CN106050476A - Liquid-propellant rocket engine ignition device and ignition method thereof - Google Patents
Liquid-propellant rocket engine ignition device and ignition method thereof Download PDFInfo
- Publication number
- CN106050476A CN106050476A CN201610540366.7A CN201610540366A CN106050476A CN 106050476 A CN106050476 A CN 106050476A CN 201610540366 A CN201610540366 A CN 201610540366A CN 106050476 A CN106050476 A CN 106050476A
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- China
- Prior art keywords
- front head
- housing
- medicine
- gunpowder
- frame
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/95—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by starting or ignition means or arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)
Abstract
The invention discloses a liquid-propellant rocket engine ignition device and an ignition method thereof. The device comprises an igniter base, a front end socket and a shell. The igniter base is of a T-shaped structure, the two sides of the igniter base are provided with electric ignition tube connectors, and the bottom of the igniter base is connected with the front end socket. The other end of the front end socket is connected to the shell. A gunpowder box is installed in the front end socket. The gunpowder box is a hollow cylindrical gunpowder box with one closed end, the closed end is provided with a plurality of spray holes, and the unclosed end is connected with the front end socket. A gunpowder frame is installed in the shell. A gunpowder column is arranged in the gunpowder frame. A heat insulation layer is arranged between the shell and the gunpowder frame. A heat insulation sleeve is arranged between the gunpowder frame and the gunpowder column. A gunpowder blocking plate is arranged between the bottom of the gunpowder frame and the bottom of the shell. According to the liquid-propellant rocket engine ignition device, the space occupation rate can be significantly reduced, and the structural mass of the liquid-propellant engine is reduced. Many kinds of gunpowder can be selected and are unrelated with an engine supply system, influences on an injector structure are small, and use and maintenance are convenient.
Description
Technical field
The invention belongs to Liquid Propellant Rocket Engine field, be specifically related to a kind of liquid-propellant rocket engine igniter and
Its ignition method.
Background technology
The operation principle of liquid-propellant rocket engine igniter is release self-energy, and fast and reliable place burning liquid advances
Agent, so that it is guaranteed that its effecting reaction.Conventional igniter type includes cartridge, electric igniter, torch lighter, humorous
Shake lighter etc..The propellant that liquid oxygen/methane liquid engine uses is liquid oxygen and methane, and it uses temperature ratio relatively low, therefore,
Igniter is required the highest.
Summary of the invention
It is an object of the invention to provide a kind of liquid-propellant rocket engine igniter and ignition method thereof, with reach liquid oxygen/
Methane liquid electromotor can the purpose of reliable ignition.
For solving above-mentioned technical problem, the technical solution adopted in the present invention is: a kind of liquid-propellant rocket engine igniting dress
Putting, including lighter pedestal, front head and housing, described lighter pedestal is T-type structure, and its both sides are provided with electric squib and connect
Mouthful, bottom is connected with front head；The front head other end is connected to housing, is provided with medicine box in front head, and medicine box is that one end is closed
Hollow cylinder shape box body, one end of closing machined several spray orifices, and unclosed one end is connected with front head；Install in housing
Medicine frame, is provided with powder column in medicine frame, be provided with heat insulation layer, be provided with jacket between medicine frame and powder column between described housing and medicine frame；Medicine
It is mounted with grate between bottom and the housing bottom of frame.
Described electric squib seam uses the first sealing ring and plug to seal.In storage, transportation, need not
Electric squib is installed, plug is installed, lighter can be protected.
It is provided with the second sealing ring between described lighter seat and front head, between front head and housing, is provided with the 3rd sealing
Circle, the second sealing ring and have the 3rd sealing ring to use red copper material or silastic material to make.Sealing is improved by sealing ring
Energy.
There is also mounted cushion between front head and medicine frame, it uses silicone rubber or sponge material to make.Powder column is avoided to exist
Transport, work process are rocked.
Described front head includes that heat exchanger head, heat exchanger head side are boss, and boss machined screwed hole, by boss and igniting
Device pedestal connects, and opposite side machined medicine box interface and end socket interface, and medicine box interface connects with the screwed hole of boss, end socket interface
It is connected with housing.Medicine box interface and end socket interface are helicitic texture.
