CN202833603U - Pivot structure for longitudinally folding missile wing - Google Patents
Pivot structure for longitudinally folding missile wing Download PDFInfo
- Publication number
- CN202833603U CN202833603U CN 201220314144 CN201220314144U CN202833603U CN 202833603 U CN202833603 U CN 202833603U CN 201220314144 CN201220314144 CN 201220314144 CN 201220314144 U CN201220314144 U CN 201220314144U CN 202833603 U CN202833603 U CN 202833603U
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- China
- Prior art keywords
- thrust ball
- missile wing
- single direction
- direction thrust
- rotating shaft
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- Expired - Fee Related
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- Pivots And Pivotal Connections (AREA)
- Support Of The Bearing (AREA)
Abstract
The utility model discloses a pivot structure for longitudinally folding a missile wing. A missile wing joint is inserted into a position between an upper cantilever and a lower cantilever of a forked end of a missile wing cross beam in a movable fit mode, same single direction thrust ball bearings are installed in bearing seats respectively, the bearing seats share the same vertical center line and are located above and below the missile wing joint, a copper bush is arranged between the two single direction thrust ball bearings, a rotating shaft is vertically inserted into inner rings of the two ingle direction thrust ball bearings and the copper bush from a matching hole of the upper cantilever of the forked end of the missile wing cross beam, a thread sleeve is arranged on the lower cantilever of the forked end of the missile wing cross beam, the thread sleeve and the rotating shaft share the same vertical center line, an outer diameter of the thread sleeve is larger than those of outer rings of the single direction thrust ball bearings, an outer ring screw thread of the thread sleeve is matched with an inner screw thread of the lower cantilever of the forked end of the missile wing cross beam and abuts against the single direction thrust ball bearings and can adjust the gap between the single direction thrust ball bearings, a center hole of the thread sleeve is sleeved into the lower end of the rotating shaft, and the thread sleeve is connected through a nut which is in a screw-thread fit with the lower end of the rotating shaft. The pivot structure for longitudinally folding the missile wing has the advantages of being compact in structure, reliable in connection, good in sealing performance, small in weight, convenient to disassemble and assemble and fast in unfolding.
Description
Technical field
The utility model relates to military project guided missile field, particularly the longitudinal folding pivot structure of a kind of missile wing.
Background technique
High aspect ratio missile wing transverse dimension is larger, be not easy to guided missile box type storing dress, transportation and on-hook emission etc., the design of general employing folding wing, wherein the folding wing pivot is member the most key in the fold mechanism, mainly bear the aerofoil aerodynamic loading causes in the flight course shearing and moment of flexure, and assurance folding wing mounted resistance is minimum, connection is reliable etc.Tradition folding wing pivot structure mainly contains guide rail grooved, moment bearing, roller bearing guide-track type, single normal pin type etc., and wherein guide rail grooved, moment bearing, roller bearing guide-track type pivot all exist to occupy affects wire and pipe laying, foreign material and enter easily pivot and increase the maintenance work difficulty and affect the shortcomings such as functional reliability than large space.For single normal pin type pivot structure also exist when running shaft bearing be in larger stress, in order to realize that necessary load delivery request missile wing part is thicker, rely on the shortcomings such as larger for the integrity of patrilineal line of descent with only one son in each generation power route.
Summary of the invention
The purpose of this utility model provide a kind of size little, lightweight, launch the rapidly longitudinal folding pivot structure of missile wing.
The technical solution adopted in the utility model is: the pivot structure that a kind of missile wing is longitudinal folding, comprise missile wing crossbeam, Wing Joint, described Wing Joint is inserted between the fork-shaped termination upper cantilever and lower cantalever of missile wing crossbeam movingly, on Wing Joint with in the bearing support of following total same vertical center line, identical single direction thrust ball bearing is housed respectively, is provided with copper bush between two identical single direction thrust ball bearings; The inner ring of rotating shaft and two single direction thrust ball bearings and copper bush movingly; Rotating shaft is from the matching hole vertical inner ring that insert two single direction thrust ball bearings and copper bush of missile wing crossbeam fork-shaped termination upper cantilever with two single direction thrust ball bearings and the total same vertical center line of copper bush; Be provided with and the total same vertical center line of rotating shaft, the external diameter swivel nut greater than the single direction thrust ball bearing outer ring at the fork-shaped termination of missile wing crossbeam lower cantalever, the fork-shaped termination lower cantalever screw-internal thread fit of the outer ring screw thread of swivel nut and missile wing crossbeam, withstand the gap that also can regulate single direction thrust ball bearing; The mesopore of swivel nut is inserted in the rotating shaft lower end, and swivel nut relies on and the nut of rotating shaft lower end screw-thread fit is located by connecting.
The above and below bearing support of described rotating shaft and Wing Joint, two total same vertical center lines of single direction thrust ball bearing, copper bush, swivel nut and nut.The major part of described rotating shaft cooperates with the round concave table rank of missile wing crossbeam fork-shaped termination upper cantilever.Described swivel nut is provided with the plum blossom-shaped bead.
The beneficial effects of the utility model are: member of the present utility model is few, compact structure, take up space less, connect reliable, encapsulation is good, lightweight, easy accessibility, expansion are rapid.
Description of drawings
Below in conjunction with drawings and Examples the utility model is further specified.
Fig. 1 is structural representation of the present utility model.
Among the figure: 1, swivel nut, 2, rotating shaft, 3, Wing Joint, 4, copper bush, 5, nut, 6, single direction thrust ball bearing, 7, the missile wing crossbeam.
Embodiment
Embodiment 1: the pivot structure that a kind of missile wing is longitudinal folding, Wing Joint 3 is inserted between the fork-shaped termination upper cantilever and lower cantalever of missile wing crossbeam 7 movingly, on Wing Joint 3 with in the bearing support of following total same vertical center line, be equipped with respectively between 6, two identical single direction thrust ball bearings 6 of identical single direction thrust ball bearing and be provided with copper bush 4; The inner ring of rotating shaft 2 and two single direction thrust ball bearings 6 and copper bush 4 movingly; Rotating shaft 2 is from the matching hole vertical inner ring that insert two single direction thrust ball bearings 6 and copper bush 4 of missile wing crossbeam 7 fork-shaped termination upper cantilevers with two single direction thrust ball bearings 6 and copper bush 4 total same vertical center lines; Be provided with and the total same vertical center lines of rotating shaft 2, the external diameter swivel nut 1 greater than single direction thrust ball bearing 6 outer rings at the fork-shaped termination of missile wing crossbeam 7 lower cantalever, the fork-shaped termination lower cantalever screw-internal thread fit of the outer ring screw thread of swivel nut 1 and missile wing crossbeam 7, withstand the gap that also can regulate single direction thrust ball bearing 6; The mesopore of swivel nut 1 is inserted in rotating shaft 2 lower ends, and swivel nut 1 relies on and the nut 5 of rotating shaft 2 lower end screw-thread fit is located by connecting.
Described rotating shaft 2 and Wing Joint 3 above and below bearing supports, two single direction thrust ball bearings 6, copper bush 4, swivel nut 1 and nut 5 total same vertical center lines.The major part of described rotating shaft 2 cooperates with the round concave table rank of missile wing crossbeam 7 fork-shaped termination upper cantilevers.Described swivel nut 1 is provided with the plum blossom-shaped bead.
The utility model adopts single direction thrust ball bearing 6, guarantees that missile wing 2 freely rotates around the shaft with the surface friction drag of minimum, realizes the rapid expansion of missile wing, transmits simultaneously the aerofoil aerodynamic loading causes in the missile flight process shearing and moment of flexure.
During assembling, in the bearing support above the Wing Joint of first upper single direction thrust ball bearing 6 being packed into 3, in the rotary shaft hole of the Wing Joint 3 of again copper bush 4 being packed into, between the fork-shaped termination upper cantilever and lower cantalever with above-mentioned member together missile wing crossbeam 7, guarantee the rotary shaft hole alignment simultaneously.The microcephaly of rotating shaft 2 is inserted the inner ring of single direction thrust ball bearing 6 and copper bush 4 from the hole, round concave table rank of missile wing crossbeam 7 fork-shaped termination upper cantilevers, again from the microcephaly of rotating shaft 2 pack into lower unidirectional thrust ball bearing 6 and swivel nut 1; Rotate swivel nut 1, withstand and regulate the gap of single direction thrust ball bearing 6; Tighten subsequently the nut 5 of rotating shaft 2 lower ends.
Claims (3)
1. pivot structure that missile wing is longitudinal folding, comprise missile wing crossbeam (7), Wing Joint (3), it is characterized in that: described Wing Joint (3) is inserted between the fork-shaped termination upper cantilever and lower cantalever of missile wing crossbeam (7) movingly, on Wing Joint (3) with in the bearing support of following total same vertical center line, identical single direction thrust ball bearing (6) is housed respectively, is provided with copper bush (4) between two identical single direction thrust ball bearings (6); The inner ring of rotating shaft (2) and two single direction thrust ball bearings (6) and copper bush (4) movingly; Rotating shaft (2) is from missile wing crossbeam (7) fork-shaped termination upper cantilever and matching hole vertical insertion two single direction thrust ball bearings (6) of two single direction thrust ball bearings (6) and the total same vertical center line of copper bush (4) and the inner ring of copper bush (4); Be provided with and the total same vertical center line of rotating shaft (2), the external diameter swivel nut (1) greater than single direction thrust ball bearing (6) outer ring at the fork-shaped termination of missile wing crossbeam (7) lower cantalever, the fork-shaped termination lower cantalever screw-internal thread fit of the outer ring screw thread of swivel nut (1) and missile wing crossbeam (7), withstand the gap that also can regulate single direction thrust ball bearing (6); The mesopore of swivel nut (1) is inserted in rotating shaft (2) lower end, and swivel nut (1) relies on and the nut (5) of rotating shaft (2) lower end screw-thread fit is located by connecting.
2. the longitudinal folding pivot structure of missile wing as claimed in claim 1 is characterized in that: described rotating shaft (2) and the total same vertical center line of the above and below bearing support of Wing Joint (3), two single direction thrust ball bearings (6), copper bush (4), swivel nut (1) and nut (5).
3. the longitudinal folding pivot structure of missile wing as claimed in claim 1, it is characterized in that: the major part of described rotating shaft (2) cooperates with the round concave table rank of missile wing crossbeam (7) fork-shaped termination upper cantilever.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220314144 CN202833603U (en) | 2012-07-02 | 2012-07-02 | Pivot structure for longitudinally folding missile wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220314144 CN202833603U (en) | 2012-07-02 | 2012-07-02 | Pivot structure for longitudinally folding missile wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202833603U true CN202833603U (en) | 2013-03-27 |
Family
ID=47945316
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220314144 Expired - Fee Related CN202833603U (en) | 2012-07-02 | 2012-07-02 | Pivot structure for longitudinally folding missile wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202833603U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102767560A (en) * | 2012-07-02 | 2012-11-07 | 江西洪都航空工业集团有限责任公司 | Pivot structure with longitudinally-foldable missile swing |
| CN106225604A (en) * | 2016-07-29 | 2016-12-14 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of rudder face |
| CN113251064A (en) * | 2021-06-17 | 2021-08-13 | 中国工程物理研究院总体工程研究所 | Folding pivot means that expandes based on joint bearing |
-
2012
- 2012-07-02 CN CN 201220314144 patent/CN202833603U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102767560A (en) * | 2012-07-02 | 2012-11-07 | 江西洪都航空工业集团有限责任公司 | Pivot structure with longitudinally-foldable missile swing |
| CN102767560B (en) * | 2012-07-02 | 2015-02-25 | 江西洪都航空工业集团有限责任公司 | Pivot structure with longitudinally-foldable missile swing |
| CN106225604A (en) * | 2016-07-29 | 2016-12-14 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of rudder face |
| CN106225604B (en) * | 2016-07-29 | 2018-01-26 | 江西洪都航空工业集团有限责任公司 | A kind of longitudinal folding mechanism of rudder face |
| CN113251064A (en) * | 2021-06-17 | 2021-08-13 | 中国工程物理研究院总体工程研究所 | Folding pivot means that expandes based on joint bearing |
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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: 20140821 |
|
| 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: 20140821 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: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. |
|
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: Jiangxi Hongdu Technology Co., Ltd. Assignor: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000218 Denomination of utility model: Pivot structure with longitudinally-foldable missile swing Granted publication date: 20130327 License type: Exclusive License Record date: 20140724 |
|
| 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: Hongdu Aviation Industry Group Co., td., Jiangxi Prov. Contract record no.: 2014360000218 Date of cancellation: 20141202 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130327 Termination date: 20160702 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |