CN113091530A - Floating device suitable for infrared missile air supply mechanism - Google Patents
Floating device suitable for infrared missile air supply mechanism Download PDFInfo
- Publication number
- CN113091530A CN113091530A CN202110234310.XA CN202110234310A CN113091530A CN 113091530 A CN113091530 A CN 113091530A CN 202110234310 A CN202110234310 A CN 202110234310A CN 113091530 A CN113091530 A CN 113091530A
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- China
- Prior art keywords
- limiting ring
- supply mechanism
- cylinder
- air supply
- vertical
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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.)
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Classifications
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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
- F42B15/34—Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/30—Use of alternative fuels, e.g. biofuels
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Aviation & Aerospace Engineering (AREA)
- Combustion & Propulsion (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention provides a floating device suitable for an infrared missile air supply mechanism, which comprises a circumferential limiting ring 1 and a vertical limiting ring 2; the circumferential limiting ring 1 and the vertical limiting ring 2 are sequentially coaxially connected and sleeved on the cylindrical gas supply mechanism 4, and the circumferential limiting ring 1 and the vertical limiting ring 2 are both arranged inside the launch barrel shell 5; there is the circumference clearance between circumference spacing ring 1 and the air feed mechanism 4, there is the axial clearance between circumference spacing ring 1 and the vertical spacing ring 2, air feed mechanism 4 is last along radially being provided with the journal stirrup, and the journal stirrup is located inside the axial clearance. The invention realizes the floating connection of the air supply mechanism and the shell of the launching barrel, ensures that the air supply mechanism does not bear under the working conditions of missile transportation, ship-borne (or vehicle-mounted) duty and the like, improves the reliability of products, ensures that the air supply mechanism is reliably separated when the missile is launched, and ensures that the part positioned outside the missile does not interfere with the guide ejecting barrel.
Description
Technical Field
The invention relates to the technical field of missile launching, in particular to a floating device suitable for an infrared missile air supply mechanism.
Background
Before the guided missile adopting the infrared guidance mode is launched, a gas supply mechanism of a launching barrel is required to provide high-pressure gas to refrigerate a seeker. However, under 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 of the missile. Therefore, the air supply mechanism is required to have a certain floating amount to adapt to the vibration of the missile.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a floating device suitable for an infrared missile air supply mechanism.
The floating device suitable for the infrared missile air supply mechanism comprises a circumferential limiting ring and a vertical limiting ring;
the circumferential limiting ring and the vertical limiting ring are sequentially coaxially connected and sleeved on the cylindrical gas supply mechanism, and are arranged inside the launching barrel shell;
there is the circumference clearance between circumference spacing ring and the air feed mechanism, there is axial clearance between circumference spacing ring and the vertical spacing ring, air feed mechanism is last along radially being provided with the journal stirrup, and the journal stirrup is located inside the axial clearance.
Preferably, the inner diameter of the circumferential limiting ring is larger than the outer diameter of the gas supply mechanism.
Preferably, the inner diameter of the circumferential limiting ring is matched with the inner diameter of the vertical limiting ring.
Preferably, the circumferential limiting ring comprises a first cylinder and a second cylinder, and the inner diameter of the first cylinder is smaller than that of the second cylinder;
the first cylinder is coaxially connected with the second cylinder, and the second cylinder is connected with the vertical limiting ring.
Preferably, the inner diameter of the second cylinder is larger than the outer diameter of the gas supply mechanism plus the radial length of the support lug;
the inner diameter of the first cylinder is smaller than the size of the outer diameter of the air supply mechanism plus the radial length of the support lug;
an axial gap is formed between part of the bottom surface of the first cylinder and the top surface of the vertical limiting ring, and the support lug is positioned in the axial gap.
Preferably, the outer diameters of the circumferential limiting ring and the vertical limiting ring are matched with the inner diameter of the launching barrel shell.
Preferably, a fine tuning pad is further included;
the fine tuning gasket is arranged on one surface, which is not contacted with the circumferential limiting ring, of the vertical limiting ring, is coaxially connected with the vertical limiting ring and is sleeved on the gas supply mechanism, and the fine tuning gasket is arranged inside the transmitting cylinder shell.
Preferably, the fine tuning shim comprises a rubber shim.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention has simple structure and convenient operation, realizes the floating connection of the gas supply mechanism and the launching tube shell, ensures that the gas supply mechanism is not carried under the working conditions of missile transportation, ship-borne (or vehicle-borne) duty and the like, and improves the reliability of the product.
2. The invention adopts the technical means that the support lug of the air supply mechanism is arranged in the axial gap between the circumferential limiting ring and the vertical limiting ring, so that the reliable separation of the air supply mechanism is ensured when the guided missile is launched, and the part positioned outside the guided missile cannot interfere with the guide ejection cylinder.
3. The invention adopts the technical means of arranging the fine adjustment gasket at one side of the vertical limiting ring, can reduce the abrasion of the vertical limiting ring, and can change the axial clearance by adjusting the fine adjustment gasket.
