CN111173825A

CN111173825A - Outer hexagonal screw rod device of aviation anti-disassembly

Info

Publication number: CN111173825A
Application number: CN202010083116.1A
Authority: CN
Inventors: 龚云超
Original assignee: Xinchang Chenglong Bearing Factory
Current assignee: XINCHANG LIANHANG MACHINERY Co.,Ltd.
Priority date: 2020-02-08
Filing date: 2020-02-08
Publication date: 2020-05-19
Anticipated expiration: 2040-02-08
Also published as: CN111173825B

Abstract

The invention discloses an aviation anti-disassembly outer hexagonal screw device which comprises a bolt cap assembly and an anti-disassembly seat assembly, wherein the bolt cap assembly comprises a bolt cap and a bolt cap; the bottom surface of the bolt cap component is welded with a limiting ring, and the bottom surface of the limiting ring is vertically welded with a screw rod; the anti-disassembly seat assembly is of an annular seat structure and is sleeved on the outer side of the bolt cap assembly, and the bottom end face of the anti-disassembly seat assembly is in extrusion contact with the top face of the limiting ring; a locking pad is also spot-welded on the bottom surface of the limiting ring, and a circle of anti-skid threads are also arranged on the bottom surface of the locking pad; the bolt cap component is in an outer hexagonal style, the anti-dismantling seat is dismantled in a mode that the spring piece is compressed after six flat-mouth screwdrivers outside are inserted into the spring piece, so that the outer hexagonal of the bolt cap leaks out, and the original rotary screwing-out application state of the bolt is recovered.

Description

Outer hexagonal screw rod device of aviation anti-disassembly

Technical Field

The invention relates to the technical field of bolt structures, in particular to an aviation anti-disassembly outer hexagonal screw device.

Background

The bolt is a mechanical part and is a cylindrical threaded fastener matched with a nut. A fastener consisting of a head part and a screw (a cylinder with external threads) needs to be matched with a nut and is used for fastening and connecting two parts with through holes. This form of connection is known as a bolted connection. If the nut is screwed off from the bolt, the two parts can be separated, so the bolt connection belongs to detachable connection, bolts applied to some special occasions are directly screwed on the connecting piece, the other end of the bolt does not need to be locked by the nut, the bolt part is usually longer in size, for example, the bolt adopted on aviation equipment is in a long rod shape and is much longer than the bolt of a common standard part, the bolt penetrates into a threaded hole formed on the equipment from the bottom upwards to connect two parts of accessories together, and the bolt needs to be subjected to anti-loosening or anti-disassembling treatment on the outer end due to the particularity of the installation occasion, so the use completeness is improved.

Disclosed in chinese patent application No. CN201721790867.7 is an anti-dismantle bolt, its structure includes nut, screw rod and packing ring, the nut includes screw thread and magnetite, the screw thread is cruciform structure, the nut middle part is located to the screw thread, the screw thread is connected in the nut through the mode of inlaying, the screw thread middle part is located to the magnetite, the magnetite is connected in the nut through the mode of inlaying, the screw rod includes dead lever, threaded rod and fried piece, the screw rod left side is located to the dead lever, the screw rod is connected in the nut through welded mode, the dead lever right side is located to the threaded rod, the threaded rod passes through welded mode and connects in the screw rod, the threaded rod right side is located to the fried piece, the fried piece is connected in the threaded rod through swing joint's.

Above-mentioned bolt of anti-disassembly formula through addding the fried piece, can make the bolt get into the touching in the wall body and open to not only can reach the purpose of preventing tearing open, be favorable to improving the practicality of bolt moreover, simple structure, the practicality is strong.

However, the application of the above-mentioned case to the tamper-proof structure has the following problems in practical use:

the anti-dismantling ring of the anti-loosening structure arranged at the inner end of the bolt and the fried piece are not connected with the long threaded hole formed in the equipment in a threaded manner along with the long screw, so that the anti-dismantling and anti-loosening mode cannot be adapted to the design, the bolt of the long screw is fixed in the installation mode of the long threaded hole, the disclosed fried piece extends into the wall along with the screw and can be dismantled, obviously, the anti-dismantling and anti-loosening mode is ideal and difficult to realize, and both sides of the fried piece cannot penetrate into the wall even after the fried piece is dismantled, so that the anti-dismantling function is formed, and therefore, the structural design is not reasonable.

Disclosure of Invention

The invention aims to provide an aviation anti-disassembly outer hexagonal screw device, which aims to solve the problems that the prior anti-disassembly ring similar to the anti-loosening structure arranged at the inner end of the bolt disclosed in the comparison document and the frying piece are provided in the background technology, the anti-disassembly and anti-loosening mode cannot be in threaded connection with a long screw rod together in a long threaded hole formed in equipment, so that the anti-disassembly and anti-loosening mode cannot be adapted to the installation mode of fixing the bolt of the long screw rod in the long threaded hole, and the disclosed frying piece can be exploded when the bolt extends into a wall body along with the screw rod, obviously, the anti-disassembly ring and the frying piece are more ideal and difficult to realize.

In order to achieve the purpose, the invention provides the following technical scheme: an aviation anti-disassembly outer hexagonal screw device comprises a bolt cap assembly and an anti-disassembly seat assembly; the bottom surface of the bolt cap component is welded with a limiting ring, and the bottom surface of the limiting ring is vertically welded with a screw rod; the anti-disassembly seat assembly is of an annular seat structure and is sleeved on the outer side of the bolt cap assembly, and the bottom end face of the anti-disassembly seat assembly is in extrusion contact with the top face of the limiting ring; a locking pad is also spot-welded on the bottom surface of the limiting ring, and a circle of anti-skid threads are also arranged on the bottom surface of the locking pad; the bolt cap component is in an outer hexagonal shape, the inner ring of the anti-disassembly seat component sleeved on the outer side of the bolt cap component is also in an inner hexagonal shape, and the bolt cap component and the anti-disassembly seat component are in close contact.

Further: the bolt cap assembly comprises a bolt cap, a notch and a jack; the outer hexagonal surface of the bolt cap is also provided with notches in a U-shaped groove pattern in a vertical mode, and the notches are also internally provided with jacks in a circular through hole pattern.

Further: six sunk cavity type groove cavities which are positioned on the outer hexagonal surface of the bolt cap are formed between the jack and the notch, and the inlet at the top side of the notch is arranged in a chamfer structure.

Further: the anti-disassembly seat assembly comprises an anti-disassembly seat, spring pieces and compression columns, wherein the spring pieces are arranged at six positions, the spring pieces are uniformly welded on the hexagonal socket faces of the anti-disassembly seat, and the compression columns are welded on the spring pieces one by one.

Further: the size of the hexagonal surface of the inner ring of the anti-dismantling seat is larger than that of the outer hexagonal surface of the bolt cap sleeved with the anti-dismantling seat, and the bottom ends of the spring pieces spot-welded on the hexagonal surface of the anti-dismantling seat are designed to be in a chamfer structure.

Further: the inner end of the compression leg is processed by adopting a smooth round angle, and the size of the inner end corresponds to that of the jack arranged on the outer hexagonal surface of the bolt cap component.

Further: the outer circular surface of the anti-dismantling seat is of a conical structure, and the diameter of the top end of the anti-dismantling seat is smaller than that of the bottom end of the anti-dismantling seat.

Compared with the prior art, the invention has the beneficial effects that:

the long screw bolt of this structure has the functional characteristic of anti-disassembly equally, and its anti-disassembly function is located outside bolt cap department, and through the design of matter, makes its anti-disassembly function be a precautionary, and the bolt still can be through reasonable mode of cracking, is demolishd by the outside, still makes two parts work piece that it assembled realize the dismouting combination.

Six side faces of screw bolt cap end have all been seted up one set of notch, form screens location structure, and the corresponding seat accessory of preventing tearing open that has set up of screens structure with these six faces, accessory excircle surface is the tapered surface pattern, and its spiral-lock is served in the bolt cap of the outer end of screw rod back, and the other people is difficult to relax loosens it, realizes withholding and prevents the purpose of tearing open outward.

The anti-dismantling seat is of a buckling type, an inner hexagonal surface type structure is adopted inside, a piece of spring steel sheet is welded on a structural surface in a spot mode, and after the anti-dismantling seat can be buckled with a bolt cap protected, the anti-loosening effect is achieved, and a short column is arranged on the six pieces of spring steel sheets, and can form elastic clamping with a clamping groove structure arranged on the bolt cap after the anti-dismantling seat is buckled on the bolt cap, so that two layers of application modes for preventing bolts from being dismantled or loosened are formed. Although the anti-loosening and anti-dismantling device has the double functional characteristics of better anti-loosening and anti-dismantling, the buckled and pressed anti-dismantling seat of the accessory still has the detachable functional characteristics, the anti-dismantling seat can be dismantled in a mode that the spring piece is compressed after six flat screwdrivers outside are inserted into the spring piece, so that the outer hexagon of the bolt cap leaks out and the original application state of the bolt in a rotary screwing-out mode is recovered, and common personnel cannot expect due to the fact that the dismantling mode adopts the six flat screwdrivers to assist dismantling, and therefore the bolt has the anti-dismantling functional characteristics, but has the concealed dismantling characteristics.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a schematic top view of the present invention;

FIG. 3 is a schematic top plan view of the present invention;

FIG. 4 is a disassembled schematic view of the present invention;

FIG. 5 is a partial schematic view of the present invention taken from FIG. 1;

FIG. 6 is a schematic view of the present invention as it would appear laid flat;

FIG. 7 is a schematic plan view of the spring plate of the present invention.

In the figure: 1. a screw; 2. a limiting ring; 3. a bolt cap assembly; 301. a bolt cap; 302. a notch; 303. a jack; 4. a tamper-evident seat assembly; 401. a tamper evident base; 402. a spring plate; 403. pressing the column; 5. a locking pad; 501. and (4) anti-skid lines.

Detailed Description

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 only a part of the embodiments of the present invention, and not all of the embodiments. 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.

Referring to fig. 1-7, the present invention provides a technical solution: an aviation anti-disassembly outer hexagonal screw device comprises a bolt cap assembly 3 and an anti-disassembly seat assembly 4; the bottom surface of the bolt cap component 3 is welded with a limiting ring 2, and the bottom surface of the limiting ring 2 is vertically welded with a screw rod 1; the anti-disassembly seat assembly 4 is of an annular seat structure and is sleeved on the outer side of the bolt cap assembly 3, and the bottom end face of the anti-disassembly seat assembly 4 is in extrusion contact with the top face of the limiting ring 2; the bottom surface of the limiting ring 2 is also spot-welded with a piece of anti-loosening pad 5, and the bottom surface of the anti-loosening pad 5 is also provided with a circle of anti-skidding lines 501, the anti-loosening pad 5 has an anti-loosening effect similar to a standard part pattern, and is directly welded on the bottom surface of the limiting ring 2 to form the anti-loosening effect, so that the time for assembling the bolt during the installation of the bolt can be reduced; the bolt cap component 3 is in an outer hexagonal shape, the inner ring of the anti-dismounting seat component 4 sleeved on the outer side of the bolt cap component is also in an inner hexagonal shape, and the bolt cap component and the anti-dismounting seat component are in close contact.

Wherein: as shown in fig. 4 and 5, the cap assembly 3 includes a cap 301, a notch 302, and a receptacle 303; the outer hexagonal face of bolt cap 301 is still seted up U-shaped groove type's notch 302 according to the perpendicular mode, and all inwards have opened the jack 303 of circular through-hole pattern again in these notches 302, six spacing notches that lie in bolt cap 301 hexagonal face have been constituted by notch 302 and jack 303, and six groove cavities that lie in the heavy cavate on the outer hexagonal face of bolt cap 301 have been constituted altogether between jack 303 and the notch 302, and the top side entry of notch 302 adopts the chamfer structure setting that is convenient for top side pushing down's pressure post 403 to stretch into wherein, for the speed of impressing that improves pressure post 403, improve the smoothness, the interior end of pressure post 403 adopts smooth fillet to handle, and its size corresponds with the jack 303 size of seting up on the outer hexagonal face of bolt cap subassembly 3.

Wherein: as shown in fig. 4 and 5, the anti-detach base assembly 4 includes an anti-detach base 401, a spring plate 402 and pressing columns 403, wherein the number of the spring plates 402 is six, the spring plates 402 are uniformly welded on the hexagon socket surface of the anti-detach base 401, and the pressing columns 403 are welded on the spring plates 402 one by one, after the anti-detach base assembly 4 is pressed down, the spring plates 402 on the spring plates can be fastened on six outer surfaces of the bolt cap 301, and after the anti-detach base 401 is pressed down continuously, the pressing columns 403 spot-welded on the inner end surfaces of the spring plates 402 are pressed into the clamping groove structures arranged on the six surfaces of the bolt cap 301 one by one, at this time, the bolt cap 301 in the hexagonal form is protected by the outer circular shape of the anti-detach base assembly 4, other people are difficult to screw the bolt cap 301, because the outer side of the bolt cap 301 is changed into the circular surface structure by the anti-detach base 401, which is not convenient for screwing operation, and because the outer circular surface of the anti-, the diameter of the top end of the anti-disassembly seat 401 is smaller than that of the bottom end of the anti-disassembly seat, so that the difficulty of screwing the anti-disassembly seat is improved again.

Wherein: the size of the hexagonal surface of the inner ring of the anti-disassembly seat 401 is larger than the size of the outer hexagonal surface of the bolt cap 301 sleeved with the anti-disassembly seat 401, and the bottom end of the spring piece 402 spot-welded on the hexagonal surface of the anti-disassembly seat 401 is designed in a chamfer structure, so that when the spring piece 402 is buckled and pressed on the bolt cap 301 along with the anti-disassembly seat 401, the spring piece 402 is inserted into the outer hexagonal surface of the bolt cap 301 more smoothly.

The working principle is as follows: after the screw 1 of the structure is screwed into the threaded hole of the equipment, in order to prevent the bolt cap 301 from being screwed again by other people, the accessory anti-dismantling seat 401 can be pressed down on the bolt cap 301, the anti-dismantling seat 401 is inserted on six outer faces of the bolt cap 301 by using the spring sheet 402 on the hexagon socket, and the short columnar pressing columns 403 arranged on the inner end face of the spring sheet 402 are pressed into the clamping groove structures arranged on the six faces of the bolt cap 301 one by one according to the notch 302, so that it can be seen that the anti-dismantling seat 401 with protective function is limited on the bolt cap 301, at this time, the bolt cap 301 with the hexagonal pattern is protected by using the outer circular shape of the anti-dismantling seat component 4, other people are difficult to screw the bolt cap 301, because the outer side of the anti-dismantling seat 401 is changed into the circular face structure at this time, the screwing operation is inconvenient, and because the outer circular face of the anti-dismantling seat 401 is the conical structure, the diameter size of the top end is smaller than the diameter size of the bottom, the difficulty of turning the tamper evident seat 401 is thus increased again.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. An aviation anti-disassembly outer hexagonal screw device comprises a bolt cap assembly (3) and an anti-disassembly seat assembly (4); the method is characterized in that: the bottom surface of the bolt cap component (3) is welded with a limiting ring (2), and the bottom surface of the limiting ring (2) is vertically welded with a screw (1); the anti-disassembly seat assembly (4) is of an annular seat structure and is sleeved on the outer side of the bolt cap assembly (3), and the bottom end face of the anti-disassembly seat assembly (4) is in extrusion contact with the top face of the limiting ring (2); a piece of anti-loosening pad (5) is also spot-welded on the bottom surface of the limiting ring (2), and a circle of anti-skidding threads (501) are also arranged on the bottom surface of the anti-loosening pad (5); the bolt cap component (3) is in an outer hexagonal shape, the inner ring of the anti-dismounting seat component (4) sleeved on the outer side of the bolt cap component is also in an inner hexagonal shape, and the bolt cap component and the anti-dismounting seat component are in close contact.

2. The aviation anti-disassembly outer hexagonal screw device of claim 1, wherein: the cap assembly (3) comprises a cap (301), a slot (302), and a receptacle (303); the outer hexagonal surface of the bolt cap (301) is also provided with notches (302) in a U-shaped groove pattern in a vertical mode, and the notches (302) are also internally provided with jacks (303) in a circular through hole pattern.

3. The aircraft dismounting-proof outer hexagonal screw device according to claim 21, wherein: six sunk cavity type groove cavities which are positioned on the outer hexagonal surface of the bolt cap (301) are formed between the jack (303) and the notch (302), and the top side inlet of the notch (302) is arranged in a chamfering structure.

4. The aviation anti-disassembly outer hexagonal screw device of claim 1, wherein: the anti-disassembly seat assembly (4) comprises an anti-disassembly seat (401), spring plates (402) and press columns (403), wherein the spring plates (402) are arranged at six positions, the spring plates are uniformly welded on an inner hexagonal surface of the anti-disassembly seat (401), and the press columns (403) are welded on the spring plates (402) one by one.

5. The aviation disassembly-preventing outer hexagonal screw device as claimed in claim 4, wherein: the size of the hexagonal surface of the inner ring of the anti-dismantling seat (401) is larger than that of the outer hexagonal surface of the bolt cap (301) sleeved with the anti-dismantling seat, and the bottom end of the spring piece (402) spot-welded on the hexagonal surface of the anti-dismantling seat (401) is designed to be in a chamfer structure.

6. The aviation disassembly-preventing outer hexagonal screw device as claimed in claim 4, wherein: the inner end of the compression leg (403) is processed by adopting a smooth round angle, and the size of the compression leg corresponds to that of the jack (303) arranged on the outer hexagonal surface of the bolt cap component (3).

7. The aviation disassembly-preventing outer hexagonal screw device as claimed in claim 4, wherein: the outer circular surface of the anti-dismantling seat (401) is of a conical structure, and the diameter of the top end of the anti-dismantling seat is smaller than that of the bottom end of the anti-dismantling seat.