Six-degree-of-freedom attitude adjusting device for large component of airplane

Abstract

A six-degree-of-freedom attitude adjusting device for a large aircraft component comprises a sliding block, a fixed guide rail, a horizontal spiral positioner, a double-lug supporting rod, a positioning and locking assembly, a movable adapter frame, a horizontal rack positioner, a supporting plate assembly, an aircraft body attitude adjusting framework platform and a movable guide rail, and a foundation framework guide rail guide mechanism is formed on a foundation framework through the fixed guide rail and the sliding block; a horizontal spiral positioner installed on a machine body posture adjusting framework platform is connected with a double-lug supporting rod, and the double-lug supporting rod is vertically and fixedly connected with a foundation framework. A positioning and locking assembly is mounted between the foundation framework and the fuselage posture adjusting framework platform; a double-guide-rail guide mechanism is formed on the machine body posture adjusting framework platform through a movable guide rail and a sliding block; a horizontal rack positioner is mounted on the machine body posture adjusting framework platform, and is fixedly connected with a movable transfer frame; six-degree-of-freedom posture adjustment is achieved through adjustment of the positioning locking assembly, the double-moving guide rail and horizontal rack positioners and the horizontal spiral positioners installed between the supporting plate assembly and the moving transfer frame.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft attitude adjustment devices, in particular to a six-degree-of-freedom attitude adjustment device for large aircraft components. Background Art

[0002] When aligning large components such as aircraft fuselages, traditional support frame positioning platforms are adjusted through special hoists and positioning devices. However, during the large component assembly operation process, each component installation is very difficult, the alignment quality is poor, and there are certain safety hazards in the operation process, which affects the quality of product delivery at the next station. Utility Model Content

[0003] The technical problem solved by the present invention is to provide a six-degree-of-freedom attitude adjustment device for large aircraft components, so as to solve the problems in the above-mentioned background technology.

[0004] The technical problem solved by the present invention is achieved by the following technical solutions:

[0005] A six-degree-of-freedom attitude adjustment device for large aircraft components comprises a slider (1), a fixed guide rail (2), a horizontal spiral positioner (3), a double-ear support rod (4), a positioning and locking assembly (5), a mobile adapter (6), a horizontal rack positioner (7), a support plate assembly (8), a fuselage attitude adjustment skeleton platform (9) and a mobile guide rail (10), wherein the upper end of the foundation skeleton is two horizontally parallel fixed guide rails (2), and each fixed guide rail (2) is respectively installed with four sliders (1) to form a foundation skeleton guide rail guiding mechanism; the fuselage attitude adjustment skeleton platform (9) is provided with a plurality of sliders (1) on each fixed guide rail. A horizontal spiral positioner (3) is installed, and the horizontal spiral positioner (3) includes a horizontal spiral base and a horizontal spiral screw, the horizontal spiral base is fixed on the fuselage posture adjustment frame platform (9), the horizontal spiral screw is connected to the double-ear support rod (4), and the double-ear support rod (4) is vertically fixed to the foundation frame; and a positioning locking assembly (5) is respectively installed at the front end and the rear end on both sides between the foundation frame and the fuselage posture adjustment frame platform (9), one end of the positioning locking assembly (5) is installed on the foundation frame, and the other end of the positioning locking assembly (5) is installed on the fuselage posture adjustment frame platform (9);

[0006] The upper end of the fuselage posture adjustment skeleton platform (9) is provided with two sets of horizontally parallel movable guide rails (10), and the movable adapter frame (6) is provided with four sliders, each slider being matched with a movable guide rail (10) to form a double-guide rail guiding mechanism; a horizontal rack positioner (7) is provided on the right side of the upper end of the fuselage posture adjustment skeleton platform (9), the base of the horizontal rack positioner (7) is fixed to the upper end of the fuselage posture adjustment skeleton platform (9), and the screw of the horizontal rack positioner (7) is fixedly connected to the movable adapter frame (6);

[0007] The pallet assembly (8) includes a front group pallet and a rear group pallet. A horizontal screw positioner (3) is installed between the mobile adapter (6) and the front group pallet and the rear group pallet, and the base of each horizontal screw positioner (3) is fixed on the mobile adapter (6). The front group pallet and the rear group pallet are respectively connected to the screw of the horizontal screw positioner (3). The horizontal screw positioners (3) of the front group pallet and the rear group pallet independently control the feed, and can realize Y (up and down direction) independent freedom posture adjustment; when the Y direction is adjusted to the working position, the horizontal screw positioner (3) is locked with a pin, providing a Z-axis rotation movement (Z axis) formed by rotation along the parallel X-axis axis, up and down movement (Y) along the Y direction, and inconsistent front and back up and down movement, three independent degrees of freedom posture adjustment, thereby forming a six-degree-of-freedom adjustment, which can realize the posture adjustment of the product after it is put on the shelf.

[0008] In the present utility model, the horizontal spiral positioner (3) installed on the fuselage posture adjustment skeleton platform (9) is arranged in parallel with the two fixed guide rails (2), ensuring smooth movement without interference.

[0009] In the utility model, the positioning and locking components (5) on the foundation frame and the fuselage attitude adjustment frame platform (9) are respectively provided with latch holes, and the fuselage attitude adjustment frame platform (9) and the foundation frame are locked by inserting latches into the latch holes.

[0010] In the utility model, a latch hole for inserting a latch is provided on the horizontal rack positioner (7), and the horizontal rack positioner (7) is locked by inserting the latch into the latch hole.

[0011] In the utility model, a transition frame is provided on the horizontal rack positioner (7).

[0012] In the present invention, the front support plate and the rear support plate are arc-shaped structures and are used to carry large aircraft components. Beneficial effects

[0013] 1) The utility model effectively solves the problems of difficult posture adjustment and low work efficiency during the alignment of large aircraft components, reduces safety hazards, improves assembly efficiency, and saves labor costs;

[0014] 2) The horizontal spiral positioner installed on the fuselage posture adjustment frame platform of the utility model is arranged in parallel with the two fixed guide rails, effectively ensuring smooth movement without interference and guiding accuracy;

[0015] 3) The positioning and locking devices in this utility model are arranged symmetrically front and back to ensure the stability of the fuselage posture adjustment skeleton platform;

[0016] 4) The utility model provides six degrees of freedom posture adjustment and can be used in parallel to achieve the assembly of multiple large components. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a front view of a preferred embodiment of the present utility model.

[0018] Figure 2 It is a left view of a preferred embodiment of the present utility model.

[0019] Figure 3 It is a top view of a preferred embodiment of the present invention.

[0020] Figure 4 for Figure 1 Enlarged view of point A in the middle.

[0021] Figure 5 This is an axonometric view of a preferred embodiment of the present invention. DETAILED DESCRIPTION

[0022] In order to make the technical means, creative features, objectives and effects achieved by the present invention easier to understand, the present invention is further described below with reference to specific illustrations.

[0023] See also Figures 1 to 5 A six-degree-of-freedom attitude adjustment device for a large aircraft component comprises a slider (1), a fixed guide rail (2), a horizontal spiral positioner (3), a double-ear support rod (4), a positioning and locking assembly (5), a mobile adapter (6), a horizontal rack positioner (7), a support plate assembly (8), and a fuselage attitude adjustment skeleton platform (9), wherein the upper end of the foundation skeleton is two horizontal parallel fixed fixed guide rails (2), and each fixed guide rail (2) is respectively installed with four sliders (1) to form a foundation skeleton guide rail guide mechanism; a horizontal spiral positioner (3) is installed on the fuselage attitude adjustment skeleton platform (9), and the horizontal spiral positioner (3) comprises a horizontal spiral base and a horizontal spiral screw, the horizontal spiral base is fixed on the fuselage attitude adjustment skeleton platform (9), and the horizontal spiral screw is connected to the double-ear support rod. Rod (4), the angle of the double-ear support rod (4) is adjustable, and when the fuselage attitude adjustment skeleton platform (9) is close to the theoretical position, the double-ear support rod (4) is vertically fixed to the foundation skeleton; when the fuselage attitude adjustment skeleton platform is moved to the working position by the horizontal spiral positioner (3), a positioning locking assembly (5) (four in total) is installed at the front and rear ends of both sides between the foundation skeleton and the fuselage attitude adjustment skeleton platform (9), one end of the positioning locking assembly (5) is installed on the foundation skeleton, and the other end of the positioning locking assembly (5) is installed on the fuselage attitude adjustment skeleton platform (9), and a pin is inserted into the positioning locking assembly (5) to lock the fuselage attitude adjustment skeleton platform (9) and the foundation skeleton, thereby realizing independent freedom attitude adjustment in the X direction (forward and backward direction), providing one independent freedom adjustment (X);

[0024] The upper end of the fuselage posture adjustment skeleton platform (9) is provided with two sets of horizontal parallel movable guide rails (10), and the movable adapter frame (6) is provided with four sliders, each slider cooperates with a movable guide rail (10) to form a double guide rail guiding mechanism; a horizontal rack positioner (7) is provided on the right side of the upper end of the fuselage posture adjustment skeleton platform (9), and the base of the horizontal rack positioner (7) is fixed to the upper end of the fuselage posture adjustment skeleton platform (9), and the screw of the horizontal rack positioner (7) is fixedly connected with the movable adapter frame (6) (forming two independent groups in the front and rear). By manipulating the transition frame of the double movable guide rails (10) and the horizontal rack positioner (7) on the fuselage posture adjustment skeleton platform (9), since the front and rear transition frames are independent and adjusted separately, the independent degree of freedom posture adjustment in the Z direction (left and right direction) can be realized. When the Z direction is adjusted to the working position, the horizontal rack positioner (7) is locked with a pin to form Z-direction movement (Z) and axial movement along the parallel Y axis (Y axis), forming two independent degrees of freedom adjustment;

[0025] The pallet assembly (8) includes a front pallet and a rear pallet. A horizontal spiral positioner (3) is installed between the mobile adapter (6) and the front pallet and the rear pallet respectively. The base of the horizontal spiral positioner (3) is fixed on the mobile adapter (6). The screw of the horizontal spiral positioner (3) is fixed to the front pallet and the rear pallet (the front and rear groups are independent of each other). The horizontal spiral positioners (3) of the front pallet and the rear pallet are independently controlled to feed, and can realize Y (up and down direction) independent freedom posture adjustment; when the Y direction is adjusted to the working position, the horizontal spiral positioner (3) is locked with a pin, providing rotation along the parallel X-axis axis, up and down movement (Y) along the Y direction and Z-axis rotation movement (Z axis) formed by inconsistent up and down movement, three independent degrees of freedom posture adjustment, thereby forming six degrees of freedom adjustment, which can realize the posture adjustment of the product after it is put on the shelf.

