CN117685282A - Aviation anti-loosening bolt based on memory alloy and fastening method - Google Patents
Aviation anti-loosening bolt based on memory alloy and fastening method Download PDFInfo
- Publication number
- CN117685282A CN117685282A CN202410156360.4A CN202410156360A CN117685282A CN 117685282 A CN117685282 A CN 117685282A CN 202410156360 A CN202410156360 A CN 202410156360A CN 117685282 A CN117685282 A CN 117685282A
- Authority
- CN
- China
- Prior art keywords
- loosening
- gasket
- groove
- cutting
- nut
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 229910001285 shape-memory alloy Inorganic materials 0.000 title claims abstract description 63
- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000005520 cutting process Methods 0.000 claims abstract description 115
- 238000005553 drilling Methods 0.000 claims description 16
- 230000008859 change Effects 0.000 claims description 12
- 230000002265 prevention Effects 0.000 claims description 12
- 238000005452 bending Methods 0.000 claims description 11
- 239000000956 alloy Substances 0.000 claims description 6
- 230000000149 penetrating effect Effects 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 3
- 238000012545 processing Methods 0.000 abstract description 4
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 14
- 238000009434 installation Methods 0.000 description 12
- 239000007788 liquid Substances 0.000 description 7
- 229910052757 nitrogen Inorganic materials 0.000 description 7
- 230000008569 process Effects 0.000 description 7
- 238000013461 design Methods 0.000 description 6
- 238000003825 pressing Methods 0.000 description 5
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- 239000002023 wood Substances 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 229910001566 austenite Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000006386 memory function Effects 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Gasket Seals (AREA)
Abstract
The invention discloses an aviation anti-loosening bolt based on a memory alloy and a fastening method, which relate to the technical field of fasteners, and are characterized in that the structure of an existing common bolt is improved in a simple structure, the structural strength of the existing bolt is basically not changed, a U-shaped hole groove is only processed on a screw rod piece, a cutting drill hole is respectively formed at two end positions of the groove and the groove, and the cutting drill hole penetrates through a hexagon head and forms a semicircular slot with a certain length on the screw rod of the screw rod piece; although the U-shaped hole groove is processed on the existing screw rod part, the structure of the screw rod part is affected to a certain extent, the anti-loosening insert is inserted into the U-shaped hole groove, the anti-loosening insert is made of NiTiNb shape memory alloy, the influence of processing the U-shaped hole groove on the screw rod part is made up through the anti-loosening insert, and the structural strength of the screw rod part is further enhanced through the anti-loosening insert.
Description
Technical Field
The invention relates to the technical field of fasteners, in particular to an aviation anti-loosening bolt based on a memory alloy and a fastening method.
Background
Bolts are a common type of fastener, typically made of metal, used to join two or more objects together. The bolt is composed of a head portion, a shaft portion and a screw thread, and an object is fixed by rotating or tightening the screw thread.
The anti-loosening bolt is a special bolt, and the design purpose of the anti-loosening bolt is to prevent loosening of the bolt. Such bolts typically have special locking means to lock the bolt head and nut so that they are not easily loosened. Common anti-loosening bolts include self-locking screws, spring washers, counter nuts, and the like. These bolts are widely used in applications requiring long-term fixation or high-strength fixation, for example, in the fields of machinery, vehicles, ships, aviation, and the like.
Publication (bulletin) number: CN115163633a discloses a locking bolt structure, which comprises a bottom plate, a gasket ring, a pressing plate, an inserting rod and an upper stud, wherein the top of the bottom plate is provided with a center pillar, two half studs symmetrically arranged at the front end and the rear end of the center pillar, and two expansion sheets symmetrically arranged at two sides of the center pillar; the gasket sleeve is sleeved on the outer side of the middle column, and the bottom end of the gasket sleeve is sleeved on the bottom end of the middle column; a sinking groove is formed in the top end of the middle column, the pressing plate is horizontally arranged in the sinking groove and is connected with the middle column in an up-down sliding manner, and a jacking column is vertically arranged in the middle of the pressing plate; the compression ring is arranged on the inserted link, the bottom end of the inserted link is inserted into a space formed by the half stud, the expansion piece and the middle column, a notch is formed in the bottom end of the inserted link positioned below the compression ring, two clips which are distributed in an X shape and are hinged with the inserted link through a fixing pin are arranged in the notch, and a tension spring is arranged between the two clips positioned above the fixing pin; the upper stud is arranged on the inserted link above the compression ring in a rotating way. The technology can effectively prevent the fastening piece from loosening, and ensures the reliability of the bolt connection structure.
However, the anti-loosening bolt is complicated in structure, high in cost and inconvenient to popularize and use, and the structural strength of the original bolt is changed in order to realize the anti-loosening structure, so that time and labor are wasted in fastening and installation.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides an aviation anti-loosening bolt and a fastening method based on a memory alloy, which solve the problems that the prior anti-loosening bolt is excessively complex in structure, high in cost and inconvenient to popularize and use, and the structural strength of the prior bolt is changed to realize the anti-loosening structure, so that the fastening and the installation are time-consuming and labor-consuming.
