CN112676890B - Flexible positioning device for digitally manufacturing airplane skin parts - Google Patents
Flexible positioning device for digitally manufacturing airplane skin parts Download PDFInfo
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- CN112676890B CN112676890B CN202110284545.XA CN202110284545A CN112676890B CN 112676890 B CN112676890 B CN 112676890B CN 202110284545 A CN202110284545 A CN 202110284545A CN 112676890 B CN112676890 B CN 112676890B
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Abstract
The invention provides a digital manufacturing flexible positioning device for airplane skin parts, which comprises a main base, wherein a fixed tower and a movable tower are arranged on the main base, an airplane skin is clamped between the fixed tower and the movable tower, a first auxiliary base is arranged on one side of the main base, which is close to the inner arc surface of the airplane skin, and a second auxiliary base is arranged on the other side of the main base. When the first auxiliary base is provided with two inner shape positioning units, the second auxiliary base is provided with an outer shape positioning unit; when the manipulator is arranged on the first auxiliary base, the two appearance positioning units are arranged on the second auxiliary base. According to the invention, the aircraft skin is fixed on the main base, the two auxiliary bases are arranged on the two sides of the main base, and the appearance positioning unit, the inner shape positioning unit and the machining manipulator can be arranged on the auxiliary bases, so that the aircraft skin can be flexibly positioned by using the appearance positioning unit and the inner shape positioning unit in the machining process, and the machining of the aircraft skin is conveniently completed.
Description
Technical Field
The invention belongs to the technical field of aircraft skin processing, and particularly relates to a digital manufacturing flexible positioning device for aircraft skin parts.
Background
The aircraft skin is a dimensional component which is wrapped outside an aircraft framework structure and is fixed on the framework by using an adhesive or rivets to form the aerodynamic shape of the aircraft. The skin structure formed by the aircraft skin and the framework has large bearing capacity and rigidity, and light dead weight, and plays a role in bearing and transmitting aerodynamic load. The skin bears the aerodynamic action and transmits the acting force to the connected fuselage wing framework, the stress is complex, and in addition, the skin is directly contacted with the outside, so that the skin material is required to have high strength and good plasticity, the surface is required to be smooth, the corrosion resistance is higher, the early or low-speed small aircraft cloth (hemp or cotton) is used as the skin, and the skin can only bear part of limited aerodynamic load at the moment and does not participate in the integral stress. The common skin of the current airplane is a metal skin, a composite material laminated skin, a sandwich skin, an integral wallboard and the like.
The traditional aircraft skin manufacturing adopts full-size mould tire marking and manual processing in the part manufacturing stage. In the assembly stage, an assembly fixture is adopted, each component is assembled manually, the tool manufacturing period is long, the occupied area is large, the cost is high, the product adaptability is poor, one-to-one, namely, one part/component needs one tool, different machine type tools cannot be generally used, the aircraft development period is long, and the duration is generally about 15 years.
In recent years, a dot-matrix vacuum chuck flexible positioning system is adopted in aircraft component manufacturing, and some simple replaceable units are only added on the basis of an original rigid tool. Wherein multipoint mode vacuum chuck is comparatively popular, and product adaptability is effectively solved to this system, uses with the cooperation of numerical control processing equipment, improves part manufacturing accuracy.
However, the multi-point vacuum chuck system has high manufacturing cost and a complex adjustment process, and is difficult to popularize and use in the large-area aircraft skin processing process, thereby influencing the positioning operation in the aircraft skin processing process.
Disclosure of Invention
In order to overcome the problems in the related technology, the dot-matrix vacuum chuck flexible positioning system for manufacturing the aircraft parts is improved, the appearance positioning unit is matched with the appearance action unit to complete the processing of large-area aircraft skins, the part manufacturing and the wallboard assembling and positioning during the aircraft skin processing are integrated, the coordination link in the skin manufacturing process is reduced, a special tool for positioning the aircraft skins is reduced, the secondary positioning of the aircraft skins is omitted, the manufacturing and the assembling are integrated, the turnover frequency of the parts is reduced, the product adaptability is higher, the processing cost is reduced, and the efficiency is improved.
The main base is provided with a fixed tower and a movable tower, the fixed tower is fixed at one end of the main base, the main base is further provided with a slide rail, the movable tower is connected to the slide rail in a sliding mode, and an aircraft skin is clamped between the fixed tower and the movable tower.
