CN201680764U - Missile launching device - Google Patents
Missile launching device Download PDFInfo
- Publication number
- CN201680764U CN201680764U CN2010202067249U CN201020206724U CN201680764U CN 201680764 U CN201680764 U CN 201680764U CN 2010202067249 U CN2010202067249 U CN 2010202067249U CN 201020206724 U CN201020206724 U CN 201020206724U CN 201680764 U CN201680764 U CN 201680764U
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- CN
- China
- Prior art keywords
- launching device
- corner
- rotating base
- launching
- hydroboom
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Abstract
The utility model relates to a missile launching device, which can solve the problems that a plurality of missiles launched by the existing launching device are mutually parallel and relatively centralized, so that the hit rate of objects is relatively low. The lower end of each launcher of the missile launching device is hinged with a side overturn plate through a corner hinge, an included angle is formed between two adjacent launchers, a corner hydraulic support arm is connected with each launcher, a hydraulic support arm of the side overturn plate is arranged on the side overturn plate, a rotating base is arranged below the side overturn plate, a universal ball is arranged on a launching carrier frame, and the central position of the lower plane of the rotating base is hinged with the universal ball. The missile launching device can enable the missiles launched by the launching device to have the included angles mutually, enable the plurality of the missiles launched by the launching device to be in the shape of a fan, and enable the range of the captured objects to be wide, and thus has the advantages of high hit rate and effects of not only seizing the opportunity for battle, but also effectively killing enemy.
Description
Technical field
The utility model relates to guided missile launcher.
Background technology
At present, many pieces of guided missiles of existing guided missile launcher emission are parallel, more concentrated each other, so the hit rate of target lower (hit rate is about 70%) is promptly bungled the chance of winning a battle, and can not effectively eliminate enemy's problem again.
The utility model content
The utility model is parallel for many pieces of guided missiles that solve existing emitter emission each other, more concentrated, so, the hit rate of target lower (hit rate is about 70%), promptly bungle the chance of winning a battle, can not effectively eliminate enemy's problem again, a kind of guided missile launcher is provided, the concrete technical scheme that addresses the above problem is as follows:
A kind of guided missile launcher of the present utility model, form by launching carrier frame, launching tube, corner hinge, corner hydroboom, rollover flap, rollover flap hydroboom, rotating base and multi-directional ball, the lower end of launching tube is linked by the corner hinge with the rollover flap, between adjacent two launching tubes an angle is arranged, the corner hydroboom is connected with launching tube, rollover flap hydroboom is located on the rollover flap, rotating base is located at the below of rollover flap, multi-directional ball is located on the launching carrier frame, the center of rotating base lower plane and multi-directional ball hinge joint.
A kind of guided missile launcher of the present utility model, many pieces of guided missiles of emitter emission are that an angle is arranged each other, make many pieces of guided missiles of emitter emission be fan-shaped, the scope of pouncing on the target of catching is big, so, shoot straight (hit rate is more than 90%), can catch opportunity of combat, can effectively eliminate enemy's advantage again.It is vehicle-mounted, carrier-borne or airborne that this device is applicable to.
Description of drawings
Fig. 1 is a structural representation of the present utility model.9 is target zone among the figure.
The specific embodiment
The specific embodiment one: describe present embodiment in conjunction with Fig. 1.Present embodiment is by launching carrier frame 1, launching tube 2, corner hinge 3, corner hydroboom 4, rollover flap 5, rollover flap hydroboom 6, rotating base 7 and multi-directional ball 8 are formed, the lower end of launching tube 2 is linked by corner hinge 3 with rollover flap 5, between adjacent two launching tubes 2 angle is arranged, a plurality of corner hydrobooms 4 are connected with each launching tube 2, rollover flap hydroboom 6 is located on the rollover flap 5, rotating base 7 is located at the below of rollover flap 5, multi-directional ball 8 is located on the launching carrier frame 1, the center of rotating base 7 lower planes and multi-directional ball 8 hinge joints, rotating base 7 is rotated by receiving target control.
The specific embodiment two: describe present embodiment in conjunction with Fig. 1.Angle between adjacent two launching tubes 2 of present embodiment is 3 °～10 ° degree.
The specific embodiment three: describe present embodiment in conjunction with Fig. 1.The rotating base 7 of present embodiment is 360 ° of rotations.
Claims (3)
1. guided missile launcher, it is by launching carrier frame (1), launching tube (2), corner hinge (3), corner hydroboom (4), rollover flap (5), rollover flap hydroboom (6), rotating base (7) and multi-directional ball (8) are formed, the lower end that it is characterized in that launching tube (2) is linked by corner hinge (3) with rollover flap (5), between adjacent two launching tubes (2) angle is arranged, corner hydroboom (4) is connected with launching tube (2), rollover flap hydroboom (6) is located on the rollover flap (5), rotating base (7) is located at the below of rollover flap (5), multi-directional ball (8) is located on the launching carrier frame (1), the center of rotating base (7) lower plane and multi-directional ball (8) hinge joint.
2. a kind of guided missile launcher according to claim 1 is characterized in that the angle between adjacent two launching tubes (2) is 3 °～10 ° degree.
3. a kind of guided missile launcher according to claim 1 is characterized in that corner hydroboom (4) is for a plurality of.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202067249U CN201680764U (en) | 2010-05-28 | 2010-05-28 | Missile launching device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202067249U CN201680764U (en) | 2010-05-28 | 2010-05-28 | Missile launching device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201680764U true CN201680764U (en) | 2010-12-22 |
Family
ID=43345805
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010202067249U Expired - Fee Related CN201680764U (en) | 2010-05-28 | 2010-05-28 | Missile launching device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201680764U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104897002A (en) * | 2012-11-05 | 2015-09-09 | 杭州航海仪器有限公司 | Modular common-frame launch device |
| CN105423814A (en) * | 2015-11-01 | 2016-03-23 | 宁波市鄞州发辉机械科技有限公司 | Multifunctional guided missile launching device |
-
2010
- 2010-05-28 CN CN2010202067249U patent/CN201680764U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104897002A (en) * | 2012-11-05 | 2015-09-09 | 杭州航海仪器有限公司 | Modular common-frame launch device |
| CN105423814A (en) * | 2015-11-01 | 2016-03-23 | 宁波市鄞州发辉机械科技有限公司 | Multifunctional guided missile launching device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101222 Termination date: 20120528 |