The invention is realized by the following technical scheme:
the aviation anti-loosening bolt based on the memory alloy comprises a screw rod piece, a nut, a gasket and anti-loosening cutting, wherein a cutting groove is formed in the middle of the end face of a hexagon head of the screw rod piece, cutting drilling holes are respectively formed in the positions of two ends of the cutting groove, and the cutting drilling holes penetrate through the hexagon head and form semicircular slots with a certain length on a screw rod of the screw rod piece;
the fastening end face of the nut is at least provided with a pair of radial nut anti-loosening grooves;
a pair of radial gasket anti-loosening grooves are formed in the top surface of the gasket and correspond to the nut anti-loosening grooves;
the gasket is made of a memory alloy material; the anti-loosening insert is of a U-shaped structure made of memory alloy materials, the screw rod piece is inserted on a connecting through hole of a connected piece, the insert part of the anti-loosening insert is inserted on an insert drill hole of the screw rod piece, the gasket is sleeved on a screw rod penetrating through the connecting through hole and the anti-loosening insert, the insert of the anti-loosening insert is bent in a gasket anti-loosening groove of the gasket, the screw cap is screwed on the screw rod, so that the screw cap is close to the gasket, when the position of the screw cap anti-loosening groove corresponds to the position of the gasket anti-loosening groove, the gasket and the insert are heated, the gasket is thickened and extruded between the screw cap and the connected piece, and the insert is extruded between the screw cap anti-loosening groove and the gasket anti-loosening groove.
Further, the tail end of the semicircular slot is provided with a chamfer for opening the cutting.
Further, the tail end of the cutting is provided with a cutting chamfer matched with the chamfer at the tail end of the semicircular slot.
Further, the section of the anti-loosening cutting is of a semicircular structure.
Further, the nut anti-loosening groove is a semicircular groove.
Further, the gasket anti-loosening groove is a concave groove.
Further, the fastening end face of the nut is provided with three pairs of radial nut anti-loosening grooves, and each nut anti-loosening groove is arranged in the middle of the hexagonal surface of the nut.
Further, the gasket and the anti-loosening insert are made of NiTiNb shape memory alloy.
Further, under the condition that the anti-loosening cutting does not have phase change, the thickness dimension of the anti-loosening cutting is 102% -105% of the depth dimension of the anti-loosening groove of the gasket.
The invention is realized by the following another technical scheme:
a fastening method of an aviation anti-loose bolt based on a memory alloy comprises the following steps:
step 1, inserting the screw rod piece on a connecting through hole of a connected piece, sleeving the gasket on the screw rod penetrating through the connecting through hole, aligning the gasket anti-loosening groove with the semicircular slot,
step 2, inserting the cutting part of the anti-loosening cutting into a cutting drilling hole of the screw rod part, wherein the cutting penetrates through the gasket to prop against the tail end of the semicircular slot and then opens;
step 3, bending the cutting into a gasket anti-loosening groove of the gasket by using a tool;
step 4, the nut is screwed on the screw rod, and when the nut is close to the gasket, the nut anti-loosening groove is aligned with the gasket anti-loosening groove;
and step 5, heating the gasket and the cutting, wherein the gasket is thickened and extruded between the nut and the connected piece, and the cutting is thickened and extruded between the nut anti-loosening groove and the gasket anti-loosening groove, so that the nut cannot rotate.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. the invention relates to an aviation anti-loosening bolt based on a memory alloy and a fastening method, which are characterized in that the structure of the existing common bolt is improved in a simple structure, the structural strength of the existing bolt is basically not changed, only U-shaped hole grooves are processed on a screw rod piece, cutting drill holes are respectively formed at the positions of two ends of the strip groove and the strip groove, and the cutting drill holes penetrate through a hexagon head and form a semicircular slot with a certain length on the screw rod of the screw rod piece; although the U-shaped hole groove is processed on the existing screw rod part, the structure of the screw rod part is affected to a certain extent, the anti-loosening insert is inserted into the U-shaped hole groove, the anti-loosening insert is made of NiTiNb shape memory alloy, the influence of processing the U-shaped hole groove on the screw rod part is made up through the anti-loosening insert, and the structural strength of the screw rod part is further enhanced through the anti-loosening insert.
2. The invention relates to an aviation anti-loosening bolt and a fastening method based on a memory alloy, wherein a gasket and an anti-loosening insert are made of a NiTiNb shape memory alloy; the characteristics of the shape memory alloy are reasonably utilized to be combined with the structural characteristics of the bolt, so that the nuts and the gaskets on the bolt are locked by the phase-changed anti-loosening cutting, thereby realizing the anti-loosening effect of the bolt.
3. According to the aviation anti-loosening bolt and the fastening method based on the memory alloy, the semicircular groove structure of the nut anti-loosening groove is adopted, the semicircular groove structure is adopted by the nut anti-loosening groove, the semicircular structure is adopted by the section of the anti-loosening cutting, the structural design of the anti-loosening cutting is adopted, the first convenience is brought to match with the semicircular groove structure, the second convenience is brought to the cutting bending operation, the semicircular structure of the third anti-loosening cutting is matched with the semicircular groove structure of the nut anti-loosening groove, and in the alignment operation of the nut anti-loosening groove and the cutting, the nut anti-loosening groove is difficult to be completely aligned with the cutting due to the fact that an operator observes and installs according to experience, so that the semicircular structural feature of the cutting can play a role of alignment with the semicircular groove of the nut anti-loosening groove, and accurate installation is realized.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiments of the invention. In the drawings:
FIG. 1 is a schematic structural view of an aviation anti-loose bolt installation state based on a memory alloy.
FIG. 2 is a schematic view of a part of a memory alloy-based aviation anti-loosening bolt installation state structure.
