CN110595276A - Gas flow self-discharging structure suitable for missile launcher - Google Patents
Gas flow self-discharging structure suitable for missile launcher Download PDFInfo
- Publication number
- CN110595276A CN110595276A CN201910877314.2A CN201910877314A CN110595276A CN 110595276 A CN110595276 A CN 110595276A CN 201910877314 A CN201910877314 A CN 201910877314A CN 110595276 A CN110595276 A CN 110595276A
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- Prior art keywords
- gas flow
- missile
- guide plate
- gas
- gas channel
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Classifications
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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
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
Abstract
The invention provides a gas flow autonomous discharge structure suitable for a missile launcher, which comprises an inner barrel (10), an outer barrel (20), a fixed guide plate (30) and a movable guide plate (40), wherein a first gas channel (11) and a second gas channel (21) are arranged among the fixed guide plate (30), the inner barrel (10) and the outer barrel (20). By arranging the fixed guide plate (30), the gas flow (50) is discharged from the second gas channel (21) before and is changed into the gas flow discharged from the first gas channel (11) and the second gas channel (21), so that the space between the missile (60) and the inner barrel (10) is effectively utilized, the gas flow (50) is effectively discharged and guided, the missile (60) is prevented from being ablated, the gas flow (50) discharged from the second gas channel (21) is reduced, the overall design size of the missile launcher is reduced, and the space adaptability of the missile launcher is enhanced.
Description
Technical Field
The invention relates to the technical field of missile launching of weapon equipment systems, in particular to a gas flow autonomous emission structure suitable for a missile launching barrel.
Background
The independent gas self-discharging launching mode is adopted as a core technology for launching the medium-and-long-range tactical missile, and the independent gas self-discharging launching mode is increasingly emphasized by all countries in the world. However, in practical use, the missile generally has wing surfaces and air rudders, so that the inner cylinder body is overlarge, and the diversion space is compressed under the condition that the integral size of the self-emission launching cylinder is limited, which is not beneficial to the emission and the diversion of fuel gas.
Therefore, the industry needs a novel gas flow autonomous emission structure, can carry out make full use of the space between guided missile and the interior barrel, improves gas drainage efficiency, reduces the clearance between the interior and exterior barrel, reduces the overall size of launch canister. Patent document CN105865262B discloses an ablation prevention method for the inner surface of a composite material launch canister and a launch canister applying the method. The method aims to provide the anti-ablation method for the inner surface of the launching tube and the launching tube applying the method, which can improve the reuse times of the composite material launching tube and reduce the launching cost. The method for preventing the ablation of the inner surface of the launching tube comprises the following steps: when the missile is launched, the gas flow washes the speed of the inner cylinder wall of the launching cylinder, and the inner cylinder wall of the launching cylinder is divided into different areas: a mild ablation zone 3, a moderate ablation zone 2, and a severe ablation zone 1; arranging a high-temperature curing fabric lining layer on the inner surface of the whole launching tube; arranging a resin-rich layer on the inner side of the lining layer in the moderate ablation area; and spraying an anti-ablation coating on the inner side of the lining layer in the severe ablation area. But the design still does not fundamentally solve the problems of low gas discharge and guide efficiency and the overall size of the launching tube.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a gas flow self-discharging structure suitable for a missile launcher.
The invention provides a gas flow self-discharging structure suitable for a missile launcher, which comprises an inner barrel body 10, an outer barrel body 20, a fixed guide plate 30 and a movable guide plate 40;
a fixed guide plate 30 is arranged inside the inner cylinder 10;
the inner cylinder 10 and the fixed guide plate 30 form a first gas channel 11;
a second gas channel 21 is formed between the inner cylinder 10 and the outer cylinder 20;
a gap 12 is arranged at the mouth end of the inner cylinder 10;
the gap 12 is blocked by the movable guide plate 40, one end of the movable guide plate 40 extends to the second gas channel 21 and contacts the outer cylinder 20, and the other end of the movable guide plate 40 extends to the first gas channel 11 and is connected with the inner cylinder 10 in a sliding way;
when the gas flow 50 is discharged, the gas flow 50 drives the movable baffle 40 to slide close to the cylinder end, and at the same time, the gas flow 50 in the first gas passage 11 is discharged through the second gas passage 21 through the notch 12.
