CN103851058A - Bolt and barrel-shaped nut assembly - Google Patents
Bolt and barrel-shaped nut assembly Download PDFInfo
- Publication number
- CN103851058A CN103851058A CN201210500088.4A CN201210500088A CN103851058A CN 103851058 A CN103851058 A CN 103851058A CN 201210500088 A CN201210500088 A CN 201210500088A CN 103851058 A CN103851058 A CN 103851058A
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- China
- Prior art keywords
- self
- bolt
- barrel
- locking nut
- retainer
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Abstract
The invention provides a bolt and barrel-shaped nut assembly which consists of a machine body frame, a bolt, a self-locking nut, a retaining rack, a barrel and a plug-in connecting hanging rack. A combined structure is shown in a drawing 1, the machine body frame is of a hollow structure, the self-locking nut and the retaining rack are installed in the barrel, hanging pieces at two ends of the retaining rack are hung on the edge of the barrel, the upper end of the retaining frame is of an open structure, and the self-locking nut is located at the center of the open structure of the upper end of the retaining rack. A gap s is reserved between the self-locking nut and the barrel, the self-locking nut can freely float in the barrel, the barrel, and the self-locking nut and the retaining rack jointly form a barrel-shaped nut assembly which is horizontally installed inside the machine body hanging rack and fixed at the barrel-shaped nut assembly mounting position by means of elastic force produced by the retaining rack subjected to stress and elastic deformation. A positioning hole for the bolt to penetrate is formed in the center of the plug-in connecting hanging rack, the bolt penetrates the positioning hole of the plug-in connecting hanging rack to be screwed with the self-locking nut of the barrel-shaped nut assembly in the machine body frame, and connection of a plug-in and a machine body is achieved.
Description
Technical field
The present invention relates to a kind of fastening piece, particularly a kind of airframe and plug-in high-strength bolt and the barrel nut assembly that is connected use.
Background technique
Airframe is to adopt shoulder shaft type joint to connect with the plug-in conventional art being connected, airframe provides the longitudinal screw hole of plug-in requirement use with not allowing frame structure in plug-in connection, traditional solution is on framework, to design a specialized structure shoulder shaft type joint is installed, the plug-in shoulder shaft type joint that passes through is connected with framework, the shortcoming of this Placement is that in the time connecting, to assemble required precision high, maintainability is poor, in use, cannot again install and remove, and weight is large, on fuselage ring, also to design the corresponding construction that shoulder shaft type joint is installed, framework increases structure and has also increased accordingly weight and volume.
Summary of the invention
1. the technical problem that will solve
In order to solve airframe and the plug-in problem being connected, alleviate the weight and volume of frame structure, the invention provides a kind of bolt and barrel nut assembly that connects use.
2. technological scheme
Bolt of the present invention and barrel nut assembly are by fuselage ring, bolt, self-locking nut, retainer, bucket and plug-in connection hanger composition, structure after combination is shown in shown in accompanying drawing 1, fuselage ring 1 inside is hollow-core construction, self-locking nut 3 and retainer 4 are contained in bucket 5, retainer 4 two ends lacing film hang on bucket 5 edge, retainer 4 upper ends are hatch frames, self-locking nut 3 is positioned at the center of retainer 4 upper end open structures, between self-locking nut 3 and bucket 5, leave gap s, self-locking nut 3 can be in bucket 5 free floating, bucket 5, the common composition barrel nut of self-locking nut 3 and retainer 4 assembly is sleeping to be contained in fuselage hanger 1 hollow, the elastic force that relies on the stressed resiliently deformable of retainer to produce is fixed the rigging position of barrel nut assembly, plug-in connection hanger 6 centers are provided with the positioning hole that can penetrate bolt 2, and bolt 2 screws through the positioning hole of plug-in connection hanger 6 and the self-locking nut 3 of the interior barrel nut assembly of fuselage ring 1, realize being connected of plug-in and fuselage.
3. beneficial effect
High-strength bolt of the present invention and the simple installation of barrel nut assembly on airframe framework, can repeated disassembled and assembled, and maintainability is good; Fuselage ring does not need to design additional structure, only needs to process a horizontal through hole, has alleviated frame weight; Bolts and nuts threaded connection pair adopts self-locking design and the locking double insurance design of safety fuse cutout, and reliability is high; Bolt and barrel nut modular construction are simple, and volume is little, lightweight; The plug-in external force that is passed to fuselage ring is not directly passed to framework by nut, and is passed to bucket by nut, then is passed to framework by bucket, has increased the area of contact of framework store mounting point force part, has improved the stress phase at framework store mounting point place.
Accompanying drawing explanation
Fig. 1 is bolt of the present invention and barrel nut assembled schematic diagram;
Fig. 2 is bolt arrangement schematic diagram;
Fig. 3 is the unsteady schematic diagram of self-locking nut in bucket;
Fig. 4 is the schematic diagram after the distortion of self-locking nut screw thread position;
Fig. 5 is the side view of Fig. 4;
Fig. 6 is the structural representation of retainer;
Fig. 7 is the comparison schematic diagram of retainer stress and free state;
Fig. 8 is that the present invention is for certain airframe and the plug-in structural representation being connected.
In figure: 1-airframe framework, 2-bolt, 3-self-locking nut, 4-retainer, 5-bucket, the plug-in connection hanger of 6-, the lock silk hole on K-bolt head, the guide cone section of T-bolt screw rod end, s-flying height, the external force of A-self-locking nut applies place, screw thread distortion place of B-self-locking nut, shape when C-retainer working state, shape when D-retainer free state.
Embodiment
Now take the present invention for aircraft fuselage and the plug-in bolt being connected and barrel nut assembly as example, the present invention is elaborated.
In the present embodiment, the bolt of use is a kind of high-strength bolt, and retainer is also to adopt high strength elastic Steel material to make.Fig. 8 is that the present invention is for aircraft fuselage and the plug-in bolt being connected and barrel nut components schematic diagram, from figure, can see, self-locking nut 3 and retainer 4 are contained in cylindrical barrel 5, retainer 4 two ends lacing film hang on the edge of cylindrical barrel, retainer 4 upper ends are hatch frames, self-locking nut 3 is positioned at the center of retainer 4 upper end open structures, flying height s between self-locking nut 3 and cylindrical barrel is about 0.5mm, self-locking nut 3 can be in cylindrical barrel 5 free floating (as shown in Figure 3), cylindrical barrel 5, the common composition barrel nut of self-locking nut 3 and retainer 4 assembly is sleeping to be contained in fuselage hanger 1 hollow, the elastic force that relies on the stressed resiliently deformable of retainer to produce is fixed the rigging position of barrel nut assembly, plug-in connection hanger 6 centers are provided with the positioning hole that can penetrate high-strength bolt 2, and high-strength bolt 2 screws through the positioning hole of plug-in connection hanger 6 and the self-locking nut of the interior barrel nut assembly of fuselage ring 1, realize being connected of plug-in and fuselage.
2 of high-strength bolts are provided with the lock silk hole K of installation insurance silk, screw rod end is provided with guide cone section T, guide cone section adopts 60o angle (as shown in Figure 2), when installation, guide cone section T enters in the tapped hole of self-locking nut 3, can automatically regulate the self-locking nut axis of thread and bolt thread dead in line.
High-strength bolt 2 adopts self-locking design with the threaded connection pair of self-locking nut 3, when after being threaded of high-strength bolt 2 and self-locking nut 3, apply certain external force at the A place of the self-locking nut shown in Fig. 4 and make screw thread distortion, screw thread form after distortion is as shown in B in Fig. 5, and the self-locking thread that forms is like this secondary just can prevent in aircraft flight that bolts and nuts are because vibrating issuable becoming flexible.
Fig. 6 and Fig. 7 show the structure shape of retainer 4, as can be seen from Figure 7, in the time that retainer 4 is not stressed, its opening is in free state D place, after retainer is stressed, opening is compressed in C place, and retainer 4 expands outwardly, with cylindrical barrel 5 close contacts, thereby fix the rigging position of barrel nut assembly.
Claims (4)
1. a bolt and barrel nut assembly, by fuselage ring (1), bolt (2), self-locking nut (3), retainer (4), bucket (5) and plug-in connection hanger (6) composition, it is characterized in that: fuselage ring (1) is inner is hollow-core construction, self-locking nut (3) and retainer (4) are contained in bucket (5), the lacing film at retainer (4) two ends hangs on the edge of bucket (5), the upper end of retainer (4) is hatch frame, self-locking nut (3) is positioned at the center of retainer (4) upper end open structure, bucket (5), self-locking nut (3) and retainer (4) form that barrel nut assembly is sleeping to be contained in fuselage hanger (1) hollow jointly, the elastic force that relies on the stressed resiliently deformable of retainer (4) to produce is fixed the rigging position of barrel nut assembly, plug-in connection hanger (6) center is provided with the positioning hole that can penetrate bolt (2), bolt (2) screws through the positioning hole of plug-in connection hanger (6) and the self-locking nut (3) of the interior barrel nut assembly of fuselage ring (1), realizes being connected of plug-in and fuselage.
2. bolt according to claim 1 and barrel nut assembly, is characterized in that: bolt (2) head is provided with the lock silk hole K of installation insurance silk, and screw rod end is provided with guide cone section T.
3. bolt according to claim 1 and barrel nut assembly, is characterized in that: self-locking nut (3) and bucket leave gap s between (5), self-locking nut (3) can be in bucket (5) free floating.