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 the present invention;
FIG. 2 is a schematic cross-sectional view of a circumferential stop collar of the present invention;
FIG. 3 is a schematic top view of the circumferential retaining ring of the present invention;
FIG. 4 is a schematic cross-sectional view of a vertical stop collar of the present invention;
FIG. 5 is a schematic cross-sectional view of a trim pad of the present invention;
FIG. 6 is a schematic structural diagram of an air supply mechanism during missile launching.
The figures show that:
air supply mechanism 4 of circumferential limiting ring 1
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.
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 invention discloses a floating device suitable for an infrared missile air supply mechanism, which comprises a circumferential limiting ring 1 and a vertical limiting ring 2; the circumferential limiting ring 1 and the vertical limiting ring 2 are sequentially coaxially connected and sleeved on the cylindrical gas supply mechanism 4, and the circumferential limiting ring 1 and the vertical limiting ring 2 are both arranged inside the launch barrel shell 5; there is the circumference clearance between circumference spacing ring 1 and the air feed mechanism 4, there is the axial clearance between circumference spacing ring 1 and the vertical spacing ring 2, air feed mechanism 4 is last along radially being provided with the journal stirrup, and the journal stirrup is located inside the axial clearance.
Because the air supply mechanism 4 is arranged on the missile 6, the air supply mechanism 4 can generate circumferential displacement and vertical displacement along with the vibration of the missile 6, and the circumferential gap and the axial gap reserved by the invention meet the circumferential displacement and the axial displacement of the air supply mechanism 4.
In the launching process of the missile 6, the gas supply mechanism 4 is sheared and broken along the stress groove of the missile so as to be divided into an upper part and a lower part, the lower part embedded in the missile 6 is launched away from the barrel together with the missile 6, and the upper part is supported on the vertical limiting ring 2 by virtue of the support lug so as not to interfere the barrel leaving process of the missile 6.
As shown in FIG. 1, the fine tuning shim 3 is made of compressible non-metallic material and is used for fine tuning the axial clearance between the gas supply device 4 and the vertical spacing ring 2. After the fine adjustment gasket 3 and the vertical limiting ring 2 are installed on the launching tube shell 5, the gas supply mechanism 4 is connected with the missile 6, the circumferential limiting ring 1 is screwed in the threaded hole of the launching tube shell 5, and the vertical floating gap between the gas supply mechanism 4 and the vertical limiting ring 2 is adjusted by adjusting the threaded screwing depth of the circumferential limiting ring 1 according to needs. Wherein, the inner hole of the circumferential spacing ring 1 is larger than the support lug of the air supply mechanism 4, and a circumferential gap is formed. When the guided missile 6 vibrates, the air supply mechanism 4 vibrates along with the guided missile 6 and has circumferential displacement and vertical displacement, and the vertical gap and the circumferential gap provided by the floating device meet the displacement of the air supply mechanism in all directions, so that the influence on the cooling effect of the guided missile due to structural damage caused by bearing force of the air supply mechanism is avoided.
As shown in figure 2, when the missile 6 is launched, the missile 8 moves along the shot direction, the air supply mechanism 4 is broken off at the stress groove under the thrust action of the missile 8, the part of the air supply mechanism 4 embedded in the missile 8 and the sealing ring 7 are left in the missile 8, and the rest part of the air supply mechanism 4 is intercepted in the launching tube by the vertical limiting ring 2. The separation process of the gas supply mechanism 4 is simple and reliable, and the process of ejecting the gas supply mechanism out of the cylinder is not influenced.
The internal diameter of circumference spacing ring 1 is greater than the external diameter of air feed mechanism 4, the internal diameter of circumference spacing ring 1 matches with the internal diameter of vertical spacing ring 2.
The circumferential limiting ring 1 comprises a first cylinder and a second cylinder, and the inner diameter of the first cylinder is smaller than that of the second cylinder; the first cylinder is coaxially connected with the second cylinder, and the second cylinder is connected with the vertical limiting ring 2; the inner diameter of the second cylinder is larger than the size of the outer diameter of the gas supply mechanism 4 plus the radial length of the support lug; the inner diameter of the first cylinder is smaller than the size of the outer diameter of the gas supply mechanism 4 plus the radial length of the support lug; an axial gap is formed between part of the bottom surface of the first cylinder and the top surface of the vertical limiting ring 2, and the support lug is positioned in the axial gap.
The outer diameters of the circumferential limiting ring 1 and the vertical limiting ring 2 are matched with the inner diameter of the launching tube shell 5.
The floating device suitable for the infrared missile air supply mechanism further comprises a fine adjustment gasket 3; the fine tuning gasket 3 is arranged on one surface of the vertical limiting ring 2 which is not contacted with the circumferential limiting ring 1, the fine tuning gasket 3 is coaxially connected with the vertical limiting ring 2 and sleeved on the gas supply mechanism 4, and the fine tuning gasket 3 is arranged inside the launching tube shell 5; the fine tuning pad 3 comprises a rubber pad, and preferably, the fine tuning pad 3 is made of elastic rubber and is molded through a die, and has a compressible characteristic.