A first auxiliary base is arranged on one side, close to the inner cambered surface of the aircraft skin, outside the main base, a second auxiliary base is arranged on the other side outside the main base, and sliding rails are also arranged on the first auxiliary base and the second auxiliary base respectively;
when the first auxiliary base is provided with two inner shape positioning units, the second auxiliary base is provided with one outer shape positioning unit.
When the first auxiliary base is provided with the manipulator, the second auxiliary base is provided with two appearance positioning units.
As a further explanation of the invention, connecting discs are respectively fixed on the adjacent sides of the fixed tower platform and the movable tower platform, the connecting discs are semicircular, and eight clamping units are uniformly arranged on the connecting discs close to the outer edge.
As a further explanation of the invention, the clamping unit comprises a conical block, an arc-shaped block and a clamping cylinder, the conical block and the arc-shaped block are respectively fixed on the side surface of the connecting disc, an aircraft skin clamping space is arranged between the conical block and the arc-shaped block, the clamping cylinder is arranged in the middle of the arc-shaped block, a telescopic shaft of the clamping cylinder penetrates through the arc-shaped block, and the aircraft skin is clamped and fixed in the clamping unit under the action of the clamping cylinder.
As a further explanation of the present invention, the inner shape positioning unit includes a first upright, a first connecting plate, a first positioning frame, a first positioning column, and a snap plate.
The first upright post is connected to a slide rail of the first auxiliary base in a sliding manner, two sides of the first upright post are respectively connected with a first slide block in a sliding manner, the first connecting plate is connected to the outer side of one of the first slide blocks in a sliding manner, a first positioning frame is fixed to the outer side of the first connecting plate, and a plurality of first positioning columns are sleeved on the outer side of the first positioning frame;
and the outer side of the other first sliding block is connected with a second connecting plate in a sliding manner, and the outer side of the second connecting plate is sleeved with a convex clamping plate.
As a further explanation of the present invention, the outer end of the first positioning column is provided with a vacuum chuck.
As a further explanation of the present invention, the first sliding block is vertically slidably connected to two sides of the first upright, and the first connecting plate and the second connecting plate are laterally slidably connected to an outer side of the first sliding block.
As a further explanation of the present invention, when the first auxiliary base is provided with two inner shape positioning units, a processing cylinder is further slidably connected between the two inner shape positioning units on the first auxiliary base.
As a further explanation of the invention, the shape positioning unit comprises a second upright post, a second sliding block, a second positioning frame, a second positioning column and a concave clamping plate.
The two sides of the second upright post are respectively and vertically connected with a second sliding block in a sliding manner, the outer side of one second sliding block is transversely connected with a second positioning frame in a sliding manner, and the outer side of the second positioning frame is respectively sleeved with a plurality of second positioning columns.
The outer side of the other second sliding block is transversely connected with a third connecting plate in a sliding mode, and the connecting end of the concave clamping plate is fixed to the side end of the third connecting plate.
As a further description of the present invention, the outer end portions of the outer sides of the second positioning pillars are also respectively provided with a vacuum chuck.
As a further explanation of the present invention, the base of the robot is fixed to the first auxiliary base by a bolt, and a machining head is fixed to the working end of the robot.
Compared with the prior art, the invention has the following beneficial technical effects:
according to the invention, the clamping units for clamping and fixing the aircraft skin are arranged on the two towers on the main base, the aircraft skin to be processed is fixed on the main base by the clamping units, the two sides of the main base are also provided with the two auxiliary bases, and the auxiliary bases can be provided with the appearance positioning unit, the inner shape positioning unit and the processing manipulator according to the processing mode, so that the aircraft skin can be flexibly positioned by matching the appearance positioning unit and the inner shape positioning unit according to the processing position and the processing mode in the processing process, and the processing of the aircraft skin in various modes is conveniently completed.
Drawings
FIG. 1 is a schematic view of an installation structure of an outer shape positioning unit and an inner shape positioning unit of a digital manufacturing flexible positioning device for airplane skin parts, which is provided by the invention;
FIG. 2 is a top view of the installation of the outer shape positioning unit and the inner shape positioning unit of the digital manufacturing flexible positioning device for the skin-type parts of the airplane provided by the invention;
FIG. 3 is a schematic view of an outline positioning unit and a manipulator mounting structure of a digital manufacturing flexible positioning device for airplane skin parts, provided by the invention;
fig. 4 is a top view of the appearance positioning unit and the manipulator mounting structure of the flexible positioning device for digitally manufacturing the skin-type parts of the airplane provided by the invention.
