CN103759597B - Missile cabin radial monoclinic bushing bolt connection structure - Google Patents
Missile cabin radial monoclinic bushing bolt connection structure Download PDFInfo
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- CN103759597B CN103759597B CN201410015491.7A CN201410015491A CN103759597B CN 103759597 B CN103759597 B CN 103759597B CN 201410015491 A CN201410015491 A CN 201410015491A CN 103759597 B CN103759597 B CN 103759597B
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Abstract
A missile cabin radial monoclinic bushing bolt connection structure comprises a cabin connecting frame A, a cabin connecting frame B, a seal ring, an inclined bushing, a bolt and a dual-lug holding plate self-locking nut. The dual-lug holding plate self-locking nut is fixed in the position of a stepped through hole B in the inner surface of the cabin connecting frame B, the seal ring is placed in a square groove of the cabin connecting frame A, the inner surface of the connecting region of the cabin connecting frame A is in sleeved connection with the outer surface of the connecting region of the cabin connecting frame B in a manner of clearance fit. A stepped through hole A and the stepped through hole B in the connecting regions are flushed coaxially. The inclined bushing is inserted into the stepped through hole, and the inclined end face of the inclined bushing is tangent to the inclined face of a right angled trapezoid groove of the outer surface of the cabin connecting frame B. The bolt penetrate the inclined bushing to match with the dual-lug holding plate self-locking nut in a screwed manner, and the cabin connecting frame A and the cabin connecting frame B are tightly connected by tightly screwing the bolt. Axial displacement of cabins is limited by radially screwing the bolt, and the missile cabin radial monoclinic bushing bolt connection structure has the advantages in both radial connection and axial connection.
Description
Technical field
The present invention relates to a kind of missile cabin radial monocline lining bolt fastening structure, this type of attachment has easy to connect, that installation space large and syndeton quality is little feature, belongs to field of aerospace technology.
Background technology
Along with the development of modern high technology, the demand of war and solid engines widely use the development progressively miniaturized with guidance unit, miniaturization of missilery forward, lighting, high maneuverability requirements, Far Range, high accuracy, prominently to prevent by force, power, systematization, multipurpose, low cost and the future development such as highly reliable greatly.
Simultaneously in order to meet the requirement of guided missile Portable device, the quality of body during master-plan, to be alleviated from the angle of structural design, thus improve missile performance.From structural design angle, structural material should be reduced as much as possible under the prerequisite meeting structural strength, rigidity or select novel light material to realize the minimizing of Shell body quality.But body wall thickness is optimized this field and developed quite ripe, it is limited that the wall thickness of guided missile each cabin section can reduce leeway, therefore to set about available room for promotion on the one hand at this be not very large.Therefore select relatively light cabin section connected mode that body loss of weight can be made to obtain larger lifting, have larger effect to the lighting realizing guided missile structure.
Therefore adopt the comparatively light radial connected mode of syndeton to obtain axially connect effect thus replace traditional axial connected mode, the quality of syndeton can be reduced, thus the properties of guided missile can be improved, as reduced the requirement to missile power system, increase work range, reduces body volume, improves the handling performance etc. of missile gear, also can increase the total amount that guided missile carries ammunition, improve its battle damage power.
Summary of the invention
1, object: the object of the invention is, in order to provide a kind of missile cabin radial monocline lining bolt fastening structure, installation to be completed more easily the while that its syndeton quality being less, dismounting.
2, technical scheme: in order to realize foregoing invention object, the present invention by the following technical solutions.
A kind of missile cabin of the present invention radial monocline lining bolt fastening structure, it is by cabin section connection box A, cabin section connection box B, sealing ring, tiltedly lining, bolt and anchor locking-nuts with twolug composition, position annexation between them is: anchor locking-nuts with twolug is fixed on section connection box B inner surface ladder hole B position, cabin, sealing ring is placed in the square groove of cabin section connection box A, the inner surface of the join domain of cabin section connection box A and the outer surface of cabin section connection box B join domain are socketed with matched in clearance, and ladder hole A on the two join domain and ladder hole B co-axially align, oblique lining inserts in ladder hole, make the right-angled trapezium groove inclined-plane of the angled end-face of oblique lining and cabin section connection box B outer surface tangent, bolt realizes threaded engagement through oblique lining and anchor locking-nuts with twolug, tight a bolt and make cabin section connection box A and cabin section connection box B compact siro spinning technology.
