CN112923807B - Floating type rebounding device suitable for variable-missile-diameter infrared missile air supply mechanism - Google Patents
Floating type rebounding device suitable for variable-missile-diameter infrared missile air supply mechanism Download PDFInfo
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- CN112923807B CN112923807B CN202110206372.XA CN202110206372A CN112923807B CN 112923807 B CN112923807 B CN 112923807B CN 202110206372 A CN202110206372 A CN 202110206372A CN 112923807 B CN112923807 B CN 112923807B
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- air supply
- missile
- supply mechanism
- pressure spring
- supply nozzle
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides a floating type rebounding device suitable for a variable-missile-diameter infrared missile air supply mechanism, which comprises: the protective cover, the pressure spring, the guide sleeve and the gas supply mechanism; safety cover downside fixed connection the uide bushing and with the uide bushing forms the cavity, air feed mechanism is vertical to be passed the safety cover with the uide bushing, air feed mechanism with install between the uide bushing the pressure spring, the pressure spring is installed in the cavity. The floating function of the variable-missile-diameter infrared missile air supply mechanism is realized, and the bearing damage of the structure during transportation, ship-borne and vehicle-mounted duty is avoided.
Description
Technical Field
The invention relates to a rebounding device, in particular to a floating rebounding device suitable for a variable-missile-diameter infrared missile air supply mechanism.
Background
Before the infrared missile is launched, an air supply mechanism on the launching barrel is needed to supply air to the infrared missile for refrigeration. The missile adopts the variable-diameter design to increase the range and the diameter of the engine. The diameter of the guide head cabin of the missile with the variable missile diameter is smaller than that of the engine cabin. In the process of launching the missile, after the air supply mechanism of the launching tube supplies air to the missile seeker and the air supply mechanism is separated from the missile, the missile moves along the shot direction, and the gap between the outer diameter of the missile and the inner diameter of the launching tube is gradually reduced due to the adoption of the variable-missile-diameter design of the missile. The air supply mechanism is required to be capable of timely separating from the missile and recovering to the space outside the inner diameter of the launching tube in the process, so that the space of the launching tube is led out. Under the vibration working conditions of missile transportation, carrier-borne (or vehicle-mounted) duty and the like, the missile can vibrate in a certain amplitude magnitude in the launching tube, and because the air supply structure usually adopts a thin-wall pipeline structure, the missile cannot directly bear the vibration overload, the air supply mechanism is required to have certain floating amount to adapt to the vibration of the missile.
CN108501643A discloses a rebounding device, which can restrain the connecting rod from being pulled out quickly and rebounding quickly, and has a bellows structure.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a floating type rebounding device suitable for an infrared missile air supply mechanism with variable missile diameters.
The invention provides a floating type rebounding device suitable for a variable-missile-diameter infrared missile air supply mechanism, which comprises: the protective cover, the pressure spring, the guide sleeve and the gas supply mechanism;
safety cover downside fixed connection the uide bushing and with the uide bushing forms the cavity, air feed mechanism is vertical to be passed the safety cover with the uide bushing, air feed mechanism with install between the uide bushing the pressure spring, the pressure spring is installed in the cavity.
Preferably, the upper part of the guide sleeve is a hollow cylinder, and the bottom of the hollow cylinder vertically extends outwards to form a first circular ring.
Preferably, the upper portion of the protection cover is provided with a cylindrical cover, the cylindrical cover is hollow, the top end of the cylindrical cover vertically extends inwards to form a second circular ring, and the bottom of the cylindrical cover vertically extends outwards to form a third circular ring.
Preferably, the upper side of the first ring is connected with the lower side of the third ring, and the first ring and the third ring are fixedly connected to the launching tube shell through fixing screws.
Preferably, the gas supply mechanism includes: the air supply nozzle comprises an air guide pipe, an upper cover of the air supply nozzle and an air supply nozzle body, wherein the upper end of the upper cover of the air supply nozzle is connected with the air guide pipe, and the lower end of the upper cover of the air supply nozzle is connected with the air supply nozzle body.
Preferably, the lower end of the upper cover of the air supply nozzle is provided with a skirt, the lower end part of the air supply nozzle body is installed in the missile, and the air supply nozzle body is connected with the outer surface of the missile and is provided with a shear stress groove.
Preferably, the air duct passes the second ring, supply the air cock upper cover to install in the cavity, the shirt rim is installed hollow cylinder top, supply the air cock body to pass hollow cylinder.
Preferably, the compression spring is installed between the skirt edge and the first circular ring, and the compression spring is wound on the outer side of the hollow cylinder.
Preferably, when the air supply nozzle body part is connected in the missile, the skirt presses the compression spring, and the compression spring still has a compression amount.