Preferably, the missile 60 is installed inside the inner cylinder 10;
the fixed guide plate 30 is arranged in a clearance with the guided missile 60.
Preferably, a support plate 22 is disposed between the inner cylinder 10 and the outer cylinder 20.
Preferably, the number of the fixed baffles 30 is plural;
the number of notches 12 matches the number of fixed baffles 30.
Preferably, the movable baffle 40 comprises an inner closing plate 41, an outer closing plate 42 and a middle section 44;
the inner closing plate 41, the middle section 44 and the outer closing plate 42 are integrally connected in sequence.
Preferably, the cross section of the first gas channel 11 is shaped as a sector ring.
Preferably, a support bracket 31;
the support bracket 31 is mounted on the fixed baffle 30;
the support bracket 31 supports the missile 60.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the invention, the fixed guide plate 30 is arranged, so that the gas flow 50 is discharged from the second gas channel 21 before and is discharged from the first gas channel 11 and the second gas channel 21, on one hand, the space between the missile 60 and the inner cylinder 10 is effectively utilized, the gas flow 50 is effectively discharged, and the missile 60 is prevented from being ablated by the gas flow 50; on the other hand, a large amount of fuel gas flow 50 is discharged from the first fuel gas passage 11, so that the fuel gas flow 50 discharged from the second fuel gas passage 21 is reduced, and therefore, the outer cylinder 20 can be designed to be reduced in size, so that the overall external dimension of the missile launcher is reduced, and the spatial adaptability of the missile launcher is enhanced.
2. The section of the fixed guide plate 30 is set to be in a fan-shaped ring shape, so that the space inside the inner cylinder 10 is effectively utilized, more fuel gas flows 50 are discharged from the first fuel gas channel 11, and the reduction of the overall design size of the outer cylinder 20 is facilitated.
3. The support bracket 31 is arranged on the fixed guide plate 30 to support the guided missile 60, so that the friction between the guided missile 60 and the inner cylinder 10 and the fixed guide plate 30 during launching can be reduced, and the support and protection effects are achieved.
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 view of the configuration of the gas stream 50 discharge of the present invention;
FIG. 3 is a schematic transverse cross-sectional view of the present invention;
FIG. 4 is a transverse cross-sectional schematic view of missile 60;
fig. 5 is a schematic cross-sectional view of the fixed deflector 30 along the radial direction of the missile launcher.
Shown in the drawings
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.
According to the invention, as shown in fig. 1, the self-discharging structure of the fuel gas flow suitable for the missile launcher comprises an inner cylinder 10, an outer cylinder 20, a fixed guide plate 30 and a movable guide plate 40, wherein the fixed guide plate 30 is arranged inside the inner cylinder 10, the inner cylinder 10 and the fixed guide plate 30 form a first fuel gas channel 11, a second fuel gas channel 21 is formed between the inner cylinder 10 and the outer cylinder 20, a notch 12 is arranged at the cylinder opening end of the inner cylinder 10, the movable guide plate 40 blocks the notch 12, one end of the movable guide plate 40 extends to the second fuel gas channel 21 and contacts with the outer cylinder 20, the other end of the movable guide plate 40 extends to the first fuel gas channel 11 and is connected with the inner cylinder 10 in a sliding manner, when the gas flow 50 is discharged, the gas flow 50 drives the movable baffle 40 to slide close to the cylinder end, and at the same time, the gas flow 50 in the first gas passage 11 is discharged through the second gas passage 21 through the notch 12. In a preferred embodiment, as shown in fig. 5, a missile 60 is installed inside the inner cylinder 10, a plurality of fins 61 are installed on the missile 60, a fixed baffle 30 is arranged between two adjacent fins 61, the missile 60 and the inner cylinder 10, a gap is arranged between the fixed baffle 30 and the missile 60, and by arranging the fixed baffle 30, the gas flow 50 is discharged from the previous second gas passage 21 and is changed into a gas flow discharged from the first gas passage 11 and the second gas passage 21, on one hand, the space between the missile 60 and the inner cylinder 10 is effectively utilized, which is beneficial to effective discharge of the gas flow 50 and prevents the gas flow 50 from ablating the missile 60; on the other hand, a large amount of fuel gas flow 50 is discharged from the first fuel gas passage 11, so that the fuel gas flow 50 discharged from the second fuel gas passage 21 is reduced, and therefore, the missile launcher with the fixed guide plate 30 added thereto can reduce the size of the outer cylinder 20, thereby reducing the overall external dimension of the missile launcher and enhancing the space adaptability of the missile launcher.
Further, as shown in fig. 1, the movable baffle 40 is connected with the inner cylinder 10 in a sliding manner; in a preferred embodiment, the movable diversion plate 40 includes an inner closing plate 41, an outer closing plate 42 and an intermediate section 44, the inner closing plate 41, the intermediate section 44 and the outer closing plate 42 are sequentially and integrally connected, the intermediate section 44 is installed at the notch 12, the inner closing plate 41 and the outer closing plate 42 respectively block the openings of the first gas passage 11 and the second gas passage 21, a spring assembly is arranged at the connection between the inner closing plate 41 and the inner cylinder 10, when the gas flow 50 pushes the movable diversion plate 40, one end of the inner closing plate 41 of the movable diversion plate 40 slides along the inner cylinder 10, and at this time, the first gas passage 11, the notch 12 and the second gas passage 21 are all opened; after the gas flow 50 is discharged, the movable guide plate 40 returns to the initial position under the action of the spring assembly and blocks the first gas channel 11, the gap 12 and the second gas channel 21; in a variation, the movable flow guiding plate 40 is connected to the inner cylinder 10 through the shear bolt 43, when a large amount of gas flow 50 respectively flows towards the cylinder opening end through the first gas passage 11 and the second gas passage 21, the pressure of the gas flow 50 respectively acts on the inner closing plate 41 and the outer closing plate 42 on the movable flow guiding plate 40, and the instantaneous large thrust causes the shear bolt 43 to be inferred, so that the movable flow guiding plate 40 is integrally pushed to slide towards the cylinder opening end, and the discharge of the gas flow 50 is realized.
Specifically, the number of the fixed guide plates 30 is plural, and in a preferred example, in order to fully utilize the space between the missile 60 and the inner cylinder 10, the number of the fixed guide plates 30 is set to 4, as shown in fig. 5, the section of the fixed guide plate 30 is in a sector ring shape, and the fixed guide plate 30 is arranged between the inner cylinder 10 and the missile 60 and integrally connected with the inner cylinder 10; in a variation, the cross-section of the fixed baffle 30 is shaped as in fig. 3, and the fixed baffle 30 is welded to the inner cylinder 10. The number and shape of the fixed baffles 30, based on the full use of the space between the missile 60 and the inner barrel 10, eventually enables more gas flow 50 to be discharged from the first gas passage 11, thus allowing the overall size of the outer barrel 20 to be designed smaller.
Specifically, as shown in fig. 3, a support plate 22 is disposed between the inner cylinder 10 and the outer cylinder 20, and in a preferred embodiment, 4 groups of support plates 22 are disposed between the inner cylinder 10 and the outer cylinder 20, each group having 2 support plates 22; in one variation, the support plates 22 between the inner cylinder 10 and the outer cylinder 20 are provided in 3 sets of 2 support plates 22; the rigid support plates 22 are arranged between the inner barrel 10 and the outer barrel 20, so that the inner barrel 10 and the outer barrel 20 can be effectively fastened, the firmness of the whole missile launching barrel can be ensured, and the effect of firm support during launching of the missile 60 can be achieved.
Further, the missile launcher also comprises a support bracket 31, as shown in fig. 3, the support bracket 31 is mounted on the fixed deflector 30, the support bracket 31 supports the missile 60, and the missile 60 mounted on the inner cylinder 10 is effectively supported by mounting the support bracket 31, so that friction between the missile 60 and the inner cylinder 10 and the fixed deflector 30 during launching is reduced, and the support and protection effects are achieved.
