CN102765471A - Wing surface root rib and capsule section longitudinal beam integrated structure of guided missile - Google Patents
Wing surface root rib and capsule section longitudinal beam integrated structure of guided missile Download PDFInfo
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- CN102765471A CN102765471A CN2012102233740A CN201210223374A CN102765471A CN 102765471 A CN102765471 A CN 102765471A CN 2012102233740 A CN2012102233740 A CN 2012102233740A CN 201210223374 A CN201210223374 A CN 201210223374A CN 102765471 A CN102765471 A CN 102765471A
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- guided missile
- missile
- capsule section
- wing surface
- root rib
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Abstract
The invention relates to a wing surface root rib and capsule section longitudinal beam integrated structure of a guided missile. A wing surface root rib is a connecting member of a wing surface framework and a capsule section longitudinal beam of the guided missile; a lapping side of the wing surface root rib is integrated with the longitudinal beam on the capsule section of the guided missile; an outer surface on the lapping side of the wing surface root rib is consistent with an outer surface of the capsule section of the guided missile; an outer end surface of the wing surface root rib is abutted and matched with a connecting surface of the wing surface framework; the wing surface root rib is fixedly connected with a guided missile capsule section framework I and a guided missile capsule section framework II by using rivets; a rear band plate is arranged on the rear edge of the wing surface root rib and is fixedly connected with a guided missile capsule section framework III by using rivets; the wing surface root rib is connected with the guided missile capsule section framework I and the guided missile capsule section framework II; and after the rear band plate is fixedly connected with the guided missile capsule section framework III, a guided missile cover is rived with a guided missile capsule body framework. According to the wing surface root rib and capsule section longitudinal beam integrated structure disclosed by the invention, the design of a capsule section reinforcing frame and a longitudinal beam is reduced, the structural weight is reduced and favorable pneumatic appearance is obtained simultaneously; and the wing surface root rib and capsule section longitudinal beam integrated structure is suitable for the riveted capsule section and is free from being detached after being assembled without influencing storage and transportation and is suitable for guided missiles and small-sized airplanes.
Description
Technical field
The present invention relates to aviation field, particularly a kind of guided missile aerofoil root and cabin section longeron integral structure.
Background technology
At present, on the structure design of guided missile, aerofoil is to separate to make with bomb body, adopts detachable connector to connect between them; But the general form that adopts auricle formula joint, many tenons formula joint, the connecting portion power transmission is concentrated, and needs to arrange very strong reinforced bulkhead at the major joint connecting portion, and structural weight is corresponding bigger.
Summary of the invention
The purpose of this invention is to provide guided missile aerofoil root and cabin section longeron integral structure, prepared missile and the blimp of not dismantling, do not influence accumulating after a kind of the assembling.
The technical scheme that the present invention adopts is: a kind of guided missile aerofoil root and cabin section longeron integral structure comprise missile bay section I frame, missile bay section II frame and missile bay section III frame; Said aerofoil root is the attaching parts of aerofoil skeleton and missile bay longeron; The longeron of the landing edge of aerofoil root and missile bay section constitutes one; The outside face of aerofoil root landing edge is consistent with missile bay section external surface, and the outer face of aerofoil root cooperates with the butt joint of aerofoil skeleton joint face; The aerofoil root is captiveed joint with rivet with missile bay section I frame, missile bay section II frame, and the trailing edge of aerofoil root is the back band plate, and back band plate is captiveed joint with rivet with missile bay section III frame.Said aerofoil root is connected with missile bay section I frame, missile bay section II frame, back band plate be connected with missile bay section III frame fix after, guided missile covering and missile bay body skeleton are riveted.
Beneficial effect of the present invention is: the present invention has adopted guided missile aerofoil root and cabin section longeron integral structure; When section is riveted in the cabin; The aerofoil root serves as cabin section longeron and the cabin section is integrally formed; The connection mode that this kind is new has reduced the design of cabin section reinforced bulkhead and longeron, has alleviated structural weight, has good aerodynamic configuration simultaneously again.The present invention is suitable for the cabin section and takes the version of riveting, and does not dismantle after assembling, and does not influence accumulating, prepared missile and blimp.
Description of drawings
Below in conjunction with accompanying drawing and embodiment the present invention is further specified.
Fig. 1 is a structural representation of the present invention.
The specific embodiment
Embodiment: a kind of guided missile aerofoil root and cabin section longeron integral structure; Comprise missile bay section I frame 1, missile bay section II frame 3 and missile bay section III frame 5; Said aerofoil root 2 is attaching partss of aerofoil skeleton and missile bay longeron, and the longeron of the landing edge of aerofoil root 2 and missile bay section constitutes one, and the landing edge outer rim is apart from missile bay section profile 1.5mm; Landing edge thickness is 4mm; The outside face of landing edge is consistent with missile bay section external surface, and width such as landing edge are 17mm, has guaranteed the riveted joint back gauge with missile bay section longeron and guided missile covering.Consider the operability of aerofoil root parts machining process, guarantee that lap plate is indeformable man-hour adding, the trailing edge landing edge is got length 30mm, also can suitably adjust according to thickness.
The outer face of aerofoil root 2 cooperates with the butt joint of aerofoil skeleton joint face; Aerofoil root 2 is captiveed joint with missile bay section I frame 1, missile bay section II frame 3 usefulness rivets 6, and the trailing edge of aerofoil root 2 is a back band plate 4, and back band plate 4 is captiveed joint with missile bay section III frame 5 usefulness rivets 6.Aerofoil root 2 is connected with missile bay section I frame 1, missile bay section II frame 3, back band plate 4 be connected with missile bay section III frame 5 fix after, guided missile covering and missile bay body skeleton are riveted.
The present invention is suitable for the cabin section and takes the version of riveting, and does not dismantle after assembling, and does not influence accumulating, prepared missile and blimp.
Claims (2)
1. guided missile aerofoil root and cabin section longeron integral structure; Comprise missile bay section I frame (1), missile bay section II frame (3) and missile bay section III frame (5); It is characterized in that: said aerofoil root (2) is the attaching parts of aerofoil skeleton and missile bay longeron; The landing edge of aerofoil root (2) and the longeron of missile bay section constitute one; The outside face of the landing edge of aerofoil root (2) is consistent with missile bay section external surface, and the outer face of aerofoil root (2) cooperates with the butt joint of aerofoil skeleton joint face; Aerofoil root (2) is captiveed joint with rivet (6) with missile bay section I frame (1), missile bay section II frame (3), and the trailing edge of aerofoil root (2) is a back band plate (4), and back band plate (4) is captiveed joint with rivet (6) with missile bay section III frame (5).
2. claim 1 described guided missile aerofoil root and cabin section longeron integral structure; It is characterized in that: said aerofoil root (2) is connected with missile bay section I frame (1), missile bay section II frame (3); Back band plate (4) be connected with missile bay section III frame (5) fix after, guided missile covering and missile bay body skeleton are riveted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210223374.0A CN102765471B (en) | 2012-07-02 | 2012-07-02 | Wing surface root rib and capsule section longitudinal beam integrated structure of guided missile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210223374.0A CN102765471B (en) | 2012-07-02 | 2012-07-02 | Wing surface root rib and capsule section longitudinal beam integrated structure of guided missile |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102765471A true CN102765471A (en) | 2012-11-07 |
| CN102765471B CN102765471B (en) | 2014-07-16 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210223374.0A Active CN102765471B (en) | 2012-07-02 | 2012-07-02 | Wing surface root rib and capsule section longitudinal beam integrated structure of guided missile |
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| Country | Link |
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| CN (1) | CN102765471B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104567561A (en) * | 2013-10-28 | 2015-04-29 | 北京临近空间飞行器系统工程研究所 | Special-shape missile bay section connecting structure for sectional fairing deploying |
| CN112417584A (en) * | 2020-10-10 | 2021-02-26 | 江西洪都航空工业股份有限公司 | Integrated resistance reduction design method for guided missile wire groove and sliding block separation socket |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3908933A (en) * | 1956-06-26 | 1975-09-30 | Us Navy | Guided missile |
| CN87211384U (en) * | 1987-11-16 | 1988-09-14 | 田丰 | Combined guided missille moudle toy |
| JPH1194500A (en) * | 1997-09-26 | 1999-04-09 | Mitsubishi Heavy Ind Ltd | Storage cover separation device of flying object |
| CN1363819A (en) * | 2001-01-09 | 2002-08-14 | 游卫峰 | Technique for integrating disguised surficial modules |
| CN202703884U (en) * | 2012-07-02 | 2013-01-30 | 江西洪都航空工业集团有限责任公司 | Integration structure of missile airfoil rib and cabin longitudinal beam |
-
2012
- 2012-07-02 CN CN201210223374.0A patent/CN102765471B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3908933A (en) * | 1956-06-26 | 1975-09-30 | Us Navy | Guided missile |
| CN87211384U (en) * | 1987-11-16 | 1988-09-14 | 田丰 | Combined guided missille moudle toy |
| JPH1194500A (en) * | 1997-09-26 | 1999-04-09 | Mitsubishi Heavy Ind Ltd | Storage cover separation device of flying object |
| CN1363819A (en) * | 2001-01-09 | 2002-08-14 | 游卫峰 | Technique for integrating disguised surficial modules |
| CN202703884U (en) * | 2012-07-02 | 2013-01-30 | 江西洪都航空工业集团有限责任公司 | Integration structure of missile airfoil rib and cabin longitudinal beam |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104567561A (en) * | 2013-10-28 | 2015-04-29 | 北京临近空间飞行器系统工程研究所 | Special-shape missile bay section connecting structure for sectional fairing deploying |
| CN104567561B (en) * | 2013-10-28 | 2015-12-02 | 北京临近空间飞行器系统工程研究所 | A kind of distinguish that is applicable to throws the special-shaped configuration missile cabin syndeton of covering |
| CN112417584A (en) * | 2020-10-10 | 2021-02-26 | 江西洪都航空工业股份有限公司 | Integrated resistance reduction design method for guided missile wire groove and sliding block separation socket |
| CN112417584B (en) * | 2020-10-10 | 2022-11-18 | 江西洪都航空工业股份有限公司 | Integrated resistance reduction design method for guided missile wire groove and sliding block separation socket |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102765471B (en) | 2014-07-16 |
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