FIG. 3 is a schematic structural view of an aviation anti-loosening bolt based on a memory alloy in a state of completing anti-loosening installation.
FIG. 4 is a schematic view of the structure of the screw member of the present invention.
Fig. 5 is a schematic view of the structure of the nut of the present invention.
FIG. 6 is a schematic view of the structure of the anti-loosening cutting according to the present invention.
Fig. 7 is a schematic view of a bending-state anti-loosening cutting structure of the present invention.
Fig. 8 is a schematic view of a gasket structure according to the present invention.
In the drawings, the reference numerals and corresponding part names:
1-screw rod, 2-nut, 3-gasket, 4-locking insert, 5-hexagon head, 6-strip groove, 7-insert drilling, 8-screw rod, 9-semicircle slot, 10-nut anti-loosening groove, 11-gasket anti-loosening groove, 12-connected piece, 13-insert, 14-insert chamfer.
Detailed Description
The technical scheme of the invention is further described below by the specific embodiments with reference to the accompanying drawings.
Wherein the drawings are for illustrative purposes only and are shown in schematic, non-physical, and not intended to limit the invention; for the purpose of better illustrating embodiments of the invention, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the size of the actual product; it will be appreciated by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.
The same or similar reference numbers in the drawings of embodiments of the invention correspond to the same or similar components; in the description of the present invention, it should be understood that, if the terms "upper", "lower", "left", "right", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, only for convenience in describing the present invention and simplifying the description, rather than indicating or implying that the apparatus or elements being referred to must have a specific orientation, be constructed and operated in a specific orientation, so that the terms describing the positional relationships in the drawings are merely for exemplary illustration and are not to be construed as limiting the present invention, and that the specific meanings of the terms described above may be understood by those of ordinary skill in the art according to specific circumstances.
In the description of the present invention, unless explicitly stated and limited otherwise, the term "coupled" or the like should be interpreted broadly, as it may be fixedly coupled, detachably coupled, or integrally formed, as indicating the relationship of components; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between the two parts or interaction relationship between the two parts. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Example 1
As shown in fig. 1 to 8, the memory alloy-based aviation locking bolt of the invention comprises a screw member 1, a nut 2, a gasket 3 and a locking cutting 4, wherein the screw member 1, the nut 2 and the gasket 3 are all of common structures of the existing bolt, and the invention is simply processed on the basis of the structures of the existing screw member 1, the nut 2 and the gasket 3, and specifically comprises the following steps: the middle part of the end face of the hexagon head 5 of the screw member 1 is provided with a strip groove 6, the depth of the strip groove 6 is about 1/2 of the thickness of the hexagon head 5, the length of the strip groove 6 is 115% -120% of the diameter of the screw 8, the installation of the anti-loosening cutting 4 is realized under the condition that the structural strength of the screw member 1 is not changed as much as possible, the two end positions of the strip groove 6 are respectively provided with a cutting drilling hole 7, and the cutting drilling holes 7 penetrate through the hexagon head 5 and form semicircular slots 9 with a certain length on the screw 8 of the screw member 1; the semicircular slot 9 has a length substantially corresponding to the thickness of the attached member 12 and the spacer 3.
As shown in fig. 5, at least a pair of radial nut loosening prevention grooves 10 are formed on the fastening end surface of the nut 2; as shown in fig. 8, a pair of radial gasket anti-loosening grooves 11 are arranged on the top surface of the gasket 3 corresponding to the nut anti-loosening grooves 10; the structural strength of the nut 2 is high, the structural strength of the nut 2 is not affected by the nut anti-loosening groove 10 arranged on the fastening end face, so that a plurality of pairs of nut anti-loosening grooves 10 can be arranged according to field requirements, three pairs of radial nut anti-loosening grooves 10 are arranged on the fastening end face of the nut 2, and each nut anti-loosening groove 10 is arranged at the middle position of the hexagonal surface of the nut 2. The plurality of pairs of nut looseness prevention grooves 10 are arranged mainly for the purpose of nearby matching of the nut looseness prevention grooves 10 and the gasket looseness prevention grooves 11.
The gasket 3 is made of a memory alloy material; as shown in fig. 6, the locking insert 4 is a U-shaped structure made of a memory alloy material, the screw rod 1 is inserted in a connecting hole of the connected piece 12, the insert 13 of the locking insert 4 is partially inserted in the insert hole 7 of the screw rod 1, the bottom of the locking insert 4 is completely inserted in the insert slot 6, the gasket 3 is sleeved on the screw rod 8 and the locking insert 4 passing through the connecting hole, the insert 13 of the locking insert 4 is bent in the gasket anti-loosening groove 11 of the gasket 3, the screw cap 2 is screwed on the screw rod 8, so that the screw cap 2 is close to the gasket 3, when the screw cap anti-loosening groove 10 corresponds to the gasket anti-loosening groove 11, because the insert 13 protrudes out of the gasket anti-loosening groove 11, the fastening surface of the screw cap 2 cannot be attached to the top surface of the gasket 3, the insert 13 is firstly contacted with the screw cap 2, when the screw cap 2 is mounted, the screw cap 2 is made to approach or press against the insert 13, whether the gasket anti-loosening groove 10 on the screw cap 2 is aligned with the gasket anti-loosening groove 11, and the gasket 2 cannot be pressed against the gasket 3 when the screw cap 2 is generally aligned with the gasket anti-loosening groove 11, and the gasket 2 is pressed against the gasket 3, and the gasket is pressed against the gasket 3.
