CN101829900B - Layout method of grand cross butting locator of aircraft wing body - Google Patents

Abstract

The invention discloses a layout method for a large cross docking locator of an aircraft wing body. The method is: the fuselage and wings of the aircraft adopt a large cross docking method; the overall fuselage adopts 4 fuselage main locators and 3 fuselage auxiliary locators, including 2 rear fuselage auxiliary locators and 1 front fuselage locator. Fuselage auxiliary locator, the fuselage locator and the fuselage are connected by ball joints; the whole wing adopts 4 wing main locators and 2 wing auxiliary locators, the connection between the wing main locator and the wing The ball hinge connection method is adopted between the wings, and the vacuum suction cup connection method is used between the wing auxiliary positioner and the wing. The present invention adopts the large cross butt joint method, the central wing and the outer wing butt joint operation space are large, it is easy to realize digital and mechanized hole making, and the processing efficiency and quality are guaranteed.

Description

Layout Method of Aircraft Wing Body Big Cross Docking Locator

technical field

The invention relates to a layout method of a large cross docking locator of an aircraft wing body.

Background technique

In the field of aircraft manufacturing, the aircraft manufacturing process always first assembles parts into components, assembles components into small parts, assembles small parts into aircraft fuselage and wings, and finally assembles the aircraft fuselage and wings. Aircraft assembly technology is one of the weak links in China's aircraft manufacturing industry. In order to improve the efficiency and quality of aircraft fuselage and wing docking assembly, it is necessary to change the current traditional aircraft general assembly mode based on analog quantities, and then propose an aircraft The layout design of the wing-body large cross docking locator can realize digital precise attitude adjustment and alignment, laser tracking measurement, and fully consider the space accessibility of manual operation and the aircraft fuselage during the docking assembly process of the aircraft wing and fuselage. , Wing and overall machine passability.

Contents of the invention

The purpose of the present invention is to provide a method for layout of aircraft wing body large cross docking locator.

The layout method of the large cross docking locator of the wing body of the aircraft is: the fuselage and wings of the aircraft adopt the large cross docking method; the overall fuselage adopts 4 fuselage main locators and 3 fuselage auxiliary locators, including 2 rear The fuselage auxiliary locator and 1 front fuselage auxiliary locator, the fuselage locator and the fuselage are connected by ball joints; the overall wing adopts 4 wing main locators and 2 wing auxiliary locators, The main positioner of the wing and the wing are connected by a ball joint, and the auxiliary positioner of the wing and the wing are connected by a vacuum suction cup.

In the layout method of the aircraft wing-body large cross docking locator, a manual mobile trolley is provided at the bottom of the auxiliary locator of the front fuselage. In the layout method of the aircraft wing body large cross docking locator, the locator can move along three coordinate directions.

The advantages of the present invention: 1) adopting the large cross docking method, the central wing and the outer wing have a large space for docking operation, easy to realize digital and mechanized hole making, and ensure processing efficiency and quality; 2) adopting the large cross docking method, the central wing and the middle and outer wings First docking assembly is not only conducive to sealing construction, but also facilitates sealing inspection to ensure the sealing requirements of the overall fuel tank; 3) Using the large cross docking method, the left and right outer wings and the central wing can be pre-connected simultaneously or successively, and then the symmetry Measurement, easy to ensure the symmetry of the entire wing; 4) The large cross docking method is adopted, and the overall wing is used as a part of the final assembly, which is convenient for production organization and management, with high production efficiency and guaranteed quality, which is in line with the general trend of modular manufacturing of aircraft in different places ;5) The layout of the main fuselage locator fully considers the attitude adjustment requirements of the fuselage and the passability of the aircraft; 6) The layout of the auxiliary fuselage locator fully considers the auxiliary holding of the fuselage and the docking requirements of the fuselage and wings ; 7) The layout of the wing main locator fully considers the attitude adjustment requirements of the wing and the passability of the aircraft; 8) The layout of the wing auxiliary locator fully considers the structural characteristics and auxiliary holding requirements of the wing.

Description of drawings

Fig. 1 Front view of fuselage locator layout;

Fig. 2 Top view of wing positioner layout;

Fig. 3 The front view of the layout of the wing positioner;

Fig. 4 top view of wing positioner layout;

Fig. 5 The front view of the layout of the large cross docking locator of the aircraft wing and fuselage;

Figure 6 is the top view of the layout of the large cross docking locator of the aircraft wing and fuselage;

In the figure: fuselage main locator 1, fuselage rear auxiliary locator 2, fuselage front auxiliary locator 3, wing main locator 4, wing auxiliary locator 5.

Detailed ways

As shown in accompanying drawings 1, 2, 3, 4, 5, 6, the layout method of the large cross docking locator of the aircraft wing body is characterized in that the fuselage and wings of the aircraft adopt a large cross docking method; the overall fuselage adopts 4 One fuselage main locator and three fuselage auxiliary locators, including 2 rear fuselage auxiliary locators and 1 front fuselage auxiliary locator, the fuselage locator and the fuselage are connected by a ball joint; The overall wing adopts 4 wing main positioners and 2 wing auxiliary positioners, the main wing positioner and the wing are connected by a ball joint, and the wing auxiliary positioner and the wing are connected by a vacuum suction cup Way.

In the layout method of the aircraft wing-body large cross docking locator, a manual mobile trolley is provided at the bottom of the auxiliary locator of the front fuselage. In the layout method of the aircraft wing body large cross docking locator, the locator can move along three coordinate directions.

The positioner is the final actuator of the attitude adjustment and docking system, including the mechanical body of the positioner and the electric drive control, with two modes of automatic operation and manual operation. Positioners can be divided into fuselage main positioner 1, fuselage rear auxiliary positioner 2, fuselage front auxiliary positioner 3, wing main positioner 4, and wing auxiliary positioner 5 according to the support position and bearing.

Among them, the fuselage locator includes four main fuselage locators 1, which are used to adjust and support the attitude of the fuselage, complete the docking of the wing-body cross, and fully consider the convenience and safety requirements of the accurate positioning of the fuselage. The process joints on the upper body form a ball-joint connection, three-coordinate control, and self-adaptive positioning; 2 rear auxiliary positioners 2 of the fuselage are used to assist in supporting the entire fuselage, and do not participate in the adjustment of the fuselage attitude, so as to improve the docking of the wing body and the large cross process stability. It forms a ball-joint connection with the process joint on the fuselage, three-coordinate control, and self-adaptive positioning; one auxiliary positioner 3 in front of the fuselage is used to assist in supporting the aircraft fuselage, and does not participate in the attitude adjustment of the fuselage, and assists the fuselage The main positioner completes the large cross docking of the wing body to ensure the stability of the docking process. In order to meet the space requirements of aircraft movement and landing gear retraction test, the auxiliary positioner in front of the fuselage can be manually moved in and out, and can be quickly positioned and bolted to the taper hole on the ground pre-embedded steel plate. It forms a ball hinge connection with the process joint on the fuselage, three-coordinate control, and self-adaptive positioning.

The wing positioner includes four main wing positioners 4, which are used to adjust and support the attitude of the wing, and realize the docking between the wing and the fuselage through the coordinated movement between multiple positioners. Fully consider the convenience and safety requirements of wing placement, attitude adjustment and docking process. It forms a spherical hinge connection with the process joint on the wing, and is controlled by three coordinates; two wing auxiliary positioners 5 are used to assist in supporting the wing after the attitude of the wing is determined. The vacuum suction cup on the top of the positioner is in contact with the wing skin to improve the holding stability of the wing assembly.

Use the steps of the present invention as follows:

1. Fuselage in place and attitude adjustment

1) Positioner self-test, each positioner reset. The fuselage main locator 1 and fuselage front auxiliary locator 3 move along the Y direction to a designated non-interference position with the fuselage; 2) The whole fuselage is pulled into place by a trailer, and the fuselage main locator 1 moves along the Y direction 3) The four fuselage main CNC positioners 1 are put in place in sequence, and after reaching the specified load, they rise up synchronously to jack up the fuselage so that the landing gear leaves the ground; 4) Based on the measurement results of the laser tracker, the fuselage main CNC Positioner 1 cooperates to complete the attitude adjustment of the overall fuselage, perform attitude evaluation, and lock the process joint; 5) The auxiliary positioner 2 behind the fuselage is synchronously in place, assisting in supporting the fuselage and locking the process joint; 6) Manual After pushing the auxiliary positioner 3 in front of the fuselage to the designated position, guide it into place through the taper hole, and fix it with bolts to support the fuselage and lock the process joint.

2 Wing in place and attitude adjustment

1) The whole wing is hoisted above the fuselage, one wing main CNC positioner 4 is in place, and the ball head is locked; the other three wing main numerical control positioners 4 are in place sequentially, and the ball head is not locked; 2 ) The main numerical control positioner 4 of the wing releases the ball head, the main numerical control positioner 4 of the wing rises synchronously to jack up the whole wing, and the spreader is withdrawn; 3) Based on the measurement results of the laser tracker, the main numerical control positioner 4 of the wing Perform attitude adjustment and attitude evaluation on the wing, and lock the technical ball head; 4) The wing auxiliary support locator 5 rises to support the wing at a designated position, and the suction cup on the top of the locator is evacuated to assist in holding the wing.

3 Wing body docking process

1) The wing maintains the posture and descends, and the main joint of the fuselage and the main joint of the wing are mated through the handwheel operation; 2) The large cross connection of the wing and the fuselage is manually completed, and the quality of the large cross connection between the wing and the fuselage is completed. Evaluate and store the results in the database; 3) After the aircraft assembly is completed, lower the wing auxiliary locator 5 and the wing main numerical control locator 4; The auxiliary locator 2 and the main numerical control locator 1 of the fuselage make the landing gear of the aircraft touch the ground; 5) after the main locator 1 of the fuselage moves to a safe position along the Y direction, the aircraft is towed by a trailer and transferred to the station.

Claims (2)

1. an aircraft wing body grand cross butt joint locator layout method is characterized in that the integral body of aircraft and whole wing adopt the grand cross docking mode; Integral body adopts 4 fuselage master locators (1) and 3 fuselage auxiliary locators; Said 3 fuselage auxiliary locators comprise 2 rear body auxiliary locators (2) and 1 forebody auxiliary locator (3), adopt the ball pivot connected mode between fuselage locator and the fuselage; Whole wing adopts 4 wing master locators (4) and 2 wing auxiliary locators (5), adopts the ball pivot connected mode between wing master locator (4) and the wing, adopts the vacuum cup connected mode between wing auxiliary locator (5) and the wing.

2. a kind of aircraft wing body grand cross butt joint locator layout method according to claim 1 is characterized in that described forebody auxiliary locator (3) bottom is provided with artificial travelling car.

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