CN202360548U - Threaded fastener structure - Google Patents
Threaded fastener structure Download PDFInfo
- Publication number
- CN202360548U CN202360548U CN 201120346084 CN201120346084U CN202360548U CN 202360548 U CN202360548 U CN 202360548U CN 201120346084 CN201120346084 CN 201120346084 CN 201120346084 U CN201120346084 U CN 201120346084U CN 202360548 U CN202360548 U CN 202360548U
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- bolt
- threaded
- threaded fastener
- fastener structure
- camber line
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Abstract
The utility model discloses a threaded fastener structure, belongs to the field of mechanical design and manufacture, and in particular relates to a threaded fastener structure. The threaded fastener structure comprises a head of a bolt, a polished rod of the bolt, a threaded tail of the bolt and a complete threaded section of the bolt, and is characterized in that: the major diameter of the complete threaded section of the bolt is smaller than the diameter of the polished rod of the bolt; on a cutting plane along the axial line of the bolt, the tail end point A of the polished rod of the bolt is connected with the starting point B of an incomplete threaded section of the bolt to form an arc line; the arc line is rotated around the axial line of the bolt to form an arc-shaped surface; and the concave surface of the arc-shaped surface faces the internal of the fastener. According to the threaded fastener structure, an installation hole of the structure is strengthened; the anti-fatigue performance of the structure is enhanced; the requirement on long service life of modern aircrafts is met; the length of the threaded tail is reduced; the weight reduction of standard components used for the aircrafts is realized; the damage to the inner wall of the hole in an installation process is reduced by adopting a novel threaded transition region structure; the requirement on model development is met; and the technical progress of domestic aviation standard components is pushed.
Description
Technical field
The utility model belongs to Machine Design and makes the field, is specifically related to a kind of threaded fastener structure.
Background technique
Standard piece is the basic component of airplane design, is the elementary cell that guarantees aircaft configuration intensity, system sealing property and full machine maintenance and reliability.Air standard part unit consumption does not generally wait to more than 200 ten thousand from hundreds of thousands spare, and wherein fastening piece accounts for 80%, and threaded fastener is topmost Fastener products, the good and bad performance and the working life that directly influences aircraft of threaded fastener performance.
Domestic conventional threads fastening piece double thread ending adopts chamfering form (like Fig. 1) with the transition zone of bar portion, interferes to be prone to when installing scratch hole wall, has increased axial length simultaneously.
The model utility content
The purpose of the utility model: the utility model is designed a kind of novel threaded fastener structure, and this type of fastening piece has reduced screw-thread ending length, uses standard piece weight thereby reduce aircraft, indirect realization the aircraft loss of weight; Adopt this type of fastening piece to carry out interference fit, can realize that high amount of interference interference connects, improve the anti-fatigue performance that structure connects, satisfy the requirement of present generation aircraft long lifetime; Through adopting the screw thread transition zone of new structure, reduce the damage that installation process causes the hole inwall; Satisfying Spielpassung with the cooperation of gauge hole series is connected.Reduce the kind of fastening piece, reduce purchase cost.
The technological scheme of the utility model is: a kind of threaded fastener structure; Comprise bolt head, bolt light rod, bolt thread ending, bolt complete thread section three parts, it is characterized in that bolt complete thread section Major Diam is less than the bolt light rod diameter; Along on the cutting plane of bolt axis; The line of bolt light rod terminal point A and bolt incomplete thread section starting point B is a camber line, and camber line forms arc shaped surface around the rotation of bolt axis, and the concave surface of arc shaped surface is inner towards fastening piece.
Said camber line is one section camber line of curvature continually varying.
Said bolt light rod, incomplete thread section are tangent with arc shaped surface respectively.
Said bolt light rod terminal point A is the intersection point of bolt light rod and camber line along on the cutting plane of bolt axis.
Said incomplete thread section starting point B is the intersection point in camber line and the big footpath of bolt thread.
Beneficial effect
The utility model is strengthened the structure mounting hole, strengthens the structure anti-fatigue performance, meets the requirement of present generation aircraft long lifetime; Reduce screw-thread ending length, realize that aircraft is with standard piece structure loss of weight; Adopt novel screw thread transition zone structure, reduce the damage that installation process causes the hole inwall; Satisfy model development demand, promote the technological progress of domestic air mail standard piece.
Description of drawings
Fig. 1 conventional threads fastening piece screw-thread ending and bar portion transition zone schematic representation
Fig. 2 bolt arrangement schematic representation
The 1-bolt head; The 2-bolt light rod; The 3-screw-thread ending; 4-incomplete thread section
The typical structure bolt transition zone schematic representation of Fig. 3 the utility model
The 5-polished rod; The 6-screw-thread ending; 7-incomplete thread section; 8-complete thread section; The 9-Major Diam; The 10-camber line
Embodiment
Through embodiment the utility model is further described below:
Domestic tradition adopts the bolt of unit bore system design; Be divided into Spielpassung type, excessive fitting-type etc., have different bar portion tolerance ranges, when high amount of interference cooperates; Can only strengthen the bar footpath; Can't realize that the fastening piece under the different matching relationships is general, and the selection of the tolerance in bolt and hole is complicated, is unfavorable for design Selection.
The utility model adopts unit shaft system, takes all factors into consideration Spielpassung and high amount of interference and cooperates the demand to the bolt shank tolerance, makes bar portion tolerance can be applicable to cooperations such as high amount of interference, transition, gap simultaneously; The tensile strength that screw thread is taken all factors into consideration in the correction of Major Diam requires and the high requirement of interfering bolt installation under the mated condition.
Shown in Figure 2 transition zone can be good at joining rod portion and screw thread in order to adopt the typical structure bolt of the utility model, and surface smoothing can well push reinforcement to the mounting hole inwall, raising structure anti-fatigue performance in the bolt installation process; Transition zone drops to i.e. termination below the Major Diam simultaneously, effectively shortens length of transition zone, reduces pts wt.Transition zone schematic representation such as Fig. 2, D ' is for revising the maximum value of Major Diam, and what bolt light rod should be level and smooth drops under the Major Diam D ' maximum value, and the curvature of any section camber line in the F district must not be greater than maximum value.
Claims (5)
1. threaded fastener structure; Comprise bolt head, bolt light rod, bolt thread ending, bolt complete thread section three parts, it is characterized in that bolt complete thread section Major Diam is less than the bolt light rod diameter; Along on the cutting plane of bolt axis; The line of bolt light rod terminal point A and bolt incomplete thread section starting point B is a camber line, and camber line forms arc shaped surface around the rotation of bolt axis, and the concave surface of arc shaped surface is inner towards fastening piece.
2. threaded fastener structure according to claim 1 is characterized in that, said camber line is one section camber line of curvature continually varying.
3. threaded fastener structure according to claim 1 is characterized in that, said bolt light rod, incomplete thread section are tangent with arc shaped surface respectively.
4. threaded fastener structure according to claim 1 is characterized in that, said bolt light rod terminal point A is the intersection point of bolt light rod and camber line along on the cutting plane of bolt axis.
5. threaded fastener structure according to claim 1 is characterized in that, said incomplete thread section starting point B is the intersection point in camber line and the big footpath of bolt thread.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120346084 CN202360548U (en) | 2011-09-14 | 2011-09-14 | Threaded fastener structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120346084 CN202360548U (en) | 2011-09-14 | 2011-09-14 | Threaded fastener structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202360548U true CN202360548U (en) | 2012-08-01 |
Family
ID=46571737
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120346084 Expired - Lifetime CN202360548U (en) | 2011-09-14 | 2011-09-14 | Threaded fastener structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202360548U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102935577A (en) * | 2012-11-21 | 2013-02-20 | 中国航空工业集团公司北京航空制造工程研究所 | Short-ending light bolt ending section rolling strengthening method and strengthening rollers |
| CN103557219A (en) * | 2013-11-13 | 2014-02-05 | 东方蓝天钛金科技有限公司 | Light bolt fastening piece as well as manufacturing method and mold thereof |
| CN103967906A (en) * | 2013-01-29 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Super-strength MJ-thread alloy steel bolt |
| EP3364049A1 (en) * | 2017-02-20 | 2018-08-22 | The Boeing Company | Radiused lead-in for interference fit fasteners |
| CN109026955A (en) * | 2018-09-12 | 2018-12-18 | 中国航空制造技术研究院 | A kind of short ending threaded fastener |
| CN112963423A (en) * | 2021-02-26 | 2021-06-15 | 山东中航和辉航空标准件有限责任公司 | Countersunk rivet structure fastener |
| CN117889137A (en) * | 2024-03-18 | 2024-04-16 | 中国航发四川燃气涡轮研究院 | Bolt structure capable of improving fatigue resistance of inter-disc bolts and design method thereof |
-
2011
- 2011-09-14 CN CN 201120346084 patent/CN202360548U/en not_active Expired - Lifetime
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102935577A (en) * | 2012-11-21 | 2013-02-20 | 中国航空工业集团公司北京航空制造工程研究所 | Short-ending light bolt ending section rolling strengthening method and strengthening rollers |
| CN102935577B (en) * | 2012-11-21 | 2014-12-24 | 中国航空工业集团公司北京航空制造工程研究所 | Short-ending light bolt ending section rolling strengthening method and strengthening rollers |
| CN103967906A (en) * | 2013-01-29 | 2014-08-06 | 中国航空工业集团公司西安飞机设计研究所 | Super-strength MJ-thread alloy steel bolt |
| CN103557219A (en) * | 2013-11-13 | 2014-02-05 | 东方蓝天钛金科技有限公司 | Light bolt fastening piece as well as manufacturing method and mold thereof |
| JP2018136021A (en) * | 2017-02-20 | 2018-08-30 | ザ・ボーイング・カンパニーＴｈｅ Ｂｏｅｉｎｇ Ｃｏｍｐａｎｙ | Radiused lead-in section for interference fit fastener |
| CN108457958A (en) * | 2017-02-20 | 2018-08-28 | 波音公司 | Fillet for Interference-fit fasteners introduces |
| EP3364049A1 (en) * | 2017-02-20 | 2018-08-22 | The Boeing Company | Radiused lead-in for interference fit fasteners |
| US10641307B2 (en) | 2017-02-20 | 2020-05-05 | The Boeing Company | Radiused lead-in for interference fit fasteners |
| CN108457958B (en) * | 2017-02-20 | 2021-10-01 | 波音公司 | Fillet lead-in for interference fit fasteners |
| JP7020877B2 (en) | 2017-02-20 | 2022-02-16 | ザ・ボーイング・カンパニー | R-introduction part for tightening fasteners |
| CN109026955A (en) * | 2018-09-12 | 2018-12-18 | 中国航空制造技术研究院 | A kind of short ending threaded fastener |
| CN112963423A (en) * | 2021-02-26 | 2021-06-15 | 山东中航和辉航空标准件有限责任公司 | Countersunk rivet structure fastener |
| CN117889137A (en) * | 2024-03-18 | 2024-04-16 | 中国航发四川燃气涡轮研究院 | Bolt structure capable of improving fatigue resistance of inter-disc bolts and design method thereof |
| CN117889137B (en) * | 2024-03-18 | 2024-06-04 | 中国航发四川燃气涡轮研究院 | Bolt structure capable of improving fatigue resistance of inter-disc bolts and design method thereof |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120801 |