CN114439648A - Gunpowder starter suitable for engine secondary starting - Google Patents
Gunpowder starter suitable for engine secondary starting Download PDFInfo
- Publication number
- CN114439648A CN114439648A CN202111669259.1A CN202111669259A CN114439648A CN 114439648 A CN114439648 A CN 114439648A CN 202111669259 A CN202111669259 A CN 202111669259A CN 114439648 A CN114439648 A CN 114439648A
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- China
- Prior art keywords
- engine
- main shell
- powder
- shell
- secondary starting
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- 239000007858 starting material Substances 0.000 title claims abstract description 34
- 239000003721 gunpowder Substances 0.000 title claims abstract description 16
- 239000000843 powder Substances 0.000 claims abstract description 31
- 238000002485 combustion reaction Methods 0.000 claims abstract description 