CN108007272A - A kind of concentric launching tube of helix flow-guiding type - Google Patents
A kind of concentric launching tube of helix flow-guiding type Download PDFInfo
- Publication number
- CN108007272A CN108007272A CN201810066899.5A CN201810066899A CN108007272A CN 108007272 A CN108007272 A CN 108007272A CN 201810066899 A CN201810066899 A CN 201810066899A CN 108007272 A CN108007272 A CN 108007272A
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- CN
- China
- Prior art keywords
- helix
- inner cylinder
- launching tube
- guiding type
- concentric
- Prior art date
- 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
-
- 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 discloses a kind of concentric launching tube of helix flow-guiding type, belong to space launch field.A kind of concentric launching tube of helix flow-guiding type of the present invention, including inner cylinder, outer barrel and deflection cone, are surrounded with helix in the annular chamber between the inner cylinder and outer barrel, the guided missile combustion gas for making after deflection cone to enter in annular chamber is discharged around helical cavity.Helix offers axial deflector hole close to one end of deflection cone, the deflector hole circumferential direction spaced set on same helix.The present invention delays powder gas and is completely exhausted out the time of annular chamber by setting helix, and tail gas is discharged to off-axis direction, so as to avoid influence during transmitting to guided missile wall ablation, helps to improve the security of MISSILE LAUNCHING.
Description
Technical field
The present invention relates to space launching technology field, launches with one heart more specifically to a kind of helix flow-guiding type
Cylinder.
Background technology
Since concentric tube emitting structural has the function of simple in structure, easy to operate and is led from row, it is in vehicle-mounted and warship
Carry and widely used in weapon.For the guided missile of concentric tube transmitting, for high temperature, high-speed fuel gas caused by transmitting, the bottom of by
After portion's guiding device deflection, discharged upwards by the annular space between two layers of cylinder.
At present in concentric tube emission process, second-time burning occurs with the oxygen in launching tube after the ejection of guided missile combustion gas stream,
After oxygen in shooting cylinder pending runs out of, the combustion gas of second-time burning does not occur and enters inner cylinder and outer by the guide functions of deflection cone
Between cylinder, combustion gas is outside the passage discharge cylinder between inner cylinder and outer barrel.At this time, the combustion gas discharged outside launching tube can surround just to go out
The guided missile of cylinder, and second-time burning process occurs with the combustion gas in air, cause guided missile wall surface temperature to raise again, seriously affect and lead
The emission security of bullet.The scheme used at present has installs deflector additional in outer barrel nozzle, and the program can improve guided missile wall
Temperature.But during actual transmission, it is inconvenient for operation, and influence launch preparation time.
Wake flame emitter (application number is removed such as published fire extinguishing guided missile：201220171918.9), it is in outer guide tube
Interior to be vertically arranged with an interior guide tube with outer guide tube concentric circles along outer guide tube, the space between outer guide tube and interior guide tube is formed
Gas channel, is equipped with track in interior guide tube, in the tail-hood being connected with outer guide tube tail end there is a conical diverter to bore, interior guide tube
Room of backflowing is constituted between tail end and tail-hood.Due to foring gas channel between outer guide tube and interior guide tube, tail-hood in addition
Stop and the effect of spreader, fire extinguishing guided missile produce the powerful wake flame erupted backward when lighting after diffluence room and spreader
The port of outer guide tube and interior guide tube will be discharged in time forward from unlimited gas channel.
Above-mentioned patent formula can adapt to the transmitting in aerodynamic missile, and allow gas to enough guiding, but existing for it
Main problem is that the combustion gas discharged outside launching tube can surround the guided missile for just going out cylinder, and guided missile wall surface temperature is caused in second-time burning
Raise again, seriously affect the emission security of guided missile.
The content of the invention
1. technical problems to be solved by the inivention
It is an object of the invention to overcome launching tube discharge tail gas second-time burning in the prior art to easily lead to guided missile wall temperature
Spend elevated deficiency again, there is provided a kind of concentric launching tube of helix flow-guiding type, the present invention prolong by setting helix
The time of annular chamber is late completely exhausted out after powder burning, and tail gas is discharged to off-axis direction, so as to avoid transmitting
When ablation on guided missile wall influence, contribute to the raising of MISSILE LAUNCHING security.
2. technical solution
To reach above-mentioned purpose, technical solution provided by the invention is：
A kind of concentric launching tube of helix flow-guiding type of the present invention, including inner cylinder, outer barrel and deflection cone, the inner cylinder with
Helix is surrounded with annular chamber between outer barrel, makes to enter the gas in annular chamber after deflection cone and is arranged around helical cavity
Go out.
As further improvement of the present invention, spacing is 0~40mm at the top of the helix and at the top of inner cylinder.
As further improvement of the present invention, the helix is close to one end of deflection cone and inner cylinder end spacing
For 1~2 times of pitch.
As further improvement of the present invention, the spiral winding carries 2~5, and the pitch of each helix is identical.
As further improvement of the present invention, the neighbouring arrangement of a plurality of helix, forms spiral winding body；Or a plurality of spiral shell
Curl up band circumferentially to arrange at equal intervals, form isometric(al) helical cavity.
As further improvement of the present invention, the helix offers axial water conservancy diversion close to one end of deflection cone
Hole, the deflector hole circumferential direction spaced set on same helix.
As further improvement of the present invention, the deflector hole is any group of circular or square or triangle or three
Close.
As further improvement of the present invention, the support of circumferentially-spaced distribution is provided between the inner cylinder and outer barrel
Plate, the support plate are located at close to deflection cone one end.
As further improvement of the present invention, the inner cylinder bottom is provided with bullet support.
As further improvement of the present invention, missile trajectory is provided with the inner cylinder.
3. beneficial effect
Using technical solution provided by the invention, compared with prior art, have the advantages that：
(1) a kind of concentric launching tube of helix flow-guiding type of the invention, it includes the spiral shell being made of some helixes
Spiral forms, and has been formed in the interior thereof spiral runner, which causes the combustion gas between inner cylinder and outer barrel
Fluid is arranged on the outside of guided missile in exit, helps to improve the temperature environment of guided missile wall.
(2) a kind of concentric launching tube of helix flow-guiding type of the invention, curl up band top and spacing at the top of inner cylinder for 0~
40mm, according to the different explosive payload of guided missile and transmitting cylinder size, can carry out corresponding adjustment；The structure can go out gas
During mouthful discharge, discharged along helix tangential direction, so as to deviate the axis direction of launching tube, if apart from inner cylinder end size compared with
Greatly, this effect is relatively weak.
(3) a kind of concentric launching tube of helix flow-guiding type of the invention, its spiral winding body are opened close to one end of deflection cone
There are some deflector holes, which can effectively improve the pressure of concentric tube bottom, contribute to gas caused by MISSILE LAUNCHING
Body is quickly discharged, reasonable in design, and principle is simple, easy to promote the use of.
Brief description of the drawings
Fig. 1 is the structure diagram of existing launching tube.
Fig. 2 is the schematic cross-section of launching tube of the present invention；
Fig. 3 is the structure diagram of spiral winding body.
Fig. 4 is the structure diagram of guide shell and helix；
Fig. 5 is the setting structure schematic diagram of circular deflector hole；
Fig. 6 is the setting structure schematic diagram of direction deflector hole.
Label declaration in schematic diagram：1st, deflection cone；2nd, support plate；3rd, bullet support；4th, deflector hole；5th, helix；6th, it is interior
Cylinder；7th, outer barrel；8th, spiral winding body.
Embodiment
To further appreciate that present disclosure, the present invention is described in detail in conjunction with the accompanying drawings and embodiments.
As shown in Figure 1, existing launching tube includes interior guide tube and outer guide tube, along outer guide tube be vertically arranged with one with it is outer
The interior guide tube of guide tube concentric circles, space between outer guide tube and interior guide tube form gas channel, track are equipped with interior guide tube, and outer
In the tail-hood of guide tube tail end connection there is a conical diverter to bore, room of backflowing is constituted between interior guide tube tail end and tail-hood.By
In foring gas channel between outer guide tube and interior guide tube, the stop of tail-hood and the effect of spreader in addition, fire extinguishing guided missile exists
The powerful wake flame erupted backward is produced when lighting will be timely forward from unlimited gas channel after diffluence room and spreader
The port of the outer guide tube of discharge and interior guide tube.
Embodiment 1
With reference to Fig. 2, a kind of concentric launching tube of helix flow-guiding type of the present embodiment, including inner cylinder 6, outer barrel 7 and water conservancy diversion
Cone 1, inner cylinder 6 is coaxially disposed with outer barrel 7, and deflection cone 1 is fixedly connected on 7 end of outer barrel.Annular chamber between inner cylinder 6 and outer barrel 7
For discharging combustion tail gas, helix 5 is surrounded with annular chamber, makes to enter the gas in annular chamber after deflection cone 1
Discharged around helical cavity.Helix 5 is surround along inner cylinder 6, and annular chamber is separated, and forms helical cavity.The pitch of helix 5
It can be adjusted according to minimum fluid resistance.
Using close to one end of deflection cone 1, as bottom, the other end is outer end, a helix 5 from 6 bottom of inner cylinder around to
Outer end, and be continuous band, at 6 outer end of inner cylinder, helix 5 is close proximity to inner cylinder end, or is flush with it.
When combustion tail gas is discharged, deflection cone 1 is flow to by 6 bottom of inner cylinder, tail gas enters ring along the conical surface of deflection cone 1
Shape intracavitary, and then each helical cavity is entered, discharged along helix 5.When gas, which reaches, to be exported, since inertia is former
Cause, can flow out along the incline direction of exit helix 5, be considered as discharging around tangential direction, motion path deviates hair
Shooting cylinder axis.
Further, since the presence of helix 5, tail gas is discharged when being discharged by helical cavity relative to straight tube, is passed through
Path increase, and be subject to certain resistance, efflux time has delayed, so that there are the regular hour with the transmitting of guided missile
Difference, avoids impacting guided missile.Guided missile time in transmitting is very short, and delaying for time referred herein is also certain amount
Time in level slows down, rather than has the larger time difference.If pitch setting is smaller, gas discharge is excessively slow, certainly will
It can cause the greater impact to bottom, it is easy to damage deflection cone 1.
For deflection cone 1, conventional structure can be used, can preferably be matched somebody with somebody with helix 5 exemplified by the present embodiment
Close, done further limitation.1 bottom case of deflection cone is axisymmetric pyramidal structure, a diameter of D at water conservancy diversion conical shell bottomout(wherein Dout
For the diameter of outer barrel), the cone angle of deflection cone isThe cone of deflection cone is a height of(wherein RoutFor the radius of outer barrel).
In order to make in the smooth ejection annular chamber of combustion gas that guided missile sprays, can use Ali formula design pitch, in Ali public affairs
In formula, the resistance formula of fluid is
λ=0.18Re-1/8(d/Deq)0.15
In formula, λ be fluid resistance, Re be combustion gas Reynolds number, d be inner cylinder outside diameter, DeqFor spiral equivalent diameter, p
For pitch, D is outer barrel internal diameter.
In inner cylinder and outer barrel diameter one periodically, when fluid resistance λ is minimum, it can be deduced that the pitch of optimal conveyor screw.
Embodiment 2
A kind of concentric launching tube of helix flow-guiding type of the present embodiment, its basic structure is same as Example 1, improves it
Be in：Helix 5 has 2, and the pitch of each helix 5 is identical, helix 5 close to one end of deflection cone 1 with it is interior
6 end spacing of cylinder are 2 times of pitch, so that gas can be rapidly introduced into annular chamber in inlet, the lower extreme point of helix 5
Flush, on the same section perpendicular to axis, so that gas can enter each cavity at the same time.
As preferable scheme, 2 helixes 5 can circumferentially be spacedly distributed, and form 2 helical cavities, tail gas is around spiral shell
Revolve chamber discharge.The top of helix 5 is 10mm with the top of inner cylinder 6, and inner cylinder 6 is flushed with the outer end of outer barrel 7.
The support plate 2 of circumferentially-spaced distribution is provided between inner cylinder 6 and outer barrel 7, which is located at close to deflection cone 1
One end, the main function of support plate 2 are support inner cylinders 6, apart from 6 end spacing of inner cylinder are 2 by helix 5 in this present embodiment
Times pitch,, can be in 6 end set support plate of inner cylinder in order to improve the stability of transmitting barrel structure with one heart apart from relatively large
2.The support plate 2 could be provided as 4 preferably, in the case where structural strength meets condition, can be changed as needed
Become adjustment.
Embodiment 3
With reference to Fig. 3, a kind of concentric launching tube of helix flow-guiding type of the present embodiment, its basic structure and 2 phase of embodiment
Together, the improvement is that：3 helixes 5, and the neighbouring arrangement of helix 5 are provided with the present embodiment, forms spiral winding
Body 8, the pitch of the spiral winding body 8 are identical with the pitch of helix 5.Unlike but, each helix in spiral winding body 8
Minor spiral chamber is formed between 5, and spiral winding body 8 is used as an entirety, and there is a larger helical cavity.
Helix 5 is single times of pitch apart from 6 end spacing of inner cylinder in the present embodiment, and the top of helix 5 is pushed up with inner cylinder 6
Portion is 20mm, and support plate 2 could be provided as 3 preferably, 3 support plates 2 are spacedly distributed in the present embodiment.6 bottom of inner cylinder
Portion is provided with bullet support 3, which is less than 6 internal diameter of inner cylinder.Bullet support annular diameters are 0.95Dmis~0.75Dmis(wherein Dmis
For the diameter of guided missile), bullet support can be connected with inner cylinder by welding.
Embodiment 4
With reference to Fig. 4, Fig. 5, a kind of concentric launching tube of helix flow-guiding type of the present embodiment, its basic structure and embodiment
3 is identical, thes improvement is that：Helix 5 offers axial circular deflector hole close to one end of deflection cone 1 in the present embodiment
4, the circumferential spaced set of deflector hole 4 on same helix 5.
Deflector hole 4 perforative 5 length thereof of helix be not less than whole helix 5 1/4, be preferably its 1/3,
The deflector hole can effectively improve the pressure of concentric tube bottom, contribute to gas caused by MISSILE LAUNCHING quickly to discharge.Week
It can be modified to the number of deflector hole 4 is set according to the mass flowrate of guided missile combustion gas stream.In addition, either it is directed to spiral winding body
8 still for multiple helixes 5 of equidistantly distributed, can be using the set-up mode of above-mentioned deflector hole.
When launching a guided missile, it is impossible to larger pressure is produced to bottom, thus set deflector hole 4 contributes to fire
The discharge of tail-gas.When helical cavity is not enough to quickly discharge excessive gas, by deflector hole 4, it can quickly make part
Gas is entered in another helical cavity, and axial movement speed is accelerated, so as to help to improve the pressure of outer barrel bottom.
Embodiment 5
A kind of concentric launching tube of helix flow-guiding type of the present embodiment, its basic structure is same as Example 4, improves it
Be in：In the present embodiment deflector hole 4 perforative 5 length thereof of helix be whole helix 5 1/2, but be worth
Illustrate, even if length shared by deflector hole 4 is larger, but last ring of 5 outer end of helix is not provided with deflector hole 4, otherwise
The gas that deflector hole 4 is discharged can influence the trend from helical cavity discharge gas, and for portion gas to launching tube axial dipole field, there have to be unfavorable
Influence.
As shown in fig. 6, the deflector hole 4 in the present embodiment could be provided as it is square, further, it is also possible to be arranged to triangle or
Rectangle or ellipse etc., in the case where not influencing bulk mass flow rate, can suitably adjust selection.Or according to difficult processing with
Degree is selected.In view of uniformity, circle has preferable effect.
Embodiment 6
A kind of concentric launching tube of helix flow-guiding type of the present embodiment, its basic structure is same as Example 5, improves it
Be in：Missile trajectory is provided with inner cylinder 6, which is installed in inner cylinder 6 by stent, specifically can refer to disclosed
Patent document (application number：201220171918.9) be configured.
Operation principle：During MISSILE LAUNCHING, combustion gas is sprayed into deflection cone from inner cylinder, and secondary with the oxygen generation in deflection cone
Combustion process, after the guide functions of deflection cone, combustion gas enters annular chamber between inner cylinder and outer barrel, when combustion gas run into it is spiral
During around band, combustion gas is moved along the type surface current of helix, in the bottom of inner cylinder and outer barrel, due to being provided with deflector hole on flow-disturbing band,
Combustion gas flows into next runner along deflector hole, reduces the pressure in blower inlet casing, since hydrodynamic form top does not have deflector hole, combustion
Gas is excluded outside cylinder in the shape of a spiral along the type face of hurricane band, and the combustion gas is away from guided missile, so as to reduce the temperature of guided missile wall.This
Outside, helical cavity discharge gas further weakens influence degree with launching a guided missile there are the regular hour is poor.
Schematically the present invention and embodiments thereof are described above, this describes no restricted, institute in attached drawing
What is shown is also one of embodiments of the present invention, and actual structure is not limited thereto.So if common skill of this area
Art personnel are enlightened by it, without departing from the spirit of the invention, are not inventively designed and the technical solution
Similar frame mode and embodiment, are within the scope of protection of the invention.
Claims (10)
1. a kind of concentric launching tube of helix flow-guiding type, including inner cylinder (6), outer barrel (7) and deflection cone (1), it is characterised in that：
Helix (5) is surrounded with annular chamber between the inner cylinder (6) and outer barrel (7), makes to enter ring after deflection cone (1)
The gas of shape intracavitary is discharged around helical cavity.
A kind of 2. concentric launching tube of helix flow-guiding type according to claim 1, it is characterised in that：The spiral winding
Spacing is 0~40mm at the top of band (5) and at the top of inner cylinder (6).
A kind of 3. concentric launching tube of helix flow-guiding type according to claim 1, it is characterised in that：The spiral winding
Band (5) is 1~2 times of pitch close to one end of deflection cone (1) and inner cylinder (6) end spacing.
A kind of 4. concentric launching tube of helix flow-guiding type according to claim 1, it is characterised in that：The helix
(5) there are 2~5, and the pitch of each helix (5) is identical.
A kind of 5. concentric launching tube of helix flow-guiding type according to claim 4, it is characterised in that：A plurality of helix
(5) neighbouring arrangement, forms spiral winding body (8)；Or a plurality of helix (5) is circumferentially arranged at equal intervals, it is spiral to form isometric(al)
Chamber.
A kind of 6. concentric launching tube of helix flow-guiding type according to claim 1 or 4, it is characterised in that：It is described spiral
Axial deflector hole (4) is offered close to one end of deflection cone (1), the deflector hole (4) on same helix (5) around band (5)
Circumferential spaced set.
A kind of 7. concentric launching tube of helix flow-guiding type according to claim 6, it is characterised in that：The deflector hole
(4) it is circular or square or triangle or any combination of three.
8. according to a kind of concentric launching tube of helix flow-guiding type according to any one of claims 1 to 5, it is characterised in that：
The support plate (2) of circumferentially-spaced distribution is provided between the inner cylinder (6) and outer barrel (7), which is located at close to water conservancy diversion
Bore (1) one end.
9. according to a kind of concentric launching tube of helix flow-guiding type according to any one of claims 1 to 5, it is characterised in that：
Inner cylinder (6) bottom is provided with bullet support (3).
10. according to a kind of concentric launching tube of helix flow-guiding type according to any one of claims 1 to 5, it is characterised in that：
Missile trajectory is provided with the inner cylinder (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810066899.5A CN108007272A (en) | 2018-01-24 | 2018-01-24 | A kind of concentric launching tube of helix flow-guiding type |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810066899.5A CN108007272A (en) | 2018-01-24 | 2018-01-24 | A kind of concentric launching tube of helix flow-guiding type |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108007272A true CN108007272A (en) | 2018-05-08 |
Family
ID=62066516
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810066899.5A Pending CN108007272A (en) | 2018-01-24 | 2018-01-24 | A kind of concentric launching tube of helix flow-guiding type |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595276A (en) * | 2019-09-17 | 2019-12-20 | 上海机电工程研究所 | Gas flow self-discharging structure suitable for missile launcher |
| CN110864584A (en) * | 2018-08-27 | 2020-03-06 | 南京理工大学 | Adjustable gas jet flow guiding device for rocket missile launching |
| CN112026199A (en) * | 2020-08-17 | 2020-12-04 | 江苏新扬新材料股份有限公司 | Method for forming composite material concentric launching tube |
| CN113218243A (en) * | 2021-04-22 | 2021-08-06 | 中国人民解放军93305部队 | Shunting device for weakening energy of tail flame emitted by missile |
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| US20050108917A1 (en) * | 2003-11-25 | 2005-05-26 | Government Of The United States Of America | Reloadable concentric canister launcher |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110864584A (en) * | 2018-08-27 | 2020-03-06 | 南京理工大学 | Adjustable gas jet flow guiding device for rocket missile launching |
| CN110864584B (en) * | 2018-08-27 | 2022-04-08 | 南京理工大学 | Adjustable gas jet flow guiding device for rocket missile launching |
| CN110595276A (en) * | 2019-09-17 | 2019-12-20 | 上海机电工程研究所 | Gas flow self-discharging structure suitable for missile launcher |
| CN110595276B (en) * | 2019-09-17 | 2021-11-09 | 上海机电工程研究所 | Gas flow self-discharging structure suitable for missile launcher |
| CN112026199A (en) * | 2020-08-17 | 2020-12-04 | 江苏新扬新材料股份有限公司 | Method for forming composite material concentric launching tube |
| CN112026199B (en) * | 2020-08-17 | 2021-07-06 | 江苏新扬新材料股份有限公司 | Method for forming composite material concentric launching tube |
| CN113218243A (en) * | 2021-04-22 | 2021-08-06 | 中国人民解放军93305部队 | Shunting device for weakening energy of tail flame emitted by missile |
| CN113218243B (en) * | 2021-04-22 | 2022-10-25 | 中国人民解放军93305部队 | Shunting device for weakening energy of tail flame emitted by missile |
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