CN202993998U - Integration structure of missile wing connecting lug grooves and missile body - Google Patents
Integration structure of missile wing connecting lug grooves and missile body Download PDFInfo
- Publication number
- CN202993998U CN202993998U CN 201220683389 CN201220683389U CN202993998U CN 202993998 U CN202993998 U CN 202993998U CN 201220683389 CN201220683389 CN 201220683389 CN 201220683389 U CN201220683389 U CN 201220683389U CN 202993998 U CN202993998 U CN 202993998U
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- China
- Prior art keywords
- missile
- bomb body
- lug grooves
- missile wing
- utility
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- 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.)
- Expired - Lifetime
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Abstract
The utility model discloses an integration structure of missile wing connecting lug grooves and a missile body, and the integration structure adopts a scheme that the missile body and the lug grooves are integrally processed and shaped in a numerical control manner. According to the utility model, the missile wing connecting lug grooves and the missile body are designed to be integrated into a whole, a proper aluminum profile is selected and used, the missile body and the lug grooves are directly processed and produced, a link of assembling is saved, a connecting tooling is accordingly saved, production efficiency is improved and parallel operation is facilitated.
Description
Technical field
The utility model relates to a kind of missile wing engaging lug groove and bomb body fusion structure, belongs to the body structure design field.
Background technology
In the missile flight process, bomb body not only will bear and act on each part quality power on its surperficial mass force of local air power, structure own, bomb body, but also bears the larger concentrfated load that the parts such as missile wing, empennage transmit by anchor tip.The local air power that the bomb body most surfaces is born is less, and roughly symmetrical along bomb body cross section periphery, basically can no longer pass to from balancing each other other parts of bomb body, it is symmetrical that each parts are substantially also pressed the bomb body symmetrical plane, its mass force also can Equilibrium, the mass force less of bomb body structure own appends in each concentrfated load usually.Therefore, analyze the stressing conditions of bomb body, only consider the effect of concentrfated load.The concentrfated load that on bullet, each member transmits, all will be passed at last bomb body and missile wing junction, with the counterweight balance that missile wing transmits, the stressed power transmission form of bomb body missile wing has determined that missile wing and bomb body relative position will guarantee accurately, breaks full missile-borne lotus equilibrium state in order to avoid produce additional moment.
To the miniature missile of thin-wall case, wing body connects the normal ear slot type that adopts and connects.The ear groove is connected with welding with bomb body, the common process method such as rivet, be threaded.The lightweight aluminium that bomb body is selected, most welding performance is bad and postwelding is yielding.With ear groove riveted joint or be screwed onto on bomb body, on bullet, load reaches wing body joint by rivet or screw, because of fixedly tightness is inconsistent, unbalance stress, easily cause the part securing member stressed excessive to wearing and tearing, be out of shape even and rupture.The ear groove is assemblied on bomb body, no matter is which kind of process, even if type frame frock is arranged, also is difficult to guarantee ear groove and bomb body, namely the relative positional accuracy requirement of missile wing and bomb body.
Therefore, need to provide a kind of new technical scheme to solve the problems referred to above.
The utility model content
The purpose of this utility model is to provide a kind of power transmission uniform missile wing engaging lug groove and bomb body fusion structure.
The technical solution adopted in the utility model is:
A kind of missile wing engaging lug groove and bomb body fusion structure, this fusion structure adopts bomb body and the machine-shaping of ear groove direct numerical control one.
The angle of the axis of described ear groove and bomb body axis is A, A=45 ° ± 12'.
Described bomb body adopts aluminium section bar.
The beneficial effects of the utility model: ear groove and bomb body fusion structure, material is continuous, and power transmission is even, direct, and detail rigidity is good, bending resistance is large, bomb body and ear groove are fused into one, and the ear groove exceeds wing not obviously, and aerodynamic configuration is good, increase the missile wing lifting surface, reduce disturbance resistance and wave resistance have been improved the wing and have been carried distribution, make missile wing load can be directly, disperse, be passed to symmetrically wing body joint.
Description of drawings
Fig. 1 is structural representation of the present utility model.
Fig. 2 is along B-B to cutaway view in Fig. 1.
Wherein: 1, bomb body, 2, the ear groove.
The specific embodiment
The utility model is described in further detail below in conjunction with the drawings and specific embodiments.
Following examples only are used for explanation the utility model, are not used for limiting protection domain of the present utility model.
As illustrated in fig. 1 and 2, a kind of missile wing engaging lug groove of the present utility model and bomb body fusion structure, this fusion structure adopts bomb body 1 and the 2 direct numerical control one machine-shapings of ear groove, and bomb body 1 adopts aluminium section bar, the angle of the axis of ear groove 2 and bomb body 1 axis is A, A=45 ° ± 12'.
The ear groove 2 precision positional precision ratio of bomb body 1 axis especially relatively are easier to reach, and also can meet the requirement of missile wing error of fixed angles, are applicable to carry little slim missile wing,
Claims (3)
1. a missile wing engaging lug groove and bomb body fusion structure, it is characterized in that: this fusion structure adopts bomb body and the machine-shaping of ear groove direct numerical control one.
2. a kind of missile wing engaging lug groove according to claim 1 and bomb body fusion structure, it is characterized in that: the angle of the axis of described ear groove and bomb body axis is A, A=45 ° ± 12'.
3. a kind of missile wing engaging lug groove according to claim 1 and bomb body fusion structure, is characterized in that: described bomb body employing aluminium section bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220683389 CN202993998U (en) | 2012-12-12 | 2012-12-12 | Integration structure of missile wing connecting lug grooves and missile body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220683389 CN202993998U (en) | 2012-12-12 | 2012-12-12 | Integration structure of missile wing connecting lug grooves and missile body |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202993998U true CN202993998U (en) | 2013-06-12 |
Family
ID=48565171
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220683389 Expired - Lifetime CN202993998U (en) | 2012-12-12 | 2012-12-12 | Integration structure of missile wing connecting lug grooves and missile body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202993998U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103047908A (en) * | 2012-12-12 | 2013-04-17 | 江西洪都航空工业集团有限责任公司 | Fusion structure of missile wing connection lug channel and missile body |
| CN103569350A (en) * | 2013-11-06 | 2014-02-12 | 中国运载火箭技术研究院 | Initiative missile wing mechanism |
-
2012
- 2012-12-12 CN CN 201220683389 patent/CN202993998U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103047908A (en) * | 2012-12-12 | 2013-04-17 | 江西洪都航空工业集团有限责任公司 | Fusion structure of missile wing connection lug channel and missile body |
| CN103569350A (en) * | 2013-11-06 | 2014-02-12 | 中国运载火箭技术研究院 | Initiative missile wing mechanism |
| CN103569350B (en) * | 2013-11-06 | 2015-07-08 | 中国运载火箭技术研究院 | Initiative missile wing mechanism |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| ASS | Succession or assignment of patent right |
Owner name: JIANGXI HONGDU TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: HONGDU AVIATION INDUSTRY GROUP CO., TD., JIANGXI PROV. Effective date: 20140814 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| COR | Change of bibliographic data |
Free format text: CORRECT: ADDRESS; FROM: 330000 NANCHANG, JIANGXI PROVINCE TO: 330096 NANCHANG, JIANGXI PROVINCE |
|
| TR01 | Transfer of patent right |
Effective date of registration: 20140814 Address after: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee after: Jiangxi Hongdu Technology Co.,Ltd. Address before: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee before: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. |
|
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Technology Co.,Ltd. Assignor: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. Contract record no.: 2014360000190 Denomination of utility model: Fusion structure of missile wing connection lug channel and missile body Granted publication date: 20130612 License type: Exclusive License Record date: 20140714 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| EC01 | Cancellation of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Technology Co.,Ltd. Assignor: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. Contract record no.: 2014360000190 Date of cancellation: 20141202 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20151228 Address after: 330000 Jiangxi city in Nanchang Province, the new bridge box 460 box 5001 Patentee after: JIANGXI HONGDU AVIATION INDUSTRY GROUP Co.,Ltd. Address before: 330096, Nanchang hi tech Zone, Jiangxi Province, No. 59, No. 3, building 3, high tech and low carbon innovation and Pioneering Park Patentee before: Jiangxi Hongdu Technology Co.,Ltd. |
|
| CX01 | Expiry of patent term |
Granted publication date: 20130612 |
|
| CX01 | Expiry of patent term |