As shown in fig. 1-3, according to the memory alloy-based aviation locking bolt, a bolt piece 1 is inserted into a connecting through hole of a connected piece 12 by a mounting and fastening method, and a gasket 3 is sleeved on a bolt 8 penetrating through the connecting through hole, so that a gasket locking groove 11 is aligned with a semicircular slot 9; the cutting 13 of the anti-loosening cutting 4 is partially inserted into the cutting drilling hole 7 of the screw rod piece 1, in the process of inserting the anti-loosening cutting 4, a wood hammer or a rubber hammer can be used for knocking out the bottom of the anti-loosening cutting 4, the bottom of the anti-loosening cutting 4 is completely inserted into the cutting groove 6, and the cutting 13 penetrates through the gasket 3 to prop against the tail end of the semicircular slot 9 and then is opened; bending the cutting 13 into the gasket anti-loosening groove 11 of the gasket 3 by using a tool; the nut 2 is screwed on the screw rod 8, when the nut 2 is close to the gasket 3, the nut anti-loosening groove 10 is aligned with the gasket anti-loosening groove 11; the washer 3 and the insert 13 are heated, the washer 3 is thickened and pressed between the nut 2 and the connected piece 12, and the insert 13 is thickened and pressed between the nut loosening prevention groove 10 and the washer loosening prevention groove 11, so that the nut 2 cannot rotate. As shown in fig. 2, the protrusion of the cutting 13 is protruding from the top surface of the spacer 3, which is not obvious due to the view of the drawing.
In the process of bending the cutting 13, in order to prevent the cutting 13 from generating a phase change due to heat, the cutting 13 may be sprayed with liquid nitrogen to be subjected to a process of bending, and the bending may be performed according to the installation environment temperature. The cutting 13 can be bent by pressing the nut 2 using a tool such as a sleeve or pliers, and the cutting 13 is sprayed with liquid nitrogen by a common method using a sleeve tool.
In fig. 1, the washer 3 and the locking insert 4 are not phase-changed, the thickness dimension is in a contracted state, and a certain gap is left between the nut 2 and the washer 3 during the screwing process of the nut 2. As shown in fig. 2, the washer 3 and the insert 13 are heated, the washer 3 is pressed between the nut 2 and the to-be-connected member 12 in a thickened manner, and the insert 13 is pressed between the nut loosening prevention groove 10 and the washer loosening prevention groove 11 in a thickened manner, so that the nut 2 cannot rotate. Due to the special structural design of the cooperation of the cutting 13 and the nut anti-loosening groove 10, the cambered surface of the cutting 13 is convex, and the cambered surface of the nut anti-loosening groove 10 is concave, after the thickness of the cutting 13 is increased, the cutting 13 cannot completely seal the nut anti-loosening groove 10, a certain allowance is reserved between the cutting 13 and the nut anti-loosening groove, and the allowance is possibly asymmetrical, but the structural design reserves expansion allowance for the anti-loosening bolt, and when two parts are pulled by the limit, such as under the strong vibration condition, the nut 2 cannot rotate completely, and can play a good buffering role through the rotation allowance, so that the anti-loosening bolt is prevented from being broken, and the connection failure is caused.
The invention relates to an aviation anti-loosening bolt based on a memory alloy, which is structurally improved in a simple way on the structure of the existing common bolt, basically does not change the structural strength of the existing bolt, and only is a U-shaped hole groove formed in a screw rod piece 1, wherein the U-shaped hole groove comprises a strip groove 6 and two end positions of the strip groove 6 are respectively provided with a cutting drilling hole 7, and the cutting drilling hole 7 penetrates through a hexagon head 5 and forms a semicircular slot 9 with a certain length on a screw rod 8 of the screw rod piece 1; although the U-shaped hole groove is processed on the existing screw rod piece 1, the structure of the screw rod piece 1 is affected to a certain extent, the anti-loosening insert 4 is inserted into the U-shaped hole groove, the anti-loosening insert 4 is made of NiTiNb shape memory alloy, the influence of the processing of the U-shaped hole groove on the screw rod piece 1 is compensated through the anti-loosening insert 4, and the structural strength of the screw rod piece 1 is further enhanced through the anti-loosening insert 4.
According to the aviation anti-loosening bolt based on the memory alloy, when the anti-loosening bolt is disassembled, only liquid nitrogen is sprayed on the part of the cutting 13 and the gasket 3 to cool, so that the nut 2 and the gasket 3 are subjected to phase change, the size is reduced, the nut 2 can be withdrawn, the cutting 13 is straightened, and the screw part 1 and the anti-loosening cutting 4 can be pulled out from the connecting through hole on the connected piece 12, so that the bolt is disassembled.
Example 2
As shown in fig. 1 to 8, according to the memory alloy-based aviation locking bolt of the present invention, the end of the semicircular slot 9 is provided with a chamfer for expanding the cutting 13 on the basis of the above-mentioned embodiment. The tail end of the cutting 13 is provided with a cutting chamfer 14 which is matched with the chamfer at the tail end of the semicircular slot 9. The tail ends of the semicircular slots 9 and the tail ends of the cutting 13 are respectively provided with a chamfer, so that when the anti-loosening cutting 4 is inserted, the tail ends of the cutting 13 are lower than the tail ends of the semicircular slots 9 and are opened, and the cutting 13 is bent conveniently.
Example 3
As shown in fig. 1-8, according to the memory alloy-based aviation locking bolt, on the basis of the embodiment, the section of the locking cutting 4 is of a semicircular structure. The nut looseness prevention groove 10 is a semicircular groove. The gasket anti-loosening groove 11 is a concave groove.
The semicircular groove structure of the nut anti-loosening groove 10 is adopted by the nut anti-loosening groove 10, the concave groove structure is adopted by the nut anti-loosening groove 10, the semicircular structure is adopted by the section of the anti-loosening cutting 4, the structural design of the anti-loosening cutting 4 is matched with the semicircular slot 9 in structure, the cutting 13 is convenient to bend and operate in the second mode, the semicircular structure of the third anti-loosening cutting 4 is matched with the semicircular groove structure of the nut anti-loosening groove 10, in the alignment operation of the nut anti-loosening groove 10 and the cutting 13, as the operator is according to experience and observation installation, the nut anti-loosening groove 10 and the cutting 13 are inevitably aligned completely, then the semicircular structural characteristics of the cutting 13 can play a role of alignment with the semicircular groove of the nut anti-loosening groove 10, and thus accurate installation is realized.
Example 4
As shown in figures 1-8, the aviation anti-loosening bolt based on the memory alloy is characterized in that the gasket 3 and the anti-loosening insert 4 are made of NiTiNb shape memory alloy on the basis of the embodiment. In the case that the anti-loosening insert 4 does not have a phase change, the thickness dimension of the anti-loosening insert 4 is 102% -105% of the depth dimension of the gasket anti-loosening groove 11. According to the multiple tests, the phase-change deformation size of the gasket 3 and the anti-loosening cutting 4 is 102-105% of the original size, and the phase-change deformation size is made of NiTiNb shape memory alloy. Therefore, the thickness dimension of the anti-loosening insert 4 is designed to be 102% -105% of the depth dimension of the gasket anti-loosening groove 11. In this region, after the gasket 3 changes phase, it can be pressed between the nut 2 and the connected piece 12.
The invention adopts a material with a wide hysteresis shape memory function, namely NiTiNb shape memory alloy, to manufacture the gasket 3 and the anti-loosening insert 4, and the temperature is controlled during assembly, so that the deformation is driven by phase change to enlarge the thickness of the memory alloy gasket 3 and the anti-loosening insert 4, thereby completing the anti-loosening installation of the bolt. When the maintenance of the aircraft or aviation parts needs to be disassembled, the liquid nitrogen can be sprayed to the memory alloy gasket 3 and the anti-loosening insert 4 for cooling, and the gasket 3 and the anti-loosening insert 4 shrink due to phase change, so that the disassembly without damage is realized.
The memory alloy shim 3 and the anti-loosening insert 4 referred to herein are made of a wide hysteresis shape memory alloy NiTiNb. And according to the material state of the connecting piece, the three-state size design and the manufacture of the gasket 3 and the anti-loosening cutting 4 are carried out. During the screw connection, the gasket 3 and the anti-loosening cutting 4 in the finished state are assembled according to the requirement, and then the gasket is heated to enable the temperature to exceed the austenite reverse transformation point, and the thickness size of the gasket is increased due to memory recovery. The locking connection of the bolts is realized.
The invention relates to an aviation anti-loosening bolt based on a memory alloy, wherein a gasket 3 and an anti-loosening insert 4 are made of a NiTiNb shape memory alloy; the characteristics of the shape memory alloy are reasonably utilized to be combined with the structural characteristics of the bolt, so that the nuts 2 and the gaskets 3 on the bolt are locked by the phase-changed anti-loosening insert 4, thereby realizing the anti-loosening effect of the bolt, and furthermore, according to the characteristics of the shape memory alloy, the phase change of the gaskets 3 and the anti-loosening insert 4 is realized through the temperature influence, so that the anti-loosening bolt can be disassembled.
Because the gasket 3 and the anti-loosening insert 4 are made of NiTiNb shape memory alloy, the gasket 3 and the anti-loosening insert 4 can be automatically thickened and expanded to fill a loosening gap under the condition that the anti-loosening bolt connection is loosened.
Example 5
As shown in fig. 1 to 8, a fastening method of an aviation locking bolt based on a memory alloy comprises the following steps:
step 1, inserting the screw rod 1 on a connecting through hole of a connected piece 12, sleeving the gasket 3 on a screw rod 8 penetrating through the connecting through hole, aligning the gasket anti-loosening groove 11 with the semicircular slot 9,
step 2, inserting the cutting 13 part of the anti-loosening cutting 4 on the cutting drilling 7 of the screw rod part 1, wherein the cutting 13 penetrates through the gasket 3 to prop against the tail end of the semicircular slot 9 and then opens; in the process of inserting the anti-loosening cutting 4, a wood hammer or a rubber hammer can be used for knocking out the bottom of the anti-loosening cutting 4, so that the bottom of the anti-loosening cutting 4 is completely inserted in the cutting groove 6.
Step 3, bending the cutting 13 into the gasket anti-loosening groove 11 of the gasket 3 by using a tool;
step 4, the screw cap 2 is screwed on the screw rod 8, and when the screw cap 2 is close to the gasket 3, the screw cap anti-loosening groove 10 is aligned with the gasket anti-loosening groove 11;
and step 5, heating the gasket 3 and the cutting 13, wherein the gasket 3 is thickened and pressed between the nut 2 and the connected piece 12, and the cutting 13 is thickened and pressed between the nut looseness prevention groove 10 and the gasket looseness prevention groove 11, so that the nut 2 cannot rotate.
In the process of bending the cutting 13, in order to prevent the cutting 13 from generating a phase change due to heat, the cutting 13 may be sprayed with liquid nitrogen to be subjected to a process of bending, and the bending may be performed according to the installation environment temperature. The cutting 13 can be bent by pressing the nut 2 using a tool such as a sleeve or pliers, and the cutting 13 is sprayed with liquid nitrogen by a common method using a sleeve tool.
The invention relates to a fastening method of an aviation anti-loosening bolt based on a memory alloy, which is characterized in that the structure of the existing common bolt is improved in a simple structure, the structural strength of the existing bolt is basically not changed, only U-shaped hole grooves are processed on a screw rod piece 1, and the U-shaped hole grooves comprise strip grooves 6 and two end positions of the strip grooves 6 are respectively provided with a cutting drilling hole 7, and the cutting drilling hole 7 penetrates through a hexagon head 5 and forms a semicircular slot 9 with a certain length on a screw rod 8 of the screw rod piece 1; although the U-shaped hole groove is processed on the existing screw rod piece 1, the structure of the screw rod piece 1 is affected to a certain extent, the anti-loosening insert 4 is inserted into the U-shaped hole groove, the anti-loosening insert 4 is made of NiTiNb shape memory alloy, the influence of the processing of the U-shaped hole groove on the screw rod piece 1 is compensated through the anti-loosening insert 4, and the structural strength of the screw rod piece 1 is further enhanced through the anti-loosening insert 4.
According to the memory alloy-based aviation anti-loosening bolt dismantling method, when the anti-loosening bolt is dismantled, only liquid nitrogen is sprayed to the cutting 13 part and the gasket 3 to cool, so that the nut 2 and the gasket 3 are subjected to phase change, the size is reduced, the nut 2 can be withdrawn, the cutting 13 is straightened, and the bolt piece 1 and the anti-loosening cutting 4 can be pulled out from the connecting through hole on the connected piece 12, so that the bolt dismantling is completed. The invention relates to an aviation anti-loosening bolt and a fastening method based on a memory alloy, wherein a gasket 3 and an anti-loosening insert 4 are made of a NiTiNb shape memory alloy; the characteristics of the shape memory alloy are reasonably utilized to be combined with the structural characteristics of the bolt, so that the nuts 2 and the gaskets 3 on the bolt are locked by the phase-changed anti-loosening insert 4, thereby realizing the anti-loosening effect of the bolt, and furthermore, according to the characteristics of the shape memory alloy, the phase change of the gaskets 3 and the anti-loosening insert 4 is realized through the temperature influence, so that the anti-loosening bolt can be disassembled.
The foregoing description of the embodiments has been provided for the purpose of illustrating the general principles of the invention, and is not meant to limit the scope of the invention, but to limit the invention to the particular embodiments, and any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (10)
1. The utility model provides an aviation locking bolt based on memory alloy, includes screw rod piece (1), nut (2), gasket (3) and locking cutting (4), its characterized in that: the middle part of the end face of the hexagon head (5) of the screw member (1) is provided with a strip groove (6), two end positions of the strip groove (6) are respectively provided with a cutting drilling hole (7), and the cutting drilling holes (7) penetrate through the hexagon head (5) and form a semicircular slot (9) with a certain length on the screw (8) of the screw member (1);
the fastening end face of the nut (2) is at least provided with a pair of radial nut anti-loosening grooves (10);
a pair of radial gasket anti-loosening grooves (11) are formed in the top surface of the gasket (3) and correspond to the nut anti-loosening grooves (10);
the gasket (3) is made of a memory alloy material; the anti-loosening bolt is characterized in that the anti-loosening bolt (4) is of a U-shaped structure made of a memory alloy material, the bolt (1) is inserted into a connecting through hole of the connected piece (12), the bolt (13) of the anti-loosening bolt (4) is partially inserted into a bolt drilling hole (7) of the bolt (1), the gasket (3) is sleeved on the bolt (8) penetrating through the connecting through hole and the anti-loosening bolt (4), the bolt (13) of the anti-loosening bolt (4) is bent into a gasket anti-loosening groove (11) of the gasket (3), the nut (2) is screwed onto the bolt (8), the nut (2) is made to be close to the gasket (3), when the position of the nut anti-loosening groove (10) corresponds to the position of the gasket anti-loosening groove (11), the gasket (3) and the bolt (13) are heated, the gasket (3) is thickened and extruded between the nut anti-loosening groove (10) and the gasket anti-loosening groove (11) by the connecting piece (12).
2. The memory alloy-based aviation lockbolt of claim 1, wherein: the tail end of the semicircular slot (9) is provided with a chamfer for expanding the cutting (13).
3. The memory alloy-based aviation lockbolt of claim 2, wherein: the tail end of the cutting (13) is provided with a cutting chamfer (14) matched with the chamfer at the tail end of the semicircular slot (9).
4. The memory alloy-based aviation lockbolt of claim 1, wherein: the section of the anti-loosening cutting (4) is of a semicircular structure.
5. The memory alloy-based aviation lockbolt of claim 1, wherein: the nut looseness prevention groove (10) is a semicircular groove.
6. The memory alloy-based aviation lockbolt of claim 1, wherein: the gasket anti-loosening groove (11) is a concave groove.
7. The memory alloy-based aviation lockbolt of claim 1, wherein: the fastening terminal surface of nut (2) is equipped with three pairs of radial nut anti-loosening groove (10), and every nut anti-loosening groove (10) sets up in the hexagonal face middle part position of nut (2).
8. The memory alloy-based aviation lockbolt of claim 1, wherein: the gasket (3) and the anti-loosening cutting (4) are made of NiTiNb shape memory alloy.
9. The memory alloy-based aviation lockbolt of claim 1, wherein: under the condition that the anti-loosening insert (4) does not have phase change, the thickness dimension of the anti-loosening insert (4) is 102% -105% of the depth dimension of the gasket anti-loosening groove (11).
10. A method for fastening an aircraft anti-loosening bolt based on a memory alloy as claimed in any one of claims 1-9, comprising the steps of:
step 1, inserting a screw rod (1) into a connecting through hole of a connected piece (12), and sleeving a gasket (3) on a screw rod (8) penetrating through the connecting through hole to align the gasket anti-loosening groove (11) with the semicircular slot (9);
step 2, inserting a cutting (13) part of the anti-loosening cutting (4) on a cutting drilling hole (7) of the screw rod piece (1), wherein the cutting (13) penetrates through the gasket (3) to prop against the tail end of the semicircular slot (9) and then opens;
step 3, bending the cutting (13) into a gasket anti-loosening groove (11) of the gasket (3) by using a tool;
step 4, a screw cap (2) is screwed on the screw rod (8), and when the screw cap (2) is close to the gasket (3), the screw cap anti-loosening groove (10) is aligned with the gasket anti-loosening groove (11);
and 5, heating the gasket (3) and the cutting (13), wherein the gasket (3) is thickened and extruded between the nut (2) and the connected piece (12), and the cutting (13) is thickened and extruded between the nut anti-loosening groove (10) and the gasket anti-loosening groove (11), so that the nut (2) cannot rotate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410156360.4A CN117685282B (en) | 2024-02-04 | 2024-02-04 | Aviation anti-loosening bolt based on memory alloy and fastening method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410156360.4A CN117685282B (en) | 2024-02-04 | 2024-02-04 | Aviation anti-loosening bolt based on memory alloy and fastening method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117685282A true CN117685282A (en) | 2024-03-12 |
| CN117685282B CN117685282B (en) | 2024-06-14 |
Family
ID=90137627
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410156360.4A Active CN117685282B (en) | 2024-02-04 | 2024-02-04 | Aviation anti-loosening bolt based on memory alloy and fastening method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117685282B (en) |
Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB108585A (en) * | 1916-10-12 | 1917-08-16 | William Prescott | Improvements in Lock Nuts. |
| JP2005273890A (en) * | 2004-03-22 | 2005-10-06 | Etsuzo Kuinose | Locking of bolt and nut by locking washer |
| KR20100012955A (en) * | 2008-07-30 | 2010-02-09 | 윤택우 | Loose prevention apparatus of bolt and nut |
| KR20140105228A (en) * | 2013-02-22 | 2014-09-01 | 주식회사 엘지화학 | Jointng apparatus for preventing looseness |
| US20170129041A1 (en) * | 2015-11-11 | 2017-05-11 | Spirit AreoSystems, Inc. | Method for joule heating diffusion bonded honeycomb core |
| CN206234234U (en) * | 2016-09-10 | 2017-06-09 | 王一婷 | A kind of sleeve pipe check bolt |
| KR20170108503A (en) * | 2016-03-18 | 2017-09-27 | 주식회사 모두금속 | Fastener using shape memory alloy |
| JP2019078401A (en) * | 2017-10-19 | 2019-05-23 | 傳長 多田 | Metal fatigue and looseness prevention bolt |
| CN110778592A (en) * | 2019-11-12 | 2020-02-11 | 苏州国嘉记忆合金有限公司 | Anti-loosening device and method for isolating switch based on titanium-nickel-based alloy memory effect |
| CN210599805U (en) * | 2019-08-28 | 2020-05-22 | 何汉文 | Intelligent anti-loosening titanium alloy fastener based on memory alloy |
| CN213298555U (en) * | 2020-09-16 | 2021-05-28 | 河北习铁紧固件有限公司 | Anti-loosening bolt |
| CN113339384A (en) * | 2021-05-24 | 2021-09-03 | 中国电力科学研究院有限公司 | Spacing formula check bolt structure of opening gasket |
| CN215444728U (en) * | 2021-05-20 | 2022-01-07 | 吴维祥 | Anti-loosening bolt with thread blocking type function |
| CN115163633A (en) * | 2022-07-19 | 2022-10-11 | 靖江市飞天紧固件制造有限公司 | Anti-loosening bolt structure |
| CN218031031U (en) * | 2021-07-13 | 2022-12-13 | 中国船舶重工集团公司第七一五研究所 | Thread anti-loosening connection structure based on nickel-titanium memory alloy wire |
| CN219082048U (en) * | 2022-12-20 | 2023-05-26 | 株洲耀辉光机电研究开发有限公司 | Self-locking fastening mechanism |
| CN219317394U (en) * | 2022-12-13 | 2023-07-07 | 浙江三林五金制品有限公司 | High-load carbon steel flange bolt |
| CN117124108A (en) * | 2023-10-27 | 2023-11-28 | 成都鑫晨航空科技有限公司 | Screw rod piece drilling tool and clamping method |
-
2024
- 2024-02-04 CN CN202410156360.4A patent/CN117685282B/en active Active
Patent Citations (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB108585A (en) * | 1916-10-12 | 1917-08-16 | William Prescott | Improvements in Lock Nuts. |
| JP2005273890A (en) * | 2004-03-22 | 2005-10-06 | Etsuzo Kuinose | Locking of bolt and nut by locking washer |
| KR20100012955A (en) * | 2008-07-30 | 2010-02-09 | 윤택우 | Loose prevention apparatus of bolt and nut |
| KR20140105228A (en) * | 2013-02-22 | 2014-09-01 | 주식회사 엘지화학 | Jointng apparatus for preventing looseness |
| US20170129041A1 (en) * | 2015-11-11 | 2017-05-11 | Spirit AreoSystems, Inc. | Method for joule heating diffusion bonded honeycomb core |
| KR20170108503A (en) * | 2016-03-18 | 2017-09-27 | 주식회사 모두금속 | Fastener using shape memory alloy |
| CN206234234U (en) * | 2016-09-10 | 2017-06-09 | 王一婷 | A kind of sleeve pipe check bolt |
| JP2019078401A (en) * | 2017-10-19 | 2019-05-23 | 傳長 多田 | Metal fatigue and looseness prevention bolt |
| CN210599805U (en) * | 2019-08-28 | 2020-05-22 | 何汉文 | Intelligent anti-loosening titanium alloy fastener based on memory alloy |
| CN110778592A (en) * | 2019-11-12 | 2020-02-11 | 苏州国嘉记忆合金有限公司 | Anti-loosening device and method for isolating switch based on titanium-nickel-based alloy memory effect |
| CN213298555U (en) * | 2020-09-16 | 2021-05-28 | 河北习铁紧固件有限公司 | Anti-loosening bolt |
| CN215444728U (en) * | 2021-05-20 | 2022-01-07 | 吴维祥 | Anti-loosening bolt with thread blocking type function |
| CN113339384A (en) * | 2021-05-24 | 2021-09-03 | 中国电力科学研究院有限公司 | Spacing formula check bolt structure of opening gasket |
| CN218031031U (en) * | 2021-07-13 | 2022-12-13 | 中国船舶重工集团公司第七一五研究所 | Thread anti-loosening connection structure based on nickel-titanium memory alloy wire |
| CN115163633A (en) * | 2022-07-19 | 2022-10-11 | 靖江市飞天紧固件制造有限公司 | Anti-loosening bolt structure |
| CN219317394U (en) * | 2022-12-13 | 2023-07-07 | 浙江三林五金制品有限公司 | High-load carbon steel flange bolt |
| CN219082048U (en) * | 2022-12-20 | 2023-05-26 | 株洲耀辉光机电研究开发有限公司 | Self-locking fastening mechanism |
| CN117124108A (en) * | 2023-10-27 | 2023-11-28 | 成都鑫晨航空科技有限公司 | Screw rod piece drilling tool and clamping method |
Non-Patent Citations (1)
| Title |
|---|
| 李俊良, 杜彦良, 孙宝臣, 沈英明: "一种新型智能防松螺母的研究", 工程设计学报, no. 03, 30 June 2003 (2003-06-30), pages 46 - 49 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117685282B (en) | 2024-06-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20070048107A1 (en) | Nut plates and threaded inserts and methods of assembling and installing the same | |
| CN212928473U (en) | Thread anti-loosening device | |
| CN105422582A (en) | Whole overturning single-edge bolt fastening piece | |
| CN117685282B (en) | Aviation anti-loosening bolt based on memory alloy and fastening method | |
| CN110486365A (en) | A kind of unilateral side bolt fastener and its method | |
| CN211524578U (en) | Door frame section bar connection structure | |
| CN210178729U (en) | Bolt and nut assembly capable of preventing loosening | |
| US4112993A (en) | Grommet assembly | |
| CN204477001U (en) | External thread fastener with pre-grooved tail end capable of realizing riveting assembly | |
| CN111098912A (en) | Mounting and connecting structure for steering column universal joint fork and steering engine | |
| US11585163B2 (en) | Connecting tubulars in a wellbore | |
| CN108547844B (en) | Sectional type unilateral bolt fastener | |
| CN105179394A (en) | Titanium nickel iron memory alloy fastener and connector with same | |
| CN104595329A (en) | External thread fastener with pre-grooved tail end and capable of realizing riveting assembly and using method thereof | |
| CN221033494U (en) | Bolt-nut fastener and double-plate connecting structure | |
| CN210889644U (en) | Unilateral bolt fastener | |
| CN112901616A (en) | Multi-directional and multi-purpose convenient locking and connecting device | |
| CN111927870A (en) | Assembly type unilateral bolt assembly | |
| CN215928085U (en) | Brazed joint check bolt | |
| CN218644613U (en) | Connection structure | |
| CN220622399U (en) | Prevent from pine torsion bolt | |
| CN212047557U (en) | Mounting and connecting structure for steering column universal joint fork and steering engine | |
| CN219911421U (en) | Mounting and positioning structure | |
| CN214170313U (en) | Door and window assembly structure of locking pine | |
| CN213575107U (en) | Assembly type unilateral bolt assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |