CN201889342U - Impression strengthening tool for integral wall plate of aircraft - Google Patents
Impression strengthening tool for integral wall plate of aircraft Download PDFInfo
- Publication number
- CN201889342U CN201889342U CN2010206199497U CN201020619949U CN201889342U CN 201889342 U CN201889342 U CN 201889342U CN 2010206199497 U CN2010206199497 U CN 2010206199497U CN 201020619949 U CN201020619949 U CN 201020619949U CN 201889342 U CN201889342 U CN 201889342U
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- pincers
- bolt
- impression
- clamp
- strengthening
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Abstract
The utility model belongs to process equipment for impression strengthening of parts and relates to process equipment for impression strengthening of parts, in particular to an impression strengthening tool for an integral wall plate of an aircraft. The impression strengthening tool comprises a left clamp, a right clamp, powerful springs, two cylindrical pins, a bolt, a nut and an air cylinder, wherein the left clamp and the right clamp are connected through the bolt as a rotating shaft to form a clamp body, the nut is connected to external threads of the bolt in a sleeve joint manner, the two cylindrical pins are fixed at the front middle part of the left clamp and the front middle part of the right clamp respectively and perpendicular to the axis of the bolt, the two cylindrical pins face to each other, a gap of 20 mm to 30 mm is left between the head ends of the cylindrical pins, the powerful springs are sleeved on the two cylindrical pins, the two ends of one powerful spring are jointed with the left clamp and the two ends of the other powerful spring are jointed with the right clamp, and the air cylinder is between the left clamp and the right clamp. The impression strengthening tool solves the problems in the prior art that the crescent-shaped mark of the oil through-hole of the integral wall plate of the aircraft has an irregular shape and a non-uniform depth in case that the operating space is not open.
Description
Technical field
The utility model belongs to the stamping reinforced technological equipment of part, relates to a kind of being used for part is carried out stamping reinforced technological equipment.
Background technology
Stamping reinforced is by special equipment and particular manufacturing craft product surface to be applied active force, makes product surface produce the process of pressure, and forms adhere to specification shape, the uniform impression of the degree of depth, to improve a kind of process of corresponding site fatigue resistance.
Stamping reinforcedly must carry out the even application of force to mould, impress out the uniform vestige of the degree of depth by technological equipment.The technology aircraft adopted the riveted joint wallboard in the past, and there is the little problem of oil reserve in the middle soft tank that loads.In order to improve airborne oil mass, adopt integral tank now, its wallboard is that whole machine adds part, directly refuels in integral panel.
The I shape of integral panel is regulated oil mass by oil-through hole between the long purlin, in order to improve the fatigue resistance of oil-through hole, requires a pair of crescent vestige of oil-through hole outside design.Yet prior art is generally got ready by manual, is difficult to obtain the uniform crescent vestige of the degree of depth.
Summary of the invention
The utility model purpose is: a kind of stamping reinforced instrument that can impress out the uniform crescent vestige of the degree of depth on the overall aircraft wallboard is provided.
Technical solution of the present utility model is: the stamping reinforced instrument of a kind of overall aircraft wallboard, it comprises left side pincers, right pincers, brute spring, straight pin, bolt, nut and cylinder.Wherein, left side pincers and right pincers are by the composition caliper that links together of the bolt as turning cylinder, nut sleeve is connected on the external screw thread of bolt, the front middle part of left side pincers and right pincers, respectively be fixed with a straight pin perpendicular to the bolt axis direction, two straight pins are relative, and leave 20 to 30mm gap between the straight pin termination.Brute spring is enclosed within on two straight pins, and the brute spring two ends fit with left side pincers and right pincers, and described cylinder is arranged between left side pincers and the right pincers.
The jaw of described left side pincers and right pincers be the arc with the impressing mould profile mating surface form fit of use.
Described cylinder one end is arranged in the circular groove at pincers rear portion, a left side, and the other end is fitted with right pincers rear inner surface.
The upper and lower surface of described left side pincers and right pincers also all is provided with and alleviates groove.
Described two straight pins are crossed tight fit with left side pincers, right pincers installing hole respectively, and must reserve the gap of 20-30mm between two straight pin terminations, to guarantee the working space of brute spring.
The beneficial effects of the utility model are: the stamping reinforced instrument of the utility model overall aircraft wallboard can carry out the even application of force to impressing mould, guarantees that depth of cup is even, meets design requirement.Adopt stamping reinforced instrument, parts fixation is more convenient, has reduced the requirement of operating personnel's technical ability.Can change the work profile of impressing mould according to the shape of impression vestige, process difform impression, to obtain different strengthening effects.Can change the impressing mould of different-thickness, thereby can process difform workpiece according to the opening character or the position of operating space, therefore have bigger applicability.The output pressure of this instrument satisfies the degree of depth less than 3 millimeters needs that impression is stamping reinforced greater than 11 tons, realizes the generalization of stamping reinforced instrument.Volume is little, in light weight, has reduced working strength of workers, has improved operating efficiency.
Description of drawings
Fig. 1: the structural representation of the stamping reinforced instrument of the utility model overall aircraft wallboard;
Fig. 2: be the side view of Fig. 1;
Fig. 3: be the structural representation of left side pincers;
Fig. 4: be the structural representation of right side pincers;
Fig. 5: be the stamping reinforced tool operation schematic diagram of the utility model overall aircraft wallboard;
Among the figure: left side pincers 1, right pincers 2, brute spring 3, straight pin 4, bolt 5, nut 6, pad 7, cylinder 8, handle 9, jaw 10, installing hole 11, circular groove 12, impressing mould 13, part 14.
The specific embodiment
Below by specific embodiment the utility model is elaborated:
See also Fig. 1 and Fig. 2, wherein, Fig. 1 is the structural representation of the stamping reinforced instrument of the utility model overall aircraft wallboard, and Fig. 2 is the side view of Fig. 1.In the present embodiment, the stamping reinforced instrument of described overall aircraft wallboard comprises left side pincers 1, right pincers 2, brute spring 3, straight pin 4, bolt 5, nut 6, pad 7, cylinder 8 and handle 9.Wherein, described left side pincers 1 and right pincers 2 are by the composition caliper that links together of the bolt 5 as turning cylinder.Nut 6 is socketed on the external screw thread of bolt 5, and pad 7 is arranged between bolt 5 and the nut 6.The front middle part of left side pincers 1 and right pincers 2, it is relative respectively to be fixed with 4, two straight pins of a straight pin perpendicular to the bolt axis direction, and leaves 20 to 30mm gap between the straight pin termination.Described brute spring 3 is enclosed within on two straight pins 4, and brute spring 3 two ends fit the inwall of extruding left side pincers 1 and right pincers 2 with left side pincers 1 and right pincers 2.Described handle 9 shanks have external screw thread, screw in the screwed hole at left side pincers 1 and right pincers 2 rear portions.Cylinder 8 one ends are arranged in the circular groove at pincers 1 rear portion, a left side, and the other end is fitted with right pincers 2 rear inner surface.
Seeing also Fig. 3 is the structural representation of left side pincers.The jaw 10 of wherein said left side pincers 1 and the arc of the impressing mould profile mating surface form fit of using, the uniformity of when pressing mould being exerted pressure to improve pincers.Described left side pincers 1 front middle part has a monaural sheet, and the auricle end face is a circular arc, and a circular hole concentric with circular arc is arranged on the auricle.Be provided with an installing hole 11 that is used to install straight pin 4 perpendicular to the face of round hole axial direction between jaw 10 and the circular hole.Described left side pincers 1 rear inner surface is provided with the circular groove 12 that is used to place cylinder 8.Pincers 1 above and below, a described left side all is provided with and alleviates groove, is reducing weight, when alleviating labor strength, can improve the bending strength of left side pincers.
See also Fig. 4, it is the structural representation of described right pincers.Itself and left side pincers 1 structural similarity, its anterior jaw also is the identical arc of shape with the impressing mould profile mating surface that uses, front middle part has an ears sheet, and the distance between two auricles equates with the monaural sheet thickness of left side pincers 1, makes a left side clamp 1 monaural sheet and can be clipped between the ears sheet.Described right pincers end face is for to clamp 1 identical circular arc with a left side, has one to clamp on 1 auricle big circular holes such as circular hole is concentric with left on the ears sheet, is provided with an installing hole that is used to install straight pin 4 perpendicular to the face of round hole axial direction between its jaw and the circular hole.Right pincers 2 above and below also all are provided with and alleviate groove.