[0026] In this embodiment, the horizontal spiral positioner (3) installed on the fuselage posture adjustment skeleton platform (9) is arranged in parallel with the two fixed guide rails (2) to ensure smooth movement without interference.

[0027] In this embodiment, the positioning and locking components (5) on the foundation frame and the fuselage attitude adjustment frame platform (9) are respectively provided with latch holes, and the fuselage attitude adjustment frame platform (9) and the foundation frame are locked by inserting latches into the latch holes.

[0028] In this embodiment, a latch hole for inserting a latch is provided on the horizontal rack positioner (7), and the horizontal rack positioner (7) is locked by inserting the latch into the latch hole.

[0029] In this embodiment, the front support plate and the rear support plate are arc-shaped structures for carrying large aircraft components.

[0030] The above shows and describes the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Various changes and improvements may be made to the present invention without departing from the spirit and scope of the present invention. Such changes and improvements are intended to fall within the scope of the present invention. The scope of protection claimed in this invention is defined by the appended claims and their equivalents.

Claims

1. A six-degree-of-freedom attitude adjustment device for a large aircraft component, comprising a slider (1), a fixed guide rail (2), a horizontal spiral positioner (3), a double-ear support rod (4), a positioning and locking assembly (5), a mobile adapter frame (6), a horizontal rack positioner (7), a support plate assembly (8), a fuselage attitude adjustment skeleton platform (9) and a mobile guide rail (10), characterized in that: The upper end of the foundation frame is provided with two horizontally parallel fixed guide rails (2), and each fixed guide rail (2) is respectively provided with four sliders (1) to form a foundation frame guide rail guiding mechanism; a horizontal spiral positioner (3) is provided on the fuselage attitude adjustment frame platform (9), and the horizontal spiral positioner (3) includes a horizontal spiral base and a horizontal spiral screw, and the horizontal spiral base is fixed on the fuselage attitude adjustment frame platform (9), and the horizontal spiral screw is connected to the double-ear support rod (4), and the double-ear support rod (4) is vertically fixed to the foundation frame; and a positioning locking assembly (5) is respectively provided at the front end and the rear end on both sides between the foundation frame and the fuselage attitude adjustment frame platform (9), and one end of the positioning locking assembly (5) is provided on the foundation frame, and the other end of the positioning locking assembly (5) is provided on the fuselage attitude adjustment frame platform (9); The upper end of the fuselage posture adjustment skeleton platform (9) is provided with two sets of horizontally parallel movable guide rails (10), and the movable adapter frame (6) is provided with four sliders, each slider being matched with a movable guide rail (10) to form a double-guide rail guiding mechanism; a horizontal rack positioner (7) is provided on the right side of the upper end of the fuselage posture adjustment skeleton platform (9), the base of the horizontal rack positioner (7) is fixed to the upper end of the fuselage posture adjustment skeleton platform (9), and the screw of the horizontal rack positioner (7) is fixedly connected to the movable adapter frame (6); The pallet assembly (8) includes a front pallet group and a rear pallet group, and horizontal screw positioners (3) are respectively installed between the mobile adapter frame (6) and the front pallet group and the rear pallet group, and the base of each horizontal screw positioner (3) is respectively fixed on the mobile adapter frame (6), and the front pallet group and the rear pallet group are respectively fixed to the screw of the horizontal screw positioner (3).

2. The six-degree-of-freedom attitude adjustment device for large aircraft components according to claim 1, characterized in that: The horizontal spiral positioner (3) installed on the fuselage posture adjustment skeleton platform (9) is arranged in parallel with the two fixed guide rails (2).

3. The six-degree-of-freedom attitude adjustment device for large aircraft components according to claim 1, characterized in that: Pin holes for inserting pins are respectively provided in the positioning locking components (5) on the foundation frame and the fuselage attitude adjustment frame platform (9).

4. The six-degree-of-freedom attitude adjustment device for large aircraft components according to claim 1, characterized in that: The horizontal rack positioner (7) is provided with a latch hole for inserting a latch.

5. The six-degree-of-freedom attitude adjustment device for large aircraft components according to claim 1, characterized in that: A transition frame is provided on the horizontal rack positioner (7).

6. The six-degree-of-freedom attitude adjustment device for large aircraft components according to claim 1, characterized in that: The front supporting plate and the rear supporting plate are arc-shaped structures.

Images