move the flexible adjustment support unit 51 to the corresponding lower surface of the wing body 122. The industrial control center 7 simultaneously receives real-time data of the flexible adjustment support pressure sensor, and generates execution information of the stop displacement of the vertical adjustment body 521 when the pressure data reaches the rated value.

[0121] The arrangement of the flexible adjustment assembly 5 can greatly reduce the influence of the deformation of the wing mounting assembly 1 on the assembly, and is suitable for all large thin-walled part assembly processes.

[0122] Under the joint clamping and posture adjustment of the flexible support assembly 3, the flexible adjustment assembly 5, the carrying unit 81 and the support frame adjustment unit 82, the wing mounting assembly 1 as the assembled part can approach the fuselage mounting assembly 2 as the assembled part in a correct and reliable posture.

[0123] The visual guidance component 4 can guide the wing mounting body ear hole 113 of the wing mounting assembly 1 to be quickly centered to the fuselage mounting body ear hole 213 of the fuselage mounting assembly 2.

[0124] The visual guidance component 4 of the embodiment is installed on the fuselage mounting body of the fuselage mounting assembly 2.

[0125] As shown in Figure 6 and Figure 7 , the visual guidance component 4 includes a visual support assembly 41, a main visual unit 42 and an auxiliary visual unit 43, a visual power unit 44 and a visual signal transmission unit 45.

[0126] The visual signal transmission unit 45 includes a router 451 and an antenna 452.

[0127] As shown in Figure 7 and Figure 8 , the main visual unit 42 includes a main camera 421, a main camera positioning cylinder 422, a main light source unit 423 and an assembly body positioning unit 424 arranged coaxially.

[0128] As shown in Figure 7 and Figure 8As shown, the auxiliary vision unit 43 includes an auxiliary camera 431, an auxiliary camera protective housing 432, and an auxiliary camera light source 433.

[0129] The main camera 421, the auxiliary camera 431, and the vision signal transmission unit 45 substantially constitute a vision guiding sensor.

[0130] The vision guiding sensor can collect information of the installation positions of the wing mounting assembly 1 and the fuselage mounting assembly 2, and transmit the information to the industrial control center 7, which can calculate and generate comprehensive optimal path displacement information of each execution element, each execution element receives and executes the respective displacement information, and drives the wing mounting assembly 1 to move rapidly towards the fuselage mounting assembly 2, so that the installation positions of the two are aligned.

[0131] As shown in Figure 7 and Figure 8 As shown, the vision support assembly 41 includes a support frame 411, a guide rail 412, and a pushing unit 413; the guide rail unit 412 and the pushing unit 413 are connected to the support frame 411.

[0132] As shown in Figure 9 As shown, the support frame 411 includes a movable clamping plate and a fixed mounting plate, and the movable clamping plate is connected to the upper end of the fixed mounting plate. The movable clamping plate and the fixed mounting plate of the embodiment are integrally formed and arranged at 90°.

[0133] The movable clamping plate of the support frame 411 is provided with a pushing unit mounting position 4111, a guide rail mounting groove 4112, an auxiliary camera mounting portion 4113, and an auxiliary light source mounting position 4115. The lower end of the fixed mounting plate of the support frame 411 is provided with a main light source mounting portion 4114.

[0134] The main light source mounting portion 4114 is a through stepped hole, including a main light source positioning counterbore for positioning the assembly unit 424, and a main light source light passing hole in through hole structure, which penetrates the fixed mounting plate; the main light source positioning counterbore is used for positioning the assembly unit 424.

[0135] The inner side surface of the main light source mounting portion 4114 is provided with a protruding assembly ear positioning body 4116, and the assembly ear positioning body 4116 is provided with an assembly ear positioning surface 41161 towards the center of the main light source mounting portion 4114. The assembly ear positioning body 4116 can be integrally formed with the fixed mounting plate, or can be designed separately and then connected to the fixed mounting plate.

[0136] Preferably, the assembly ear positioning surface 41161 is a bevel surface perpendicular to the outer end surface of the main light source mounting portion 4114. The angle of the bevel surface is consistent with the bevel surface of the ear edge of the fuselage mounting body ear plate 212.