Described cabin section connection box A is cylindrical structure part, is divided into thin-wall regions and join domain.Join domain is uniform ladder hole A circumferentially, and the number of ladder hole A is relevant with the diameter of cabin section connection box A and structural bearing; First rank of ladder hole A and the diameter of second-order are respectively the diameter of oblique lining first rank and second-order, and the height on the first rank is the height on oblique lining first rank, the little 1 ~ 2mm of height of the aspect ratio oblique lining second-order of second-order.Join domain front inner surface circumferentially opens square groove, is put into wherein by sealing ring during connection.
Described cabin section connection box B is cylindrical structure part, and being divided into thin-wall regions and join domain, is changeover portion between thin-wall regions and join domain.Join domain outer surface circumferentially has right-angled trapezium groove, right-angled trapezium well width is the radius on oblique lining the 3rd rank, the degree of depth is the half of join domain thickness, right-angled trapezium groove hypotenuse and cabin section connection box B axis angulation, and oblique lining angled end-face and oblique busing axis angle complementary angle each other.The corresponding positions coordinated with cabin section connection box A at join domain installs ladder hole B, and the number of ladder hole B is identical with the number of the ladder hole A of cabin section connection box A, and the ladder hole B diameter near join domain outer surface is identical with the diameter of oblique lining second-order.
Described sealing ring is existing matured product, and its dimensions is chosen according to the join domain of cabin section connection box A and the join domain of cabin section connection box B.
Described oblique lining is the three rank ladder barrel shape parts that endoporus is smooth, diameter of bore 1mm larger than the diameter of bolt; Oblique lining is divided into the first rank, second-order and the 3rd rank from big to small by overall diameter, the first rank diameter is 3 times of the diameter of bolt, and the countersunk seat of bolt is opened on top; Second-order diameter is 2.5 times of the diameter of bolt; 3rd rank diameter is 2 times of the diameter of bolt, forms an angled end-face from Section of three end face diameter to second section end face, and the inclined-plane of the right-angled trapezium groove of this angled end-face and cabin section connection box B join domain outer surface cooperatively interacts.
Described bolt is existing matured product, selects the dormant bolt of M5 ~ M12.
Described anchor locking-nuts with twolug is existing matured product, selects the respective model nut of M5 ~ M12 according to bolt specification.
Wherein, cabin section connection box A thin-wall regions thickness is 2 ~ 3mm, and join domain thickness is 4 ~ 6mm.
Wherein, the number value of ladder hole A is generally 8 ~ 24.
Wherein, the transition width of cabin section connection box B is 3 ~ 6mm, and thin-wall regions thickness is 2 ~ 3mm, and join domain thickness is 6 ~ 10mm; Right-angled trapezium groove hypotenuse and cabin section connection box B axis angulation, and oblique lining angled end-face and oblique busing axis angle complementary angle each other, span 30 ~ 60 °; Ladder hole B diameter is identical with the diameter of oblique lining second-order, and its degree of depth is 1 ~ 2mm, near the ladder hole B diameter 1mm larger than the diameter of bolt of join domain inner surface.
Wherein, the height on oblique lining first rank gets 2 ~ 3mm, and the height of second-order gets 4 ~ 6mm; The height on the 3rd rank gets 4 ~ 6mm, forms an angled end-face from Section of three end face diameter to second section end face, and angled end-face and oblique busing axis angle are 30 ~ 60 °.
3, advantage and effect: the new way that a kind of missile cabin of the present invention connects, its major advantage is:
Adopt coordinating of oblique lining angled end-face and right-angled trapezium groove inclined-plane, produce an interaction force vertically by the radial compression each other in sloped contact surface, limit two cabin section displacements vertically.And with oblique lining by compared with the cooperation of upper and lower lining, one aspect of the present invention eliminates lower lining, decrease the processing for coupling assembling, on the other hand owing to being directly open right-angled trapezium groove at cabin section connection box outer surface, ensure that with the mutual extruding force of oblique lining along the axial maximum position of cabin section, and not be used in installation process adopt specific purpose tool to ensure again upper and lower lining appears at the maximum vertically position of extruding component, easy for installation.
This kind of connected mode tightens by radial bolts the displacement constraint realized cabin section axis, therefore the advantage that connected mode has had radial connection concurrently and has axially been connected, also can ensure the reliability of connection while that both syndeton being light.