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 (8)
1. A floating device suitable for an infrared missile air supply mechanism is characterized by comprising a circumferential limiting ring (1) and a vertical limiting ring (2);
the circumferential limiting ring (1) and the vertical limiting ring (2) are sequentially coaxially connected and sleeved on the cylindrical gas supply mechanism (4), and the circumferential limiting ring (1) and the vertical limiting ring (2) are arranged inside the launching tube shell (5);
there is the circumference clearance between circumference spacing ring (1) and air feed mechanism (4), there is the axial clearance between circumference spacing ring (1) and vertical spacing ring (2), air feed mechanism (4) are gone up and are radially provided with the journal stirrup, and the journal stirrup is located inside the axial clearance.
2. The floating device for the infrared missile air supply mechanism is characterized in that the inner diameter of the circumferential limiting ring (1) is larger than the outer diameter of the air supply mechanism (4).
3. The floating device for the infrared missile gas supply mechanism according to claim 1, wherein the inner diameter of the circumferential limiting ring (1) is matched with the inner diameter of the vertical limiting ring (2).
4. The floating device suitable for the infrared missile gas supply mechanism according to claim 1, wherein the circumferential limit ring (1) comprises a first cylinder and a second cylinder, and the inner diameter of the first cylinder is smaller than that of the second cylinder;
the first cylinder is coaxially connected with the second cylinder, and the second cylinder is connected with the vertical limiting ring (2).
5. A float device for use with an infrared missile supply means as claimed in claim 4, characterised in that the second cylinder has an internal diameter greater than the external diameter of the supply means (4) plus the radial length of the lugs;
the inner diameter of the first cylinder is smaller than the size of the outer diameter of the gas supply mechanism (4) plus the radial length of the support lug;
an axial gap is formed between part of the bottom surface of the first cylinder and the top surface of the vertical limiting ring (2), and the support lug is positioned in the axial gap.
6. The floating device for the infrared missile gas supply mechanism according to claim 1, wherein the outer diameters of the circumferential limiting ring (1) and the vertical limiting ring (2) are matched with the inner diameter of the launching tube shell (5).
7. The float device for an infrared missile air supply mechanism according to claim 1, further comprising a fine tuning shim (3);
fine setting gasket (3) set up in vertical spacing ring (2) the one side that does not contact circumference spacing ring (1), fine setting gasket (3) and vertical spacing ring (2) coaxial coupling and cover on air feed mechanism (4), fine setting gasket (3) set up the inside at launching tube casing (5).
8. The float device for an infrared missile air supply mechanism as claimed in claim 7, wherein the fine tuning pad (3) comprises a rubber pad.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110234310.XA CN113091530B (en) | 2021-03-03 | 2021-03-03 | Floating device suitable for infrared missile air feed mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110234310.XA CN113091530B (en) | 2021-03-03 | 2021-03-03 | Floating device suitable for infrared missile air feed mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113091530A true CN113091530A (en) | 2021-07-09 |
| CN113091530B CN113091530B (en) | 2023-03-14 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110234310.XA Active CN113091530B (en) | 2021-03-03 | 2021-03-03 | Floating device suitable for infrared missile air feed mechanism |
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| Country | Link |
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| CN (1) | CN113091530B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005288610A (en) * | 2004-03-31 | 2005-10-20 | Shin Caterpillar Mitsubishi Ltd | Position sensing method and device and positioning device |
| WO2013142418A1 (en) * | 2012-03-23 | 2013-09-26 | Bitzer Kühlmaschinenbau Gmbh | Floating scroll seal with retaining ring |
| CN104864115A (en) * | 2015-04-28 | 2015-08-26 | 宁波世亚燃气仪表管件有限公司 | Anti-theft ball valve |
| CN105953647A (en) * | 2016-04-29 | 2016-09-21 | 上海机电工程研究所 | Floating device of plugging and unplugging mechanism of launcher container electric plug |
| CN111426242A (en) * | 2020-04-14 | 2020-07-17 | 上海机电工程研究所 | Guided missile fixing mechanism |
-
2021
- 2021-03-03 CN CN202110234310.XA patent/CN113091530B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005288610A (en) * | 2004-03-31 | 2005-10-20 | Shin Caterpillar Mitsubishi Ltd | Position sensing method and device and positioning device |
| WO2013142418A1 (en) * | 2012-03-23 | 2013-09-26 | Bitzer Kühlmaschinenbau Gmbh | Floating scroll seal with retaining ring |
| CN104864115A (en) * | 2015-04-28 | 2015-08-26 | 宁波世亚燃气仪表管件有限公司 | Anti-theft ball valve |
| CN105953647A (en) * | 2016-04-29 | 2016-09-21 | 上海机电工程研究所 | Floating device of plugging and unplugging mechanism of launcher container electric plug |
| CN111426242A (en) * | 2020-04-14 | 2020-07-17 | 上海机电工程研究所 | Guided missile fixing mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113091530B (en) | 2023-03-14 |
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