Preferably, when the missile moves along the shot, the air supply mechanism is disconnected at the shearing stress groove, the pressure spring rebounds, and the air supply nozzle upper cover drives the air supply mechanism to evacuate from the missile under the action of the elastic force of the pressure spring.
Compared with the prior art, the invention has the following beneficial effects:
1. the floating function of the variable-missile-diameter infrared missile air supply mechanism is realized, and the bearing damage of the structure during transportation, ship-borne and vehicle-mounted duty is avoided.
2. When the missile is launched, the air supply mechanism can rebound to give way for the guide-out cylinder channel, so that the interference with the missile is avoided.
3. The device has simple and reliable structure and improves the reliability of the guided missile.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural view of a floating type rebounding device suitable for a variable-missile-diameter infrared missile air supply mechanism;
FIG. 2 is a schematic structural diagram of a floating type rebounding device suitable for a variable-missile-diameter infrared missile air supply mechanism during launching;
FIG. 3 is a front view of the protective cover;
FIG. 4 is a top view of the protective cover;
FIG. 5 is a front view of the guide sleeve;
fig. 6 is a top view of the guide sleeve.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, a floating type rebounding device suitable for a variable-missile diameter infrared missile air supply mechanism comprises: the device comprises a protective cover 1, a pressure spring 2, a guide sleeve 4 and an air supply mechanism 5; the lower side of the protective cover 1 is fixedly connected with the guide sleeve 4 and forms a cavity with the guide sleeve 4, the gas supply mechanism 5 vertically penetrates through the protective cover 1 and the guide sleeve 4, the pressure spring 2 is installed between the gas supply mechanism 5 and the guide sleeve 4, and the pressure spring 2 is installed in the cavity.
As shown in fig. 3 to 6, the upper part of the guide sleeve 4 is a hollow cylinder, and the bottom of the hollow cylinder extends out of the first circular ring vertically; the upper part of the protective cover 1 is provided with a cylindrical cover, the cylindrical cover is hollow, a second circular ring vertically extends inwards from the top end of the cylindrical cover, and a third circular ring vertically extends outwards from the bottom of the cylindrical cover; third ring downside is connected to first ring upside, and first ring and third ring pass through set screw 3 fixed connection on launching tube housing 6.
Specifically, a floating gap is reserved between the guide sleeve 4 and the air supply mechanism 5 in the circumferential direction, the air supply mechanism 5 is continuously compressed in the process of installing the guided missile 7, and the compressed spring 2 still has a compression amount after being installed in place, so that the air supply mechanism 5 can float in the circumferential direction and the vertical direction, and the structural damage of the air supply mechanism caused by vibration load in the guided missile transportation, ship-borne and vehicle-borne duty processes is avoided.
As shown in fig. 2, when the missile 7 is launched, the missile 7 moves along the direction of the jet, the air supply mechanism 5 is broken at the shearing stress groove under the thrust action of the missile 7, the part of the air supply mechanism 5 embedded in the missile 7 moves along with the missile 7, the pressure spring 2 rebounds and pulls the air supply mechanism 5 out of the launching tube, and the missile 7 is led out of the tube channel; in the process, the guide sleeve 4 plays a role in guiding, and the phenomenon that the pressure spring 2 overturns in the rebound process is avoided; after the inner diameter of the launching tube is completely extracted by the gas supply mechanism 5, the protective cover 1 plays a role in recovery, the phenomenon that the gas supply mechanism 5 pops up to influence the work of other equipment of the launching tube is avoided, the separation and rebound processes of the gas supply mechanism 4 are simple and reliable, and the process of popping up the launching tube is not influenced.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (4)
1. The utility model provides a be fit for infrared missile air feed mechanism's of variable bullet footpath floating resilient mounting which characterized in that includes: the device comprises a protective cover (1), a pressure spring (2), a guide sleeve (4) and an air supply mechanism (5);
the lower side of the protective cover (1) is fixedly connected with the guide sleeve (4) and forms a cavity with the guide sleeve (4), the gas supply mechanism (5) vertically penetrates through the protective cover (1) and the guide sleeve (4), the pressure spring (2) is installed between the gas supply mechanism (5) and the guide sleeve (4), and the pressure spring (2) is installed in the cavity;
the upper part of the guide sleeve (4) is a hollow cylinder, and the bottom of the hollow cylinder vertically extends outwards to form a first circular ring;
the upper part of the protective cover (1) is provided with a cylindrical cover, the cylindrical cover is hollow, a second circular ring vertically extends inwards from the top end of the cylindrical cover, and a third circular ring vertically extends outwards from the bottom of the cylindrical cover;
the upper side of the first circular ring is connected with the lower side of the third circular ring, and the first circular ring and the third circular ring are fixedly connected to a launching tube shell (6) through fixing screws (3);
the gas supply mechanism (5) includes: the air supply nozzle comprises an air guide pipe, an upper cover of the air supply nozzle and an air supply nozzle body, wherein the upper end of the upper cover of the air supply nozzle is connected with the air guide pipe, and the lower end of the upper cover of the air supply nozzle is connected with the air supply nozzle body;
the lower end of the upper cover of the air supply nozzle is provided with a skirt edge, the lower end part of the air supply nozzle body is arranged in the missile (7), and the air supply nozzle body is provided with a shear stress groove at the position connected with the outer surface of the missile (7);
the air duct penetrates through the second circular ring, the air supply nozzle upper cover is installed in the cavity, the skirt edge is installed above the hollow cylinder, and the air supply nozzle body penetrates through the hollow cylinder.
2. The floating type rebounding device suitable for the variable-missile diameter infrared missile air supply mechanism is characterized in that: the pressure spring (2) is arranged between the skirt edge and the first circular ring, and the pressure spring (2) surrounds the outer side of the hollow cylinder.
3. The floating type rebounding device suitable for the variable-missile diameter infrared missile air supply mechanism is characterized in that: when the air supply nozzle body part is connected in the missile (7), the skirt presses the pressure spring (2), and the pressure spring (2) still has a compression amount.
4. The floating type rebounding device suitable for the variable-missile diameter infrared missile air supply mechanism is characterized in that: when the missile (7) moves along the direction, the air supply mechanism (5) is disconnected at the shearing stress groove, the pressure spring (2) rebounds, and the air supply nozzle upper cover drives the air supply mechanism (5) to withdraw from the missile (7) under the elastic action of the pressure spring (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110206372.XA CN112923807B (en) | 2021-02-24 | 2021-02-24 | Floating type rebounding device suitable for variable-missile-diameter infrared missile air supply mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110206372.XA CN112923807B (en) | 2021-02-24 | 2021-02-24 | Floating type rebounding device suitable for variable-missile-diameter infrared missile air supply mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN112923807A CN112923807A (en) | 2021-06-08 |
| CN112923807B true CN112923807B (en) | 2023-02-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110206372.XA Active CN112923807B (en) | 2021-02-24 | 2021-02-24 | Floating type rebounding device suitable for variable-missile-diameter infrared missile air supply mechanism |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4291931A (en) * | 1979-02-12 | 1981-09-29 | Bunker Ramo Corporation | Shear plane separable connector |
| USH1069H (en) * | 1991-10-07 | 1992-07-07 | The United States Of America As Represented By The Secretary Of The Army | Self sealing seal |
| US5585596A (en) * | 1993-07-13 | 1996-12-17 | Tracor, Inc. | Thrusting separation system |
| CN201688618U (en) * | 2010-05-18 | 2010-12-29 | 武汉高德红外股份有限公司 | Integrated sterling refrigerating machine |
| CN202709535U (en) * | 2012-02-17 | 2013-01-30 | 武汉高德红外股份有限公司 | Novel integrated Stirling refrigerating machine |
| CN106706136A (en) * | 2016-12-08 | 2017-05-24 | 中国电子科技集团公司第十研究所 | Refrigeration infrared detector |
| CN209386908U (en) * | 2018-11-23 | 2019-09-13 | 江西洪都航空工业集团有限责任公司 | Guided missile lifting lug device |
| CN211626282U (en) * | 2020-01-13 | 2020-10-02 | 西安深瞳智控技术有限公司 | Small-size missile engine separating mechanism |
-
2021
- 2021-02-24 CN CN202110206372.XA patent/CN112923807B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4291931A (en) * | 1979-02-12 | 1981-09-29 | Bunker Ramo Corporation | Shear plane separable connector |
| USH1069H (en) * | 1991-10-07 | 1992-07-07 | The United States Of America As Represented By The Secretary Of The Army | Self sealing seal |
| US5585596A (en) * | 1993-07-13 | 1996-12-17 | Tracor, Inc. | Thrusting separation system |
| CN201688618U (en) * | 2010-05-18 | 2010-12-29 | 武汉高德红外股份有限公司 | Integrated sterling refrigerating machine |
| CN202709535U (en) * | 2012-02-17 | 2013-01-30 | 武汉高德红外股份有限公司 | Novel integrated Stirling refrigerating machine |
| CN106706136A (en) * | 2016-12-08 | 2017-05-24 | 中国电子科技集团公司第十研究所 | Refrigeration infrared detector |
| CN209386908U (en) * | 2018-11-23 | 2019-09-13 | 江西洪都航空工业集团有限责任公司 | Guided missile lifting lug device |
| CN211626282U (en) * | 2020-01-13 | 2020-10-02 | 西安深瞳智控技术有限公司 | Small-size missile engine separating mechanism |
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| CN112923807A (en) | 2021-06-08 |
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