[0137] The pushing unit installation site 4111 is arranged at the second end of the movable clamping plate of the support frame 411, and the pushing unit 413 is connected at the pushing unit installation site 4111; the guide rail installation groove 4112 is arranged on the inner surface of the movable clamping plate, and the guide rail unit 412 is installed in the guide rail installation groove 4112; the guide rail unit 412 comprises a movable guide rail 4121 and a fixed guide rail 4122; the pushing unit 413 can directly / indirectly push the movable guide rail 4121 to move linearly on the fixed guide rail 4122. The auxiliary visual unit 43 is installed at the auxiliary camera installation part 4113.

[0138] As shown in Figure 7 and Figure 8 The visual guiding part 4 further comprises a mounting housing unit 46. One side end of the lower part of the mounting housing unit 46 is provided with a mounting housing light hole; at the mounting housing light hole of the mounting housing unit 46, an internal connection main camera 421 and an external connection main camera positioning cylinder 422 are connected; the visual power unit 44 is integrally arranged in the mounting housing unit 46; an antenna 452 is mounted on the mounting housing unit 46, and a router 451 is mounted on the upper part of the movable clamping plate.

[0139] The mounting housing unit 46 is movably connected to the movable guide rail 4121 of the visual support assembly 41.

[0140] The auxiliary camera 431 is connected to the auxiliary camera installation part 4113, and an auxiliary camera protection housing 432 is arranged on the upper part of the auxiliary camera 431 and is fixedly connected to the upper part of the movable clamping plate. An auxiliary camera light source 433 is connected to the auxiliary light source installation site 4115.

[0141] Preferably, the auxiliary camera light source 433 is adjustably connected to the movable clamping plate of the support frame 411. Further preferably, the auxiliary camera light source 433 is connected to the auxiliary light source installation site 4115 through a universal joint with a fastening function, so that the auxiliary camera light source 433 can provide light to the auxiliary camera 431 in a preferred direction and can be fixed in the preferred direction position.

[0142] On the inner side of the lower end of the fixed mounting plate of the support frame 411, an assembly positioning unit 424 is connected at the main light source installation part 4114; on the outer side of the lower end of the fixed mounting plate of the support frame 411, a main light source unit 423 is connected at the opposite side of the main light source installation part 4114.

[0143] The main light source unit 423 comprises a main light source housing 4231, a main light source illuminator 4232, and a main light source switch 4233. The main light source illuminator 4232 is connected to the main light source housing 4231 through a main light source fastener 4234, and the main light source housing 4231 is connected to the outer side of the lower end of the fixed mounting plate of the support frame 411.

[0144] The structure of the assembly positioning unit 424 is matched with the main light source mounting portion 4114. The assembly positioning unit 424 is a stepped shaft structure, including a positioning body mounting portion 4241 and a positioning body centering portion 4242 arranged coaxially, and further including a positioning body main light source light passing hole 4243 penetrating through the whole stepped shaft structure.

[0145] As shown in Figure 6 and Figure 8 , optionally, the positioning body centering portion 4242 is connected to the positioning body mounting portion 4241, and a positioning body pressure sensor 4244 is further arranged on the positioning body mounting portion 4241, for sensing the pressure of the main camera positioning cylinder 422 driven by the pushing unit 413 pressing the body mounting assembly ear plate 212.

[0146] The control center 7 stores a rated positioning body pressure value, and the pressure data collected by the positioning body pressure sensor 4244 is transmitted to the control center 7, for judging whether the visual guiding component 4 and the body mounting assembly 2 are connected in place or not. When the pressure data transmitted by the positioning body pressure sensor 4244 reaches the rated positioning body pressure value, the control center 7 generates control information for stopping operation and transmits the control information to the pushing unit 413.

[0147] Preferably, the pushing unit 413 is an electric push rod controlled by a relay, and the connection or disconnection of the relay is controlled by the control information generated by the control center 7. The output end of the pushing unit 413 is connected to the mounting shell unit 46 / active guide rail 4121; the pushing unit 413 receives the displacement information generated by the control center 7 to perform extension and retraction movement, drives the mounting shell unit 46 connected to the mounting shell unit 46 / active guide rail 4121 to generate linear displacement, and makes the main camera positioning cylinder 422 approach or move away from the body mounting assembly ear plate 212.

[0148] The positioning body centering portion 4242 is a boss structure for positioning the center of the body mounting assembly ear hole 213 of the body mounting assembly 2; the assembly ear positioning body 4116 is a boss structure matched with the assembly ear positioning surface 41161, which can limit the body mounting assembly 2 from rotating radially and limit the radial position of the body mounting assembly 2. The relative position of the body mounting assembly 2 and the visual guiding component 4 is fully limited.

[0149] As shown in Figure 4 , Figure 8 and Figure 9 , the lower end of the fixed connection plate of the support frame 411 is provided with a main light source mounting portion 4114. The inner side of the main light source mounting portion 4114 is provided with an assembly positioning unit 424 for positioning the body mounting assembly 42; and the outer side of the main light source mounting portion 4114 is provided with a main light source unit 423 for providing light for the main camera 421.

[0150] AsFigure 9 As shown, the main light source mounting portion 4114 includes a main light source positioning sink, an assembly positioning unit mounting site, and a main light source through hole.

[0151] The positioning body mounting portion 4241 is arranged in the main light source positioning sink, and the positioning body mounting portion 4241 is circumferentially provided with a positioning body mounting through hole; the positioning body mounting portion 4241 fixes the assembly positioning unit 24 in the main light source positioning sink 1141 by passing through the positioning body mounting through hole with a fastener, and the bottom plane of the main light source positioning sink is provided with a screw hole matched with the positioning body mounting through hole.

[0152] The positioning body main light source light passing hole 4243 is coaxially arranged with the main light source through hole and the mounting shell light passing hole. The positioning body centering portion 4242 is used as a boss structure to limit the ear hole on the fuselage mounting body of the fuselage mounting assembly 2, so as to limit the radial position of the fuselage mounting assembly 2.

[0153] The auxiliary visual unit 43 collects the position image of the edge of the appearance position relationship between the wing mounting body 11 and the fuselage mounting body or a corresponding set of identification codes, and provides data support for the rapid displacement of the wing mounting assembly 1 to the fuselage mounting assembly 2; the main visual unit 42 collects the hole position deviation image of the wing mounting body ear hole 113 relative to the fuselage mounting body ear hole 213, and provides data support for the displacement of the fine adjustment of the installation position alignment of the wing mounting assembly 1 and the fuselage mounting assembly 2.

[0154] The real-time image data of the appearance position relationship collected by the auxiliary visual unit 43 and the real-time image data of the circumferential position deviation collected by the main visual unit 42 can be stored in the router 451, and the real-time image data is transmitted to the industrial control center 7 through the antenna 452.

[0155] The visual power unit 44 is integrated and connected in the mounting shell unit 46, including a battery unit, a booster module, a step-down module, a power switch and a power charging interface. The power charging interface charges the battery unit, the power of the battery unit is supplied to the main visual unit 42 and the auxiliary visual unit 43 through the booster module, and the power of the battery unit is supplied to the router 451 through the step-down module.

[0156] The integrated configuration of the power supply, the booster and the step-down module can significantly reduce the number of batteries and the space occupation requirement of high-voltage batteries, meet the needs of various components for different voltages in a small space range, and save space.

[0157] The industrial control center 7 includes a database; the database stores various theoretical / rated values, and the data of the database can be edited according to the actual working condition; the industrial control center 7 further includes a data processor and a position solver, and the position solver stores a theoretical criterion, which is used to generate execution information by judging the collected data.

[0158] Specifically, the data processor of the industrial control center 7 has the functions of image and data processing.

[0159] The data processor can remotely receive real-time image data / pressure data in wired or wireless mode, and perform data preprocessing to form relative position relationship data / pressure comparison data, and perform format conversion.

[0160] The position solver receives the processed data after format conversion, generates numerical criterion results by comparing with the theoretical / rated data in the database, and calculates the execution information of starting / closing / displacement amount; the position solver transmits the execution information of starting / closing / displacement amount to the execution elements in the aircraft wing-body assembly auxiliary system of the embodiment, such as the carrying unit 81 / support frame adjustment unit 82 / vertical positioning body 521 / lateral positioning body 522 / longitudinal positioning body 523 / pushing unit 413, so that the wing mounting assembly 1 further approaches the fuselage mounting assembly 2 in the correct path until the wing mounting body ear hole 113 and the fuselage mounting body ear hole 213 are aligned; then the industrial control center 7 can generate the execution information of the relevant displacement execution elements in the aircraft wing-body assembly auxiliary system to withdraw from the mounting position (including the pushing unit 413 moving away from the auxiliary vision unit 43), so as to perform the assembly work of fastening the wing mounting assembly 1 to the fuselage mounting assembly 2.

[0161] The aircraft wing-body assembly auxiliary system of the present application has compact structure, convenient use, high reusability, can integrate multiple aircraft wing-body assembly auxiliary systems in one control platform for use, and is particularly suitable for rapid and accurate assembly of large aircraft fuselages and wings. It can also be applied to the assembly process of other large toolings, has wide application range, and is particularly suitable for the assembly process of large parts hole systems prone to deformation.

[0162] The above is only the preferred specific embodiment of the present application, but the protection scope of the present application is not limited thereto, and any person skilled in the art can easily think of changes or replacements within the technical scope disclosed by the present application, which should be covered within the protection scope of the present application.

Claims

1. An aircraft wing-to-fuselage assembly aid system, characterized by, The application relates to a wing installation assembly (1) for being assembled to a fuselage installation assembly (2); the wing installation assembly (1) comprises a bracket supporting component, a visual guiding component (4), an industrial control center (7) and a carrying assembly (8); The visual guiding component (4) is installed on the fuselage installation assembly (2); The bracket supporting component comprises a flexible supporting assembly (3) and a bracket assembly (6); two ends of the bracket assembly (6) are respectively connected with one flexible supporting assembly (3); the bracket assembly (6) is a truss structure; the bracket assembly (6) comprises a bracket side support plate (61), a bracket cross beam (62), a bracket installation unit (63) and a bracket connecting unit (64); the flexible supporting assembly (3) is connected to the bracket connecting unit (64); The flexible supporting assembly (3) comprises an upper supporting part (31), a lower supporting part (32), a supporting locking unit (33), a flexible supporting installation part (34) and a flexible supporting sensing unit; The supporting locking unit (33) is hinged to the upper supporting part (31) and locked to the lower supporting part (32); the wing installation assembly (1) is clamped between the upper supporting part (31) and the lower supporting part (32); The flexible supporting sensing unit comprises a flexible supporting position sensor and a flexible supporting pressure sensor; the flexible supporting position sensor is arranged on the upper supporting part (31); the flexible supporting pressure sensor is arranged on the supporting locking unit (33); The wing installation assembly (1) is clamped on the flexible supporting assembly (3); the carrying assembly (8) comprises a carrying unit (81) and a support frame adjusting unit (82); The lower end of the support frame adjusting unit (82) is connected with the carrying unit (81), and the upper end of the support frame adjusting unit (82) is connected with the lower end of the bracket assembly (6); The industrial control center (7) can receive signals transmitted by the visual guiding component (4) and the bracket supporting component, and control displacement adjustment of the carrying assembly (8) and the bracket supporting component.

2. The aircraft wing-to-fuselage assembly aid system of Claim 1, wherein, The visual guiding component (4) comprises a visual support assembly (41), a main visual unit (42) and an auxiliary visual unit (43), a visual power unit (44) and a visual signal transmission unit (45).

3. The aircraft wing-to-fuselage assembly aid system of Claim 2, wherein, The main visual unit (42) comprises a main camera (421), and the auxiliary visual unit (43) comprises an auxiliary camera (431).

4. The aircraft wing-to-fuselage assembly aid system of Claim 1, wherein, The industrial control center (7) comprises a data processor and a position solver; the data processor can process image data collected by the visual guiding component (4) and position / pressure data collected by sensors; the position solver calculates results of the position / pressure data processor to generate control instruction information of starting / stopping / displacement of each execution element.

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