Accompanying drawing explanation
Fig. 1 is overall structure graphics of the present invention (blast profile)
Fig. 2 is partial structurtes sectional view of the present invention (blast sectional view)
Fig. 3 is cabin section connection box A structure three-dimensional figure of the present invention
Fig. 4 is cabin section connection box B structure three-dimensional figure of the present invention
Fig. 5 is the oblique bush structure graphics of the present invention
In figure, concrete label declaration is as follows:
Detailed description of the invention
Below in conjunction with drawings and Examples, the invention will be further described.
See Fig. 1 and Fig. 2, a kind of missile cabin of the present invention radial monocline lining bolt fastening structure, it is by cabin section connection box A1, cabin section connection box B2, sealing ring 3, oblique lining 4, bolt 5 and anchor locking-nuts with twolug 6 form, position annexation between them is: anchor locking-nuts with twolug 6 is fixed on section connection box B2 inner surface ladder hole 9 position, cabin, sealing ring 3 is placed in the square groove of cabin section connection box A1, the inner surface of the join domain of cabin section connection box A1 and the outer surface of cabin section connection box B2 join domain are socketed with matched in clearance, and ladder hole A7 on the two join domain and ladder hole B9 co-axially align, oblique lining 4 inserts in shoulder hole, make the angled end-face 10 of oblique lining 4 tangent with section connection box B2 outer surface right-angled trapezium groove 8 inclined-plane, cabin, bolt 5 realizes threaded engagement through oblique lining 4 with anchor locking-nuts with twolug 6, tight a bolt and 5 make cabin section connection box A1 and cabin section connection box B2 compact siro spinning technology.
See Fig. 3, described cabin section connection box A1 is cylindrical structure part, and overall diameter is 200mm.Be divided into thin-wall regions and join domain, thin-wall regions thickness is 2mm, and join domain thickness is 5mm.Join domain circumferentially uniform first rank of 12 ladder hole A7, ladder hole A7 and the diameter of second-order is respectively 24mm and 20mm, and the height on the first rank is 2mm, and the height of second-order is 3mm.Join domain front inner surface circumferentially opens the square groove of 2 × 2mm, is put into wherein by sealing ring 3 during connection.
See Fig. 4, described cabin section connection box B2 is cylindrical structure part, and be divided into thin-wall regions and join domain; be changeover portion between thin-wall regions and join domain, thin-wall regions external diameter is 200mm, and thickness is 2mm; join domain external diameter is 190mm, and thickness is 10mm, and transition width is 5mm.Join domain outer surface circumferentially has right-angled trapezium groove 8, right-angled trapezium groove 8 width is 12mm, the degree of depth is 5mm, its hypotenuse and cabin section connection box B2 axis angulation are 60 °, at uniform 12 the ladder hole B9 in relevant position that join domain coordinates with cabin section connection box A, diameter near join domain outer surface ladder hole B9 is 20mm, and the degree of depth is 1mm, and the diameter near join domain inner surface ladder hole B9 is 9mm.
Described sealing ring 3 is existing matured products, and its dimensions is chosen according to the join domain of cabin section connection box A1, cabin section connection box B2, and thickness is 2mm, and internal diameter is 190mm, and external diameter is 194mm.
See Fig. 5, described oblique lining 4 is three rank ladder barrel that endoporus is smooth, and diameter of bore is 9mm, from big to small oblique lining 4 is divided into the first rank, second-order and the 3rd rank by overall diameter, first rank diameter is 3 times of bolt 5 diameter is 24mm, and be highly 2mm, the countersunk seat of bolt 5 is opened on top; Second-order diameter is 2.5 times of bolt 5 diameter is 20mm, is highly 4mm; 3rd rank diameter is 2 times of bolt 5 diameter is 16mm, be highly 4mm, an angled end-face 10 is formed from the 3rd rank end face diameter to second-order end face, angled end-face 10 and oblique lining 4 axis angle are 30 °, and this angled end-face 10 cooperatively interacts with the inclined-plane of the right-angled trapezium groove 8 of cabin section connection box B2 join domain outer surface.
Described bolt 5 is existing matured products, selects the dormant bolt of M8.
Described anchor locking-nuts with twolug 6 is existing matured products, selects the respective model of M8 according to bolt 6 specification.
Installation process of the present invention is as follows:
Anchor locking-nuts with twolug 6 is fixed on the position of cabin section connection box B2 inner surface ladder hole B9 by self structure, the inner surface of the join domain of cabin section connection box A1 and the outer surface of cabin section connection box B2 join domain are socketed with matched in clearance, ensure that the ladder hole A7 on the section connection box A1 of cabin and the ladder hole B9 on the section connection box B2 of cabin corresponds to each other, and seal with sealing ring 3.The ladder hole A7 of oblique lining 4 from cabin section connection box A1 outer surface is put into, adjusting oblique lining 4 makes the angled end-face 10 of oblique lining 4 tangent with the inclined-plane of the circumferential right-angled trapezium groove 8 of cabin section connection box B2 outer surface, in oblique lining 4 centre bore inserting bolt 5, realize threaded engagement with anchor locking-nuts with twolug 6, tighting a bolt 5 makes cabin section connection box A1 and cabin section connection box B2 compact siro spinning technology.