Described medicine frame includes the medicine frame cylinder of hollow, and some through holes processed by the wall of medicine frame cylinder, and its one end machined multiple
Convex platform, the other end machined multiple lower convex platform, convex platform and lower convex platform and is L-type, and the centre of medicine frame cylinder is provided with props up
Frame, the centre of support is circular platform type, and edge is connected with the wall of medicine frame cylinder by dowel.By above-mentioned design, can with loss of weight,
Improve breathing area.
Described heat insulation layer and jacket all use ethylene propylene diene rubber to make.Heat insulation layer can be used for heat insulation resistance to ablation, it is to avoid
Case material high temperature failure, simultaneously works as insulation effect.
Powder column uses double-base powder；Combustion gas is clean, does not produce the impurity of blocking thrust chamber design of part；And fuel gas temperature is one
Suitably scope, will cause ablation to damage igniter and pipeline；Types of Medicine structure is cigarette burning structure, and remaining position is glued
Having connect jacket, jacket uses ethylene propylene diene rubber；Ensure that combustion face is stable；Powder column is bonded on support by adhesive；Really
Protect the stability in powder column transport, work process.
Black powder or pyrotechnic compound, or a combination thereof thing can be loaded in medicine box；
Between medicine frame and housing, it is mounted with that grate, grate include plate body, and plate body machined several spray orifices.
Described housing includes that the housing cylinder of the hollow closed one end, untight one end are connected with front head, closing
One end has nozzle boss, nozzle boss to machined nozzle, and outside machined helicitic texture, is connected with liquid engine thrust chamber.
It addition, lighter seat is provided with electric squib interface at two, it is used for electric squib is installed, is Redundancy Design at two, carries
High reliability.
A kind of liquid-propellant rocket engine ignition method, concretely comprises the following steps:
In medicine box, first load black powder and/or pyrotechnic compound, at inner walls sticking adiabatic layer, in the thermal insulation of powder column paste outside
Set, puts into grate in housing, is then placed in the medicine frame equipped with powder column, installs cushion, installs medicine box on front head, will
Front head is connected with housing, is finally connected with front head by lighter seat；And installation electric squib can enter on lighter seat
Row igniting.
When the method is as directly used, installing electric squib on lighter seat, electric squib receives control system and sends out
During the electricity instruction gone out, all can act on the black powder igniting in medicine box, medicine box output flame, light the powder column on medicine frame, produce height
Temperature gases at high pressure, discharge from boss nozzle, and the igniting for liquid propellant provides the energy；If do not carried out ignition operation immediately,
Electric squib seam installs plug, installs electric squib when needs are lighted a fire again and lights a fire.
This igniter can significantly reduce space occupancy, alleviate liquid engine architecture quality.Igniter
Simple in construction, available gunpowder kind is more, unrelated with electromotor supply system, little to ejector filler structure influence, uses dimension
Protect conveniently.By suitable Redundancy Design, reliability can reach more than 0.9999.For successfully completing Multitest, achieve good
Good effect.
Accompanying drawing explanation
Fig. 1 is the structural representation of fluid present invention rocket motor ignition device.
Fig. 2 is lighter holder structure schematic diagram.
Fig. 3 is front head profile.
Fig. 4 is casing cross-section figure.
Fig. 5 is medicine shelf structure schematic diagram.
Fig. 6 is grate structural representation.
Detailed description of the invention
Further illustrate the present invention below in conjunction with embodiment, but the scope of protection of present invention is not limited to implement
The scope of example statement.Embodiment is used only to illustrate the actual application of the present invention, help deeper into the understanding present invention.
Embodiment:
A kind of liquid-propellant rocket engine igniter, including lighter pedestal 1, front head 5 and housing 9, described lighter pedestal 1
For T-type structure, its both sides are provided with electric squib interface, and bottom is connected with front head 5；Front head 5 other end is connected to housing, front
Being provided with medicine box 6 in end socket 5, medicine box is the hollow cylinder shape box body that one end is closed, and one end of closing machined several spray orifices,
Unclosed one end is connected with front head 5；Medicine frame 11 is installed in housing, in medicine frame 11, is provided with powder column 12, described housing and medicine frame 11
Between be provided with heat insulation layer 10, be provided with jacket 13 between medicine frame 11 and powder column 12；Pacify between bottom and the housing bottom of medicine frame 11
Fill grate 14.
Further, described electric squib seam uses the first sealing ring 2 and plug 3 to seal.
Further, it is provided with the second sealing ring 4 between described lighter seat and front head, is provided with between front head and housing
3rd sealing ring 7, the second sealing ring 4 and have the 3rd sealing ring to use red copper material or silastic material to make.
Further, there is also mounted cushion 8 between front head and medicine frame, it uses silicone rubber or sponge material to make.
Further, described front head includes that heat exchanger head 5-1, heat exchanger head side are boss 5-2, and boss machined screw thread
Hole, is connected with lighter pedestal by boss, and opposite side machined medicine box interface 5-3 and end socket interface 5-4, and medicine box interface is with convex
The screwed hole connection of platform, end socket interface is connected with housing.
Further, described medicine frame includes the medicine frame cylinder 11-1 of hollow, and the wall of medicine frame cylinder processes some through holes, one
End machined multiple convex platform 11-2, and the other end machined multiple lower convex platform 11-3, and convex platform and lower convex platform are L-type, medicine frame
The centre of cylinder is provided with support 11-4, and the centre of support is circular platform type, and edge is connected with the wall of medicine frame cylinder by dowel.
Further, described heat insulation layer and jacket all use ethylene propylene diene rubber to make.
Further, described housing includes the housing cylinder of the hollow closed one end, and untight one end is with front head even
Connecing, one end of closing has nozzle boss, nozzle boss to machined nozzle, and outside machined helicitic texture, pushes away with liquid engine
Power room connects.
Use aforesaid liquid rocket engine to carry out the method lighted a fire, concretely comprise the following steps:
In medicine box, first load black powder and/or pyrotechnic compound, at inner walls sticking adiabatic layer, in the thermal insulation of powder column paste outside
Set, puts into grate in housing, is then placed in the medicine frame equipped with powder column, installs cushion, installs medicine box on front head, will
Front head is connected with housing, is finally connected with front head by lighter seat；And installation electric squib can enter on lighter seat
Row igniting.If not carrying out ignition operation immediately, at electric squib seam, plug being installed, electricity being installed when needs are lighted a fire again and sends out
Fire tube is lighted a fire.
Claims (10)
1. a liquid-propellant rocket engine igniter, it is characterised in that include lighter pedestal (1), front head (5) and housing
(9), described lighter pedestal (1) is T-type structure, and its both sides are provided with electric squib interface, and bottom is connected with front head (5)；Before
End socket (5) other end is connected to housing, is provided with medicine box (6) in front head (5), and medicine box is the hollow circuit cylinder flask that one end is closed
Body, one end of closing machined several spray orifices, and unclosed one end is connected with front head (5)；Medicine frame (11), medicine are installed in housing
It is provided with powder column (12) in frame (11), between described housing and medicine frame (11), is provided with heat insulation layer (10), medicine frame (11) and powder column (12)
Between be provided with jacket (13)；Grate (14) it is mounted with between bottom and the housing bottom of medicine frame (11).
Device the most according to claim 1, it is characterised in that: described electric squib seam uses the first sealing ring (2)
Seal with plug (3).
Device the most according to claim 1, it is characterised in that: it is provided with second between described lighter seat and front head close
Seal (4), is provided with the 3rd sealing ring (7) between front head and housing, the second sealing ring (4) and have the 3rd sealing ring to use red copper
Material or silastic material are made.
Device the most according to claim 1, it is characterised in that: there is also mounted cushion (8) between front head and medicine frame, its
Silicone rubber or sponge material is used to make.
Device the most according to claim 1, it is characterised in that: described front head includes heat exchanger head (5-1), heat exchanger head side
For boss (5-2), boss machined screwed hole, is connected with lighter pedestal by boss, and opposite side machined medicine box interface (5-
3) and end socket interface (5-4), medicine box interface connects with the screwed hole of boss, and end socket interface is connected with housing.
Device the most according to claim 1, it is characterised in that: described medicine frame includes medicine frame cylinder (11-1) of hollow, medicine
Some through holes processed by the wall of frame cylinder, and its one end machined multiple convex platform (11-2), and the other end machined multiple lower convex platform
(11-3), convex platform and lower convex platform are L-type, and the centre of medicine frame cylinder is provided with support (11-4), and the centre of support is round platform
Type, edge is connected with the wall of medicine frame cylinder by dowel.
Device the most according to claim 1, it is characterised in that: described heat insulation layer and jacket all use ethylene propylene diene rubber
Make.
Device the most according to claim 1, it is characterised in that: described housing includes the housing cylinder of the hollow closed one end
Body, untight one end is connected with front head, and one end of closing has nozzle boss, nozzle boss to machined nozzle, and outside processes
Helicitic texture, is connected with liquid engine thrust chamber.
9. a liquid-propellant rocket engine ignition method, it is characterised in that concretely comprise the following steps:
In medicine box, first load black powder and/or pyrotechnic compound, at inner walls sticking adiabatic layer, in the thermal insulation of powder column paste outside
Set, puts into grate in housing, is then placed in the medicine frame equipped with powder column, installs cushion, installs medicine box on front head, will
Front head is connected with housing, is finally connected with front head by lighter seat；And installation electric squib can enter on lighter seat
Row igniting.
10. according to the method described in claim 9, it is characterised in that after lighter seat installs with front head, no
Carry out ignition operation immediately, at electric squib seam, plug is installed, electric squib is installed when needs are lighted a fire again and lights a fire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610540366.7A CN106050476B (en) | 2016-07-11 | 2016-07-11 | A kind of liquid-propellant rocket engine igniter and its ignition method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610540366.7A CN106050476B (en) | 2016-07-11 | 2016-07-11 | A kind of liquid-propellant rocket engine igniter and its ignition method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106050476A true CN106050476A (en) | 2016-10-26 |
| CN106050476B CN106050476B (en) | 2018-06-05 |
Family
ID=57185876
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610540366.7A Active CN106050476B (en) | 2016-07-11 | 2016-07-11 | A kind of liquid-propellant rocket engine igniter and its ignition method |
Country Status (1)
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639391A (en) * | 2018-07-06 | 2018-10-12 | 湖北三江航天红林探控有限公司 | Gas generator for quick start |
| CN109357256A (en) * | 2018-10-31 | 2019-02-19 | 北京动力机械研究所 | A kind of igniter for ram rocket type heater |
| CN109883621A (en) * | 2018-12-21 | 2019-06-14 | 西安航天发动机有限公司 | A kind of telescoping structure sealing position leak rate detection method |
| CN110700967A (en) * | 2019-09-03 | 2020-01-17 | 陕西蓝箭航天技术有限公司 | Liquid starter device and attitude control power system |
| CN113958426A (en) * | 2021-10-27 | 2022-01-21 | 西安航天动力研究所 | Thrust chamber scale test device |
| CN114439648A (en) * | 2021-12-31 | 2022-05-06 | 西安近代化学研究所 | Gunpowder starter suitable for engine secondary starting |
| CN114439649A (en) * | 2021-12-31 | 2022-05-06 | 西安近代化学研究所 | Gunpowder starter capable of effectively reducing occupied space |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108639391A (en) * | 2018-07-06 | 2018-10-12 | 湖北三江航天红林探控有限公司 | Gas generator for quick start |
| CN109357256A (en) * | 2018-10-31 | 2019-02-19 | 北京动力机械研究所 | A kind of igniter for ram rocket type heater |
| CN109883621A (en) * | 2018-12-21 | 2019-06-14 | 西安航天发动机有限公司 | A kind of telescoping structure sealing position leak rate detection method |
| CN110700967A (en) * | 2019-09-03 | 2020-01-17 | 陕西蓝箭航天技术有限公司 | Liquid starter device and attitude control power system |
| CN113958426A (en) * | 2021-10-27 | 2022-01-21 | 西安航天动力研究所 | Thrust chamber scale test device |
| CN114439648A (en) * | 2021-12-31 | 2022-05-06 | 西安近代化学研究所 | Gunpowder starter suitable for engine secondary starting |
| CN114439649A (en) * | 2021-12-31 | 2022-05-06 | 西安近代化学研究所 | Gunpowder starter capable of effectively reducing occupied space |
| CN114439648B (en) * | 2021-12-31 | 2024-04-30 | 西安近代化学研究所 | Gunpowder starter suitable for engine secondary starting |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106050476B (en) | 2018-06-05 |
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Inventor after: Lv Lei Inventor after: Zou Derong Inventor after: Yu Yongchun Inventor after: Cui Ruixi Inventor after: Zhang Hao Inventor after: Zhang Huayan Inventor after: Yan Liuliu Inventor after: Liu Songhua Inventor after: Yu Yao Inventor before: Lv Lei Inventor before: Yu Yongchun Inventor before: Cui Ruixi Inventor before: Zhang Hao |
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