Description of the reference numerals
The machining device comprises a main base 1, a fixed tower 11, a movable tower 12, a connecting disc 13, a conical block 14, an arc block 15, a clamping cylinder 16, a first auxiliary base 2, a second auxiliary base 3, an aircraft skin 4, an inner positioning unit 5, a first upright column 51, a first connecting plate 53, a first positioning frame 54, a first positioning column 55, a second connecting plate 56, a convex clamping plate 57, a machining cylinder 6, a shape positioning unit 7, a second upright column 71, a second sliding block 72, a second positioning frame 73, a second positioning column 74, a third connecting plate 75, a concave clamping plate 76, a manipulator 8 and a machining head 81.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships that the products of the present invention are conventionally placed in use, and are only used for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical" and the like do not imply that the components are required to be absolutely horizontal or pendant, but rather may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The technical solution of the present invention will be explained with reference to specific embodiments.
Embodiment 1, as shown in fig. 1 and fig. 2, provides a digital manufacturing flexible positioning device for aircraft skin parts, including a main base 1, where the main base 1 is provided with a fixed tower 11 and a movable tower 12, where the fixed tower 11 is fixed at one end of the main base 1, the main base 1 is further provided with a slide rail, the movable tower 12 is slidably connected to the slide rail, and a locking mechanism is provided between the movable tower 12 and the slide rail for locking after the movable tower 12 completes position adjustment.
An aircraft skin 4 is sandwiched between the fixed tower 11 and the movable tower 12.
When the aircraft skin 4 is clamped, one end of the aircraft skin 4 is fixedly connected with the fixed tower 11 by hoisting, then the distance between the movable tower 12 and the fixed tower 11 is adjusted until the distance between the fixed tower 11 and the movable tower 12 is the same as the length of the aircraft skin 4, and the other end of the aircraft skin 4 is fixed on the movable tower 12, so that the connection between the aircraft skin 4 and the fixed tower 11 and the movable tower 12 can be completed, wherein the aircraft skin 4 is a raw material part of the aircraft skin 4 to be processed.
In order to facilitate clamping and fixing of the aircraft skin 4, connecting discs 13 are respectively fixed on the adjacent sides of the fixed tower platform 11 and the movable tower platform 12, the connecting discs 13 are semicircular, and eight clamping units are uniformly arranged on the positions, close to the outer edge, of the connecting discs 13.
The clamping unit comprises a conical block 14, an arc block 15 and a clamping cylinder 16, wherein the conical block 14 and the arc block 15 are respectively fixed on the side face of the connecting disc 13, an aircraft skin 4 clamping space is arranged between the conical block 14 and the arc block 15, and the eight clamping units mutually form a circular aircraft skin 4 clamping space.
The outer circular surfaces of the plurality of conical blocks 14 form the circular surfaces of the aircraft skin 4, so that the aircraft skin 4 can be clamped conveniently, and the conical blocks 14 can be replaced by different types of conical blocks 14 when the conical blocks are clamped facing the aircraft skins 4 with different circular surface types.
The clamping cylinder 16 is arranged in the middle of the arc-shaped block 15, the arc-shaped block 15 is penetrated through by a telescopic shaft of the clamping cylinder 16, clamping and fixing of the aircraft skin 4 in the clamping units are completed under the action of the clamping cylinder 16, namely when the aircraft skin 4 needs to be clamped and fixed, the end portion of the aircraft skin 4 is clamped into the plurality of clamping units of the fixed tower 11 respectively, then the clamping cylinder 16 is started, the clamping cylinder 16 is started to complete clamping and fixing of the end portion of the aircraft skin 4, the clamping and fixing principle of the movable tower 12 is the same as that of the fixed tower 11, and after the movable tower 12 and the fixed tower 11 fix the two ends of the aircraft skin 4 respectively, fixing of the aircraft skin 4 on the main base 1 is completed.
One side of the main base 1, which is close to the inner arc surface of the aircraft skin 4, is provided with a first auxiliary base 2, the other side of the main base 1 is provided with a second auxiliary base 3, the first auxiliary base 2 and the second auxiliary base 3 are respectively provided with a slide rail, and the first auxiliary base 2 and the second auxiliary base 3 are respectively provided with a cylinder power mechanism.
When two inner shape positioning units 5 are arranged on the first auxiliary base 2, one outer shape positioning unit 7 is arranged on the second auxiliary base 3.
The inner positioning unit 5 comprises a first upright post 51, a first connecting plate 53, a first positioning frame 54, a first positioning post 55 and a convex clamping plate 57; the first upright 51 is slidably connected to the slide rail of the first auxiliary base 2, and a locking mechanism is also arranged between the first upright 51 and the slide rail of the first auxiliary base 2, and is used for completing the position locking of the first upright 51 on the slide rail.
The two sides of the first upright post 51 are respectively connected with a first sliding block 52 in a sliding manner, and the first sliding block 52 is vertically connected with the two sides of the first upright post 51 in a sliding manner, namely the height of the first sliding block 52 on the first upright post 51 can be flexibly adjusted.
The first connecting plate 53 is transversely connected to the outer side of the first sliding block 52 in a sliding manner, a first positioning frame 54 is fixed to the outer side of the first connecting plate 53, a plurality of first positioning columns 55 are sleeved on the outer side of the first positioning frame 54, an adjusting cylinder is respectively arranged at the inner side end of each positioning column 55 in the first positioning frame 54, under the action of the adjusting cylinders, the extending lengths of the first positioning columns 55 at the outer side ends of the first positioning frames 54 are different, so that the first positioning columns 55 at different positions are mutually matched to form an outer circular surface, vacuum suction cups are arranged at the end parts of the outer side ends of the first positioning columns 55, when the plurality of first positioning columns 55 are adjusted to be the circular surface of the aircraft skin 4, the vacuum suction cups are used for fixedly adsorbing the first positioning columns and the inner arc surface of the aircraft skin 4, and then the connection between the inner shape positioning unit 5 and the aircraft skin 4 can be;
the outer side of the other first sliding block 52 is connected with a second connecting plate 56 in a sliding mode, the second connecting plate 56 is connected to the outer side of the first sliding block 52 in a transverse sliding mode, a convex clamping plate 57 is sleeved on the outer side of the second connecting plate 56, an adjusting cylinder used for adjusting the extending length of the convex clamping plate 57 is also arranged on the inner side of the second connecting plate 56, the outer side of the convex clamping plate 57 is an outer circular surface, the diameter of the outer circular surface is the same as that of the circular surface of the aircraft skin 4, and therefore supporting force in the machining process of the aircraft skin 4 is provided conveniently.
In the positioning and processing process of the aircraft skin 4, the convex clamping plate 57 is adjusted to abut against the inner circular surface of the aircraft skin 4 to complete the support of the aircraft skin 4, and then the vacuum chuck of the first positioning column 55 is used for adsorbing and fixing the inner circular surface of the aircraft skin 4, so that the stability in the processing process of the aircraft skin 4 is improved.
The shape positioning unit 7 includes a second upright column 71, second sliders 72, second positioning frames 73, second positioning columns 74 and concave clamping plates 76, the two sides of the second upright column 71 are vertically and slidably connected with the second sliders 72 respectively, the outer side of one of the second sliders 72 is transversely and slidably connected with the second positioning frame 73, the outer side of the second positioning frame 73 is also sleeved with a plurality of second positioning columns 74 respectively, and the connection mode of the second positioning columns 74 and the second positioning frames 73 is the same as the connection mode of the first positioning columns 55 on the first positioning frames 54.
In the using process, the extending length of the second positioning column 74 is adjusted to be the same as the gradually-changed outer circular surface of the aircraft skin 4, the end parts of the outer sides of the second positioning column 74 are also respectively provided with a vacuum chuck, the vacuum chucks on the outer sides of the second positioning column 74 are used for adsorption connection, the outer side of the second slider 72 is transversely connected with a third connecting plate 75 in a sliding manner, the connecting end of the concave clamping plate 76 is fixed at the side end of the third connecting plate 75, and the outer side of the concave clamping plate 76 is an inwards-concave circular surface which is the same as the gradually-changed outer circular surface of the aircraft skin 4;
therefore, in the process of machining the aircraft skin 4 in a small-range circular surface gradual change mode through the second positioning columns 74 and the concave clamping plates 76, the auxiliary supporting function is improved, the aircraft skin 4 is prevented from being damaged when the gradual change circular surface is machined, a transition function is formed, and the machining efficiency of the aircraft skin 4 is improved.
Specifically in the use process, the appearance positioning unit 7 on the second auxiliary base 3 is moved to a gradual change area in the machining process of the aircraft skin 4 through a sliding rail, then the second positioning column 74 is adjusted to enable the circular surfaces formed by the outer side ends of the second positioning columns 74 to be the same as the outer circular surface of the aircraft skin 4, the concave clamping plate 76 is abutted to the outer side of the aircraft skin 4, then the vacuum suction cups on the outer sides of the second positioning columns 74 are utilized to adsorb and fix the aircraft skin 4, the support of the aircraft skin 4 in the gradual change area is completed, and the positioning machining of the aircraft skin 4 is facilitated.
In order to facilitate the processing on the inner circular surface of the aircraft skin 4, a processing cylinder 6 is further connected between the two inner shape positioning units 5 on the first auxiliary base 2 in a sliding mode, the processing cylinder 6 is matched with the processing mode of the aircraft skin 4, and a processing tool is flexibly installed at the end of the processing cylinder.
When in use, the aircraft skin 4 is fixed between the fixed tower 11 and the movable tower 12 by using the fixed tower 11 and the movable tower 12, and the distance between the movable tower 12 and the fixed tower 11 is adjusted at the theoretical length position of the aircraft skin 4; and then, pre-adjusting the shape positioning unit 7 to a theoretical position, abutting the concave clamping plate 76 against the outer circular surface of the aircraft skin 4 by using the shape positioning unit 7, and adsorbing and fixing the outer circular surface of the aircraft skin 4 by using the vacuum chuck of the second positioning column 74, so that clamping and adsorption of the outer circular surface of the processing area of the aircraft skin 4 can be completed.
And adjusting the station of the manipulator 8, adjusting the manipulator 8 to the first processing station, completing measurement, positioning and fixation of the processing area of the aircraft skin 4 by matching the manipulator 8 with the processing head, and performing processing operation of hole making, hole opening or contour milling on the outer circular surface of the aircraft skin 4 by using the processing head.
Adopt this mode location, can realize automatic system hole, need not preassemble the type frame, can accomplish aircraft skin 4's processing mode and include: positioning a skin and processing a drilled positioning hole; deburring and cleaning the skin connecting part; cleaning a stringer, a frame with a positioning hole, and coating a sealant according to needs; positioning parts on the skin, processing temporary connection and the like.
By adopting the positioning device for the aircraft skin 4 in the embodiment, the manufacturing of the pre-assembled frame in the machining process of the aircraft skin 4 is omitted, the product turnover times are reduced, the production area is reduced, the positioning and machining cost of the aircraft skin 4 is saved, the machining efficiency of the aircraft skin 4 is improved, and the positioning device is economical and practical.
The embodiments given above are preferable examples for implementing the present invention, and the present invention is not limited to the above-described embodiments. Any non-essential addition and replacement made by the technical characteristics of the technical scheme of the invention by a person skilled in the art belong to the protection scope of the invention.
Claims (9)
1. The digital manufacturing flexible positioning device for the airplane skin parts is characterized by comprising a main base (1), wherein a fixed tower (11) and a movable tower (12) are arranged on the main base (1), the fixed tower (11) is fixed at one end of the main base (1), a sliding rail is further arranged on the main base (1), the movable tower (12) is connected onto the sliding rail in a sliding manner, and an airplane skin (4) is clamped between the fixed tower (11) and the movable tower (12);
a first auxiliary base (2) is arranged on one side, close to the inner arc surface of the aircraft skin (4), outside the main base (1), a second auxiliary base (3) is arranged on the other side outside the main base (1), and sliding rails are respectively arranged on the first auxiliary base (2) and the second auxiliary base (3);
when the first auxiliary base (2) is provided with two inner shape positioning units (5), the second auxiliary base (3) is provided with an outer shape positioning unit (7);
the inner shape positioning unit (5) comprises a first upright post (51), a first connecting plate (53), a first positioning frame (54), a first positioning post (55) and a convex clamping plate (57);
the first upright post (51) is connected to a sliding rail of the first auxiliary base (2) in a sliding manner, two sides of the first upright post (51) are respectively connected with a first sliding block (52) in a sliding manner, the first connecting plate (53) is connected to the outer side of one first sliding block (52) in a sliding manner, a first positioning frame (54) is fixed to the outer side of the first connecting plate (53), and a plurality of first positioning columns (55) are sleeved on the outer side of the first positioning frame (54);
the outer side of the other first sliding block (52) is connected with a second connecting plate (56) in a sliding mode, and a convex clamping plate (57) is sleeved on the outer side of the second connecting plate (56);
when the first auxiliary base (2) is provided with the manipulator (8), the second auxiliary base (3) is provided with two appearance positioning units (7).
2. The digital manufacturing flexible positioning device for airplane skin parts according to claim 1, characterized in that connecting discs (13) are respectively and fixedly arranged on the adjacent sides of the fixed turret table (11) and the movable turret table (12), the connecting discs (13) are semicircular, and eight clamping units are uniformly arranged on the connecting discs (13) near the outer edge.
3. The digital manufacturing flexible positioning device for the aircraft skin parts is characterized in that the clamping unit comprises a conical block (14), an arc-shaped block (15) and a clamping cylinder (16), the conical block (14) and the arc-shaped block (15) are respectively fixed on the side surface of the connecting disc (13), an aircraft skin (4) clamping space is arranged between the conical block (14) and the arc-shaped block (15), the clamping cylinder (16) is arranged in the middle of the arc-shaped block (15), a telescopic shaft of the clamping cylinder (16) penetrates through the arc-shaped block (15), and the aircraft skin (4) is clamped and fixed in the clamping unit under the action of the clamping cylinder (16).
4. Digital manufacturing flexible positioning device for aircraft skin-like parts according to claim 1, characterized in that the outer ends of the first positioning posts (55) are provided with vacuum suction cups.
5. Digital manufacturing flexible positioning device for airplane skin parts according to claim 1, characterized in that the first slider (52) is vertically slidably connected on both sides of the first upright (51), and the first connecting plate (53) and the second connecting plate (56) are laterally slidably connected on the outer side of the first slider (52).
6. The digital manufacturing flexible positioning device for airplane skin parts according to claim 1, characterized in that when two inner-shaped positioning units (5) are arranged on the first auxiliary base (2), a processing cylinder (6) is connected between the two inner-shaped positioning units (5) on the first auxiliary base (2) in a sliding manner.
7. The digital manufacturing flexible positioning device of airplane skin parts according to claim 1, characterized in that the shape positioning unit (7) comprises a second upright column (71), a second sliding block (72), a second positioning frame (73), a second positioning column (74) and a concave clamping plate (76);
two sides of the second upright post (71) are respectively connected with second sliding blocks (72) in a vertical sliding manner, the outer side of one second sliding block (72) is transversely connected with a second positioning frame (73) in a sliding manner, and the outer side of the second positioning frame (73) is respectively sleeved with a plurality of second positioning columns (74);
the outer side of the other second sliding block (72) is transversely connected with a third connecting plate (75) in a sliding mode, and the connecting end of the concave clamping plate (76) is fixed to the side end of the third connecting plate (75).
8. The digital manufacturing flexible positioning device for airplane skin parts according to claim 7, characterized in that the outer side ends of the outer sides of the second positioning columns (74) are respectively provided with a vacuum chuck.
9. Digital manufacturing flexible positioning device for airplane skin parts according to claim 1, characterized in that the base of the manipulator (8) is fixed on the first auxiliary base (2) by bolts and a processing head (81) is fixed at the working end of the manipulator (8).
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| US5833795A (en) * | 1996-09-19 | 1998-11-10 | Mcdonnell Douglas Corporation | Magnetic particle integrated adhesive and associated method of repairing a composite material product |
| CN102554660B (en) * | 2012-01-17 | 2014-04-09 | 清华大学 | Flexible processing system for aircraft skin |
| CN104400086B (en) * | 2014-10-10 | 2016-07-06 | 南京航空航天大学 | Aircraft skin mirror image method for milling and equipment |
| CN110216235B (en) * | 2019-06-03 | 2024-02-09 | 西安飞机工业（集团）有限责任公司 | Flexible fuselage wall plate assembly tool and assembly method based on measured data |
| CN110900481A (en) * | 2019-11-06 | 2020-03-24 | 浙江大学 | Flexible array aircraft skin adsorbs frock |
| CN111421210A (en) * | 2020-05-08 | 2020-07-17 | 法孚低温设备(苏州)有限公司 | Numerical control plasma cutting machine's system semicircle pipe centre gripping equipment of book |
| CN212371644U (en) * | 2020-05-29 | 2021-01-19 | 重庆久德机械制造有限公司 | Clamping mechanism for drilling |
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