The working principle of the invention is as follows:
as shown in fig. 1, the cross-sections of the inner cylinder 10 and the outer cylinder 20 are concentric circles, the missile 60 is installed inside the inner cylinder 10, as shown in fig. 4, the missile 60 is provided with fins 61, the shell of the missile 60, two adjacent fins 61 and the inner cylinder 10 form a first installation space 13, as shown in fig. 3, a fixed deflector 30 is installed in the first installation space 13, the shape and size of the fixed baffle 30 are reasonably selected according to the space size of the first installation space 13, the larger gas flow 50 exhaust space is formed between the fixed guide plate 30 and the inner cylinder 10, so that on one hand, the damage of the gas flow 50 to the missile 60 can be avoided, on the other hand, the whole gas flow 50 is prevented from being discharged through the second gas channel 21, the more the gas flow 50 discharged in the first gas channel 11 is, the less the gas flow 50 discharged in the second gas channel 21 is, and the volume of the whole outer cylinder 20 can be reduced in the whole design. When the gas flow 50 is discharged, the gas flow 50 simultaneously discharges the gas flow 50 from the first gas passage 11 and the second gas passage 21, because the gap 12 is blocked by the movable diversion plate 40, a large amount of gas flow 50 respectively gushes towards the cylinder opening end through the first gas channel 11 and the second gas channel 21, the movable diversion plate 40 is provided with an inner closing plate 41 and an outer closing plate 42, at the moment, the gas flow 50 respectively pushes the inner closing plate 41 and the outer closing plate 42, the inner closing plate 41 and the outer closing plate 42 drive the whole movable diversion plate 40 to move, the movable diversion plate 40 is pushed towards the cylinder opening end by the gas flow 50 and protrudes out of the cylinder opening end, at the moment, the gap 12 is opened due to the movement of the movable diversion plate 40, as shown in fig. 2, while the gas flow 50 is discharged through the second gas passage 21, and also discharged through the first gas channel 11, through the notch 12 and then through the cylinder end of the second gas channel 21.
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 (7)
1. A fuel gas flow self-discharging structure suitable for a missile launcher is characterized by comprising an inner barrel (10), an outer barrel (20), a fixed guide plate (30) and a movable guide plate (40);
a fixed guide plate (30) is arranged in the inner cylinder (10);
the inner cylinder (10) and the fixed guide plate (30) form a first gas channel (11);
a second gas channel (21) is formed between the inner cylinder (10) and the outer cylinder (20);
a notch (12) is arranged at the mouth end of the inner cylinder body (10);
the gap (12) is blocked by the movable guide plate (40), one end of the movable guide plate (40) extends to the second gas channel (21) and contacts the outer cylinder (20), and the other end of the movable guide plate (40) extends to the first gas channel (11) and is connected with the inner cylinder (10) in a sliding manner;
when the gas flow (50) is discharged, the gas flow (50) drives the movable guide plate (40) to slide close to the cylinder opening end, and at the moment, the gas flow (50) in the first gas channel (11) is discharged through the second gas channel (21) through the notch (12).
2. The gas flow self-discharge structure suitable for missile launcher according to claim 1, wherein the missile (60) is installed inside the inner cylinder (10);
the fixed guide plate (30) and the guided missile (60) are arranged in a clearance way.
3. The gas flow self-discharge structure for missile launcher according to claim 1, wherein a support plate (22) is provided between the inner barrel (10) and the outer barrel (20).
4. The gas flow autonomous discharge structure for missile launchers as claimed in claim 1, characterized in that the number of the fixed deflectors (30) is plural;
the number of the notches (12) is matched with the number of the fixed guide plates (30).
5. The autonomous emission structure of the flow of gas suitable for missile launcher of claim 1, characterized in that said mobile deflector (40) comprises an inner closing plate (41), an outer closing plate (42) and an intermediate segment (44);
the inner closing plate (41), the middle section (44) and the outer closing plate (42) are sequentially and integrally connected.
6. The gas flow autonomous discharge structure for missile launchers as claimed in claim 5, characterized in that said first gas channel (11) has a cross section in the shape of a sector ring.
7. The gas flow autonomous discharge structure for missile launchers as claimed in claim 1, further comprising a support bracket (31);
the supporting bracket (31) is arranged on the fixed guide plate (30);
the support bracket (31) supports the missile (60).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910877314.2A CN110595276B (en) | 2019-09-17 | 2019-09-17 | Gas flow self-discharging structure suitable for missile launcher |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910877314.2A CN110595276B (en) | 2019-09-17 | 2019-09-17 | Gas flow self-discharging structure suitable for missile launcher |
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| Publication Number | Publication Date |
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| CN110595276A true CN110595276A (en) | 2019-12-20 |
| CN110595276B CN110595276B (en) | 2021-11-09 |
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| CN201910877314.2A Active CN110595276B (en) | 2019-09-17 | 2019-09-17 | Gas flow self-discharging structure suitable for missile launcher |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111238305A (en) * | 2020-03-16 | 2020-06-05 | 上海机电工程研究所 | Anti-impact tail cover suitable for missile launcher and missile launcher |
| CN112665457A (en) * | 2020-12-17 | 2021-04-16 | 中国航空工业集团公司成都飞机设计研究所 | Pressurization launching device for airborne buried weapon |
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| DE1801614A1 (en) * | 1968-10-07 | 1970-06-11 | Precitronic | Guide device for launching unguided missiles (launching device for unguided rockets) |
| DE19643829A1 (en) * | 1996-10-30 | 1998-05-07 | Wegmann & Co Gmbh | Launching device for self-propelled missiles, in particular artillery missiles |
| US5837919A (en) * | 1996-12-05 | 1998-11-17 | The United States Of America As Represented By The Secretary Of The Navy | Portable launcher |
| US6230604B1 (en) * | 1997-01-14 | 2001-05-15 | United Defense, L.P. | Concentric canister launcher |
| CN202522139U (en) * | 2012-04-20 | 2012-11-07 | 卢钦一 | Tail flame removing launcher for fire-fight missile |
| CN105910492A (en) * | 2016-04-15 | 2016-08-31 | 中国运载火箭技术研究院 | Winged missile vertical thermal emission inner-round outer-square concentric cylinder structure |
| CN108007272A (en) * | 2018-01-24 | 2018-05-08 | 安徽工业大学 | A kind of concentric launching tube of helix flow-guiding type |
| CN108151584A (en) * | 2018-01-08 | 2018-06-12 | 广州鼎飞科技有限公司 | Integral type rocket bomb transmitting cylinder and emitter |
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2019
- 2019-09-17 CN CN201910877314.2A patent/CN110595276B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1801614A1 (en) * | 1968-10-07 | 1970-06-11 | Precitronic | Guide device for launching unguided missiles (launching device for unguided rockets) |
| DE19643829A1 (en) * | 1996-10-30 | 1998-05-07 | Wegmann & Co Gmbh | Launching device for self-propelled missiles, in particular artillery missiles |
| US5837919A (en) * | 1996-12-05 | 1998-11-17 | The United States Of America As Represented By The Secretary Of The Navy | Portable launcher |
| US6230604B1 (en) * | 1997-01-14 | 2001-05-15 | United Defense, L.P. | Concentric canister launcher |
| CN202522139U (en) * | 2012-04-20 | 2012-11-07 | 卢钦一 | Tail flame removing launcher for fire-fight missile |
| CN105910492A (en) * | 2016-04-15 | 2016-08-31 | 中国运载火箭技术研究院 | Winged missile vertical thermal emission inner-round outer-square concentric cylinder structure |
| CN108151584A (en) * | 2018-01-08 | 2018-06-12 | 广州鼎飞科技有限公司 | Integral type rocket bomb transmitting cylinder and emitter |
| CN108007272A (en) * | 2018-01-24 | 2018-05-08 | 安徽工业大学 | A kind of concentric launching tube of helix flow-guiding type |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111238305A (en) * | 2020-03-16 | 2020-06-05 | 上海机电工程研究所 | Anti-impact tail cover suitable for missile launcher and missile launcher |
| CN111238305B (en) * | 2020-03-16 | 2021-12-03 | 上海机电工程研究所 | Anti-impact tail cover suitable for missile launcher and missile launcher |
| CN112665457A (en) * | 2020-12-17 | 2021-04-16 | 中国航空工业集团公司成都飞机设计研究所 | Pressurization launching device for airborne buried weapon |
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| Publication number | Publication date |
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| CN110595276B (en) | 2021-11-09 |
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