Claims (5)
1. a missile cabin radial monocline lining bolt fastening structure, it is by cabin section connection box A, cabin section connection box B, sealing ring, tiltedly lining, bolt and anchor locking-nuts with twolug composition, anchor locking-nuts with twolug is fixed on section connection box B inner surface ladder hole B position, cabin, sealing ring is placed in the square groove of cabin section connection box A, the inner surface of the join domain of cabin section connection box A and the outer surface of cabin section connection box B join domain are socketed with matched in clearance, and ladder hole A on the two join domain and ladder hole B co-axially align, oblique lining inserts in ladder hole, make the right-angled trapezium groove inclined-plane of the angled end-face of oblique lining and cabin section connection box B outer surface tangent, bolt realizes threaded engagement through oblique lining and anchor locking-nuts with twolug, tight a bolt and make cabin section connection box A and cabin section connection box B compact siro spinning technology,
It is characterized in that: described cabin section connection box A is cylindrical structure part, is divided into thin-wall regions and join domain; Join domain is uniform ladder hole A circumferentially, and the number of ladder hole A is relevant with the diameter of cabin section connection box A and structural bearing; First rank of ladder hole A and the diameter of second-order are respectively the diameter of oblique lining first rank and second-order, and the height on the first rank is the height on oblique lining first rank, the little 1 ~ 2mm of height of the aspect ratio oblique lining second-order of second-order; Join domain front inner surface circumferentially opens square groove, puts into wherein during connection by sealing ring;
Described cabin section connection box B is cylindrical structure part, and being divided into thin-wall regions and join domain, is changeover portion between thin-wall regions and join domain; Join domain outer surface circumferentially has right-angled trapezium groove, right-angled trapezium well width is the radius on oblique lining the 3rd rank, the degree of depth is the half of join domain thickness, right-angled trapezium groove hypotenuse and cabin section connection box B axis angulation, and oblique lining angled end-face and oblique busing axis angle complementary angle each other; The corresponding positions coordinated with cabin section connection box A at join domain installs ladder hole B, and the number of ladder hole B is identical with the number of the ladder hole A of cabin section connection box A, and the ladder hole B diameter near join domain outer surface is identical with the diameter of oblique lining second-order;
Described sealing ring, its dimensions is chosen according to the join domain of cabin section connection box A and the join domain of cabin section connection box B;
Described oblique lining is the three rank ladder barrel shape parts that endoporus is smooth, diameter of bore 1mm larger than the diameter of bolt; Oblique lining is divided into the first rank, second-order and the 3rd rank from big to small by overall diameter, the first rank diameter is 3 times of the diameter of bolt, and the countersunk seat of bolt is opened on top; Second-order diameter is 2.5 times of the diameter of bolt; 3rd rank diameter is 2 times of the diameter of bolt, forms an angled end-face from Section of three end face diameter to second section end face, and the inclined-plane of the right-angled trapezium groove of this angled end-face and cabin section connection box B join domain outer surface cooperatively interacts;
Described bolt is the dormant bolt selecting M5 ~ M12;
Described anchor locking-nuts with twolug is the respective model nut selecting M5 ~ M12.
2. a kind of missile cabin according to claim 1 radial monocline lining bolt fastening structure, is characterized in that: this cabin section connection box A thin-wall regions thickness is 2 ~ 3mm, and join domain thickness is 4 ~ 6mm.
3. a kind of missile cabin according to claim 1 radial monocline lining bolt fastening structure, is characterized in that: the number value of this ladder hole A is generally 8 ~ 24.
4. a kind of missile cabin according to claim 1 radial monocline lining bolt fastening structure, is characterized in that: the transition width of this cabin section connection box B is 3 ~ 6mm, and thin-wall regions thickness is 2 ~ 3mm, and join domain thickness is 6 ~ 10mm; Right-angled trapezium groove hypotenuse and cabin section connection box B axis angulation, and oblique lining angled end-face and oblique busing axis angle complementary angle each other, span 30 ~ 60 °; Ladder hole B diameter is identical with the diameter of oblique lining second-order, and its degree of depth is 1 ~ 2mm, near the ladder hole B diameter 1mm larger than the diameter of bolt of join domain inner surface.
5. a kind of missile cabin according to claim 1 radial monocline lining bolt fastening structure, is characterized in that: the height on these oblique lining first rank gets 2 ~ 3mm, and the height of second-order gets 4 ~ 6mm; The height on the 3rd rank gets 4 ~ 6mm, forms an angled end-face from Section of three end face diameter to second section end face, and angled end-face and oblique busing axis angle are 30 ~ 60 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410015491.7A CN103759597B (en) | 2014-01-14 | 2014-01-14 | Missile cabin radial monoclinic bushing bolt connection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410015491.7A CN103759597B (en) | 2014-01-14 | 2014-01-14 | Missile cabin radial monoclinic bushing bolt connection structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103759597A CN103759597A (en) | 2014-04-30 |
| CN103759597B true CN103759597B (en) | 2015-06-17 |
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| CN201410015491.7A Expired - Fee Related CN103759597B (en) | 2014-01-14 | 2014-01-14 | Missile cabin radial monoclinic bushing bolt connection structure |
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| CN104085526B (en) * | 2014-06-25 | 2016-03-30 | 西北工业大学 | A kind of realize patrolling fly device wing body connect, fixing, locked, unblock integral structure |
| CN104196859A (en) * | 2014-09-17 | 2014-12-10 | 江西洪都航空工业集团有限责任公司 | Limit bolt component for missile launching frames |
| CN104406468B (en) * | 2014-11-21 | 2016-01-06 | 中国空空导弹研究院 | A kind of guided missile and enging cabin section body thereof |
| CN105129069B (en) * | 2015-08-04 | 2017-04-26 | 江西洪都航空工业集团有限责任公司 | Wedge block cabin connecting device |
| CN107458621B (en) * | 2017-06-29 | 2020-03-17 | 成都立航科技股份有限公司 | Missile hanging system of missile |
| CN107664465B (en) * | 2017-08-21 | 2019-06-18 | 中国运载火箭技术研究院 | A kind of guided missile endpiece bottom thermal protection and heat seal structure |
| CN110466801B (en) * | 2019-05-24 | 2021-03-02 | 上海宇航系统工程研究所 | Aircraft cabin structure |
| CN111268058B (en) * | 2020-03-07 | 2022-03-15 | 西北工业大学 | Mechanical connector for cabin section of carbon fiber composite material shell |
| CN111674575B (en) * | 2020-05-26 | 2023-04-18 | 宁波天擎航天科技有限公司 | Cabin section connecting structure and aircraft |
| CN112344808A (en) * | 2020-10-11 | 2021-02-09 | 中国运载火箭技术研究院 | Plug-in structure and cabin section subassembly |
| CN113027254A (en) * | 2021-04-12 | 2021-06-25 | 无锡忻润汽车安全系统有限公司 | Hidden type automobile outer door handle mounting structure and mounting method |
| CN113970276A (en) * | 2021-11-16 | 2022-01-25 | 天津爱思达新材料科技有限公司 | High-strength connecting assembly for carbon fiber composite material |
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| US3781042A (en) * | 1970-09-30 | 1973-12-25 | Raytheon Co | Joint having force converting means |
| EP0898146A2 (en) * | 1997-08-16 | 1999-02-24 | BODENSEEWERK GERÄTETECHNIK GmbH | Connection of two tubular missile body parts |
| CN103075411A (en) * | 2012-12-10 | 2013-05-01 | 江西洪都航空工业集团有限责任公司 | Anti-loosening structure of threaded connection of missile covering cap and missile body |
| CN202964525U (en) * | 2012-11-27 | 2013-06-05 | 凯迈（洛阳）气源有限公司 | Missile bay section connection auxiliary tool |
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2014
- 2014-01-14 CN CN201410015491.7A patent/CN103759597B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3781042A (en) * | 1970-09-30 | 1973-12-25 | Raytheon Co | Joint having force converting means |
| EP0898146A2 (en) * | 1997-08-16 | 1999-02-24 | BODENSEEWERK GERÄTETECHNIK GmbH | Connection of two tubular missile body parts |
| CN202964525U (en) * | 2012-11-27 | 2013-06-05 | 凯迈（洛阳）气源有限公司 | Missile bay section connection auxiliary tool |
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| CN103759597A (en) | 2014-04-30 |
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Granted publication date: 20150617 Termination date: 20170114 |