4. bolt according to claim 1 and barrel nut assembly, is characterized in that: bolt (2) adopts self-locking design with the threaded connection pair of self-locking nut (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210500088.4A CN103851058A (en) | 2012-11-30 | 2012-11-30 | Bolt and barrel-shaped nut assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210500088.4A CN103851058A (en) | 2012-11-30 | 2012-11-30 | Bolt and barrel-shaped nut assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103851058A true CN103851058A (en) | 2014-06-11 |
Family
ID=50859084
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210500088.4A Pending CN103851058A (en) | 2012-11-30 | 2012-11-30 | Bolt and barrel-shaped nut assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103851058A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105240383A (en) * | 2015-09-15 | 2016-01-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Bolt positioning structure |
| CN106763089A (en) * | 2016-12-26 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airframe structure docks anti-loosening device of bolt |
| CN110895183A (en) * | 2019-11-28 | 2020-03-20 | 北京机电工程研究所 | Switching device and test system in vibration test of external aircraft of aircraft |
| WO2020124402A1 (en) * | 2018-12-19 | 2020-06-25 | 黄国城 | Nut positioning cage |
| CN114194017A (en) * | 2020-09-17 | 2022-03-18 | 奥动新能源汽车科技有限公司 | Battery pack mounting part for horizontally mounting battery pack and electric automobile with battery pack mounting part |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4498826A (en) * | 1980-04-30 | 1985-02-12 | Simmonds Oliver E | Self locking nut including an axially extending reinforcement |
| DE3911300C1 (en) * | 1989-04-07 | 1990-08-16 | Peri Gmbh, 7912 Weissenhorn, De | Spindle unit, in particular for shuttering construction work |
| CN2849294Y (en) * | 2005-12-05 | 2006-12-20 | 成都飞机设计研究所 | Barrel shaped self locking nut connector |
| CN101608657A (en) * | 2009-07-21 | 2009-12-23 | 北京市春立正达科技开发有限公司 | Self-locking nut |
| CN201723559U (en) * | 2010-08-12 | 2011-01-26 | 贵州航天精工制造有限公司 | Barrel-shaped floating self-locking nut connecting component |
| CN102678722A (en) * | 2011-03-11 | 2012-09-19 | 喜利得股份公司 | Fastening arrangement |
| CN203023241U (en) * | 2012-11-30 | 2013-06-26 | 中国航空工业标准件制造有限责任公司 | Bolt and barrel-shaped nut component |
-
2012
- 2012-11-30 CN CN201210500088.4A patent/CN103851058A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4498826A (en) * | 1980-04-30 | 1985-02-12 | Simmonds Oliver E | Self locking nut including an axially extending reinforcement |
| DE3911300C1 (en) * | 1989-04-07 | 1990-08-16 | Peri Gmbh, 7912 Weissenhorn, De | Spindle unit, in particular for shuttering construction work |
| CN2849294Y (en) * | 2005-12-05 | 2006-12-20 | 成都飞机设计研究所 | Barrel shaped self locking nut connector |
| CN101608657A (en) * | 2009-07-21 | 2009-12-23 | 北京市春立正达科技开发有限公司 | Self-locking nut |
| CN201723559U (en) * | 2010-08-12 | 2011-01-26 | 贵州航天精工制造有限公司 | Barrel-shaped floating self-locking nut connecting component |
| CN102678722A (en) * | 2011-03-11 | 2012-09-19 | 喜利得股份公司 | Fastening arrangement |
| CN203023241U (en) * | 2012-11-30 | 2013-06-26 | 中国航空工业标准件制造有限责任公司 | Bolt and barrel-shaped nut component |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105240383A (en) * | 2015-09-15 | 2016-01-13 | 中国航空工业集团公司沈阳发动机设计研究所 | Bolt positioning structure |
| CN106763089A (en) * | 2016-12-26 | 2017-05-31 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airframe structure docks anti-loosening device of bolt |
| WO2020124402A1 (en) * | 2018-12-19 | 2020-06-25 | 黄国城 | Nut positioning cage |
| CN110895183A (en) * | 2019-11-28 | 2020-03-20 | 北京机电工程研究所 | Switching device and test system in vibration test of external aircraft of aircraft |
| CN114194017A (en) * | 2020-09-17 | 2022-03-18 | 奥动新能源汽车科技有限公司 | Battery pack mounting part for horizontally mounting battery pack and electric automobile with battery pack mounting part |
| CN114194016A (en) * | 2020-09-17 | 2022-03-18 | 奥动新能源汽车科技有限公司 | Battery pack mounting part for horizontally hanging battery pack and electric automobile |
| CN114274754A (en) * | 2020-09-17 | 2022-04-05 | 奥动新能源汽车科技有限公司 | Battery mounting part for vertically hanging battery pack and electric automobile |
| CN114274754B (en) * | 2020-09-17 | 2024-05-31 | 奥动新能源汽车科技有限公司 | Battery installation part for vertically hanging battery pack and electric automobile |
| CN114194016B (en) * | 2020-09-17 | 2024-05-31 | 奥动新能源汽车科技有限公司 | Battery pack mounting part for horizontally hanging battery pack and electric automobile |
| CN114194017B (en) * | 2020-09-17 | 2024-05-31 | 奥动新能源汽车科技有限公司 | Battery pack mounting part for horizontally mounting battery pack and electric automobile with battery pack mounting part |
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Legal Events
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140611 |