See also Fig. 5, it is the stamping reinforced tool operation schematic diagram of the utility model overall aircraft wallboard.Wherein, two impressing moulds 13 are symmetricly set on product parts 14 both sides, and the left and right clamp of the stamping reinforced instrument of overall aircraft wallboard is on impressing mould 13.When starting source of the gas, cylinder 8 beginnings are to two lateral movements, the left side pincers 1 and right pincers 2 afterbodys of fitting are with it moved laterally, because left side pincers 1 and right pincers 2 rotate around bolt 5, cause left side pincers 1 and right pincers 2 anterior jaws to move to the inside, compress impressing mould, and then integral panel is exerted pressure, obtain the crescent vestige, realize the purpose stamping reinforced oil-through hole.
The stamping reinforced instrument of the utility model overall aircraft wallboard can be changed the work profile of impressing mould according to the shape of impression vestige, processes difform impression, to obtain different strengthening effects.Can change the impressing mould of different-thickness, thereby can process difform workpiece according to the opening character or the position of operating space, therefore have bigger applicability.
Claims (5)
1. stamping reinforced instrument of overall aircraft wallboard, it is characterized in that: comprise left side pincers (1), right pincers (2), brute spring (3), straight pin (4), bolt (5), nut (6) and cylinder (8), wherein, described left side pincers (1) and right pincers (2) are by the composition caliper that links together of the bolt (5) as turning cylinder, and nut (6) is socketed on the external screw thread of bolt (5), and the front middle part of (2) is clamped on the left side pincers (1) and the right side, respectively be fixed with a straight pin (4) perpendicular to the bolt axis direction, two straight pins are relative, and leave 20 to 30mm gap between the straight pin termination, and described brute spring (3) is enclosed within on two straight pins (4), and brute spring (3) two ends fit with left side pincers (1) and right pincers (2), and described cylinder (8) is arranged between left side pincers (1) and the right pincers (2).
2. the stamping reinforced instrument of overall aircraft wallboard according to claim 1 is characterized in that: the arc of the jaw of described left side pincers (1) and right pincers (2) and the impressing mould profile mating surface form fit of use.
3. the stamping reinforced instrument of overall aircraft wallboard according to claim 2 is characterized in that: described cylinder (8) one ends are arranged in the circular groove at pincers (1) rear portion, a left side, and the other end is fitted with right pincers (2) rear inner surface.
4. the stamping reinforced instrument of overall aircraft wallboard according to claim 3 is characterized in that: the upper and lower surface of described left side pincers (1) and right pincers (2) all is provided with and alleviates groove.
5. the stamping reinforced instrument of overall aircraft wallboard according to claim 4 is characterized in that: described two straight pins (4) are crossed tight fit, and are reserved the gap of 20-30mm between two straight pins (4) termination with left side pincers (1), right pincers (2) installing hole respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206199497U CN201889342U (en) | 2010-11-19 | 2010-11-19 | Impression strengthening tool for integral wall plate of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010206199497U CN201889342U (en) | 2010-11-19 | 2010-11-19 | Impression strengthening tool for integral wall plate of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201889342U true CN201889342U (en) | 2011-07-06 |
Family
ID=44218817
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010206199497U Expired - Fee Related CN201889342U (en) | 2010-11-19 | 2010-11-19 | Impression strengthening tool for integral wall plate of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201889342U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113579663A (en) * | 2021-09-26 | 2021-11-02 | 中国航发北京航空材料研究院 | Method for prolonging fatigue life of 2124-T851 aluminum alloy porous aviation part |
| CN113664460A (en) * | 2021-09-26 | 2021-11-19 | 中国航发北京航空材料研究院 | Method for prolonging fatigue life of 7050-T7451 aluminum alloy perforated aviation part |
-
2010
- 2010-11-19 CN CN2010206199497U patent/CN201889342U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113579663A (en) * | 2021-09-26 | 2021-11-02 | 中国航发北京航空材料研究院 | Method for prolonging fatigue life of 2124-T851 aluminum alloy porous aviation part |
| CN113664460A (en) * | 2021-09-26 | 2021-11-19 | 中国航发北京航空材料研究院 | Method for prolonging fatigue life of 7050-T7451 aluminum alloy perforated aviation part |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110706 Termination date: 20181119 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |