CN104197791A - Crossing folding missile wing mechanism - Google Patents
Crossing folding missile wing mechanism Download PDFInfo
- Publication number
- CN104197791A CN104197791A CN201410471106.XA CN201410471106A CN104197791A CN 104197791 A CN104197791 A CN 104197791A CN 201410471106 A CN201410471106 A CN 201410471106A CN 104197791 A CN104197791 A CN 104197791A
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- missile wing
- gear
- missile
- wing
- output shaft
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Abstract
The invention relates to the field of missile parts, in particular to a crossing folding missile wing mechanism comprising a left missile wing, a right missile wing, a left gear, a right gear and a power output shaft. The left missile wing is mounted on the left gear. The right missile wing is mounted on the right gear. The left gear meshes with the right gear. The left missile wing and the right missile wing are mounted on the respective gears in a mutually staggered manner. The power output shaft drives the right gear to rotate. The crossing folding missile wing mechanism has the advantages that the structure is simple, transmission efficiency is high, and the folding missile wings can extend out more stably and more synchronously.
Description
Technical field
The present invention relates to missile parts field, relate to specifically a kind of cross folding missile wing mechanism.
Background technology
For meeting modern war needs, improve guided missile mobile operations, can higher requirement be proposed transport capacity to guided missile.Under this demand, sophisticated missile design system adopts folding wing more at present, and for improving guided missile maneuverability, left and right missile wing is generally in the symmetrical expansion of same level.In horizontal folding missile wing mechanism missile wing expansion process, launch to put in place after, left and right missile wing lifting force moment balance, missile organization balance, navigability can be good, but larger to folding space requirement.And at present in certain novel stealthy guided missile system of grinding, missile wing lateral dimension is larger, bomb body insufficient space, for improving guided missile Stealth Fighter, overcomes the little problem in the collapsible space of guided missile bomb body, has proposed a kind of cross folding missile wing mechanism in design.For realizing missile wing cross folding, generally adopt dual power source to separate transmission or single-power power source by mechanism's transmission of transferring.Dual power source transmission exists left and right missile wing to open poor synchronization, larger to space requirement; There is complex structure, problem that transmission efficiency is low in existing single power source transmission mechanism.
Summary of the invention
The object of the invention is to address the above problem, a kind of cross folding missile wing mechanism is provided.
In order to realize object of the present invention, the technical solution used in the present invention is:
One cross folding missile wing mechanism, comprise left missile wing, right missile wing, left gear, right gear, power output shaft, left missile wing is arranged on left gear, and right missile wing is arranged on right gear, and left gear engages with right gear, left missile wing and right missile wing mutual dislocation are arranged on gear separately, and power output shaft drives right gear to rotate.
Beneficial effect of the present invention is: simple in structure, transmission efficiency is high, has improved stability and synchronism that folding wing launches.
Brief description of the drawings
Fig. 1 is structural representation of the present invention.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is further described:
Embodiment: referring to Fig. 1.
One cross folding missile wing mechanism, comprise left missile wing 1, right missile wing 2, left gear 3, right gear 4, power output shaft 5, left missile wing 1 is arranged on left gear 3, and right missile wing 2 is arranged on right gear 4, and left gear 3 engages with right gear 4, left missile wing 1 is arranged on gear separately with right missile wing 2 mutual dislocation, and power output shaft 5 drives right gear 4 to rotate.
Specification: the intermeshing rotation of left and right gear, both direction setoff installation is on left and right gear up and down respectively for left and right missile wing, and realization intersection is launched; Increase the tooth height of left and right gear, to overcome because the inclined to one side powershift gear of missile wing connects the additional moment that plane causes; Power output shaft 5 drives right gear 4 to rotate, and right gear drives left gear to rotate, left and right missile wing synchronous expansion thereupon.
What embodiments of the invention were announced is preferred embodiment, but is not limited to this, those of ordinary skill in the art; very easily, according to above-described embodiment, understand spirit of the present invention, and make different amplifications and variation; but only otherwise depart from spirit of the present invention, all in protection scope of the present invention.
Claims (1)
1. a cross folding missile wing mechanism, comprise left missile wing, right missile wing, left gear, right gear, power output shaft, it is characterized in that: left missile wing is arranged on left gear, right missile wing is arranged on right gear, and left gear engages with right gear, left missile wing and right missile wing mutual dislocation are arranged on gear separately, and power output shaft drives right gear to rotate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410471106.XA CN104197791A (en) | 2014-09-17 | 2014-09-17 | Crossing folding missile wing mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410471106.XA CN104197791A (en) | 2014-09-17 | 2014-09-17 | Crossing folding missile wing mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104197791A true CN104197791A (en) | 2014-12-10 |
Family
ID=52083119
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410471106.XA Pending CN104197791A (en) | 2014-09-17 | 2014-09-17 | Crossing folding missile wing mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104197791A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112985675A (en) * | 2021-01-26 | 2021-06-18 | 河北汉光重工有限责任公司 | Folding missile wing torque measuring method |
| CN112985674A (en) * | 2021-01-26 | 2021-06-18 | 河北汉光重工有限责任公司 | Rolling torque measuring method of folding missile wing combination |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001059698A (en) * | 1999-08-19 | 2001-03-06 | Mitsubishi Electric Corp | Unfolding device of wings of flying object |
| US20100264260A1 (en) * | 2009-04-17 | 2010-10-21 | Itt Manufacturing Enterprises, Inc. | Mechanism for folding, sweeping, and locking vehicle wings about a single pivot |
| CN102121512A (en) * | 2010-12-23 | 2011-07-13 | 江西洪都航空工业集团有限责任公司 | Crossing and folding wing transmission device |
| CN103837045A (en) * | 2014-02-24 | 2014-06-04 | 中国航天时代电子公司 | Foldable diamond-shaped missile wing spread system |
| CN103968002A (en) * | 2014-04-18 | 2014-08-06 | 江西洪都航空工业集团有限责任公司 | Missile wing gear transmission folding mechanism |
| CN204085332U (en) * | 2014-09-17 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | A kind of cross folding missile wing mechanism |
-
2014
- 2014-09-17 CN CN201410471106.XA patent/CN104197791A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001059698A (en) * | 1999-08-19 | 2001-03-06 | Mitsubishi Electric Corp | Unfolding device of wings of flying object |
| US20100264260A1 (en) * | 2009-04-17 | 2010-10-21 | Itt Manufacturing Enterprises, Inc. | Mechanism for folding, sweeping, and locking vehicle wings about a single pivot |
| CN102121512A (en) * | 2010-12-23 | 2011-07-13 | 江西洪都航空工业集团有限责任公司 | Crossing and folding wing transmission device |
| CN103837045A (en) * | 2014-02-24 | 2014-06-04 | 中国航天时代电子公司 | Foldable diamond-shaped missile wing spread system |
| CN103968002A (en) * | 2014-04-18 | 2014-08-06 | 江西洪都航空工业集团有限责任公司 | Missile wing gear transmission folding mechanism |
| CN204085332U (en) * | 2014-09-17 | 2015-01-07 | 江西洪都航空工业集团有限责任公司 | A kind of cross folding missile wing mechanism |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112985675A (en) * | 2021-01-26 | 2021-06-18 | 河北汉光重工有限责任公司 | Folding missile wing torque measuring method |
| CN112985674A (en) * | 2021-01-26 | 2021-06-18 | 河北汉光重工有限责任公司 | Rolling torque measuring method of folding missile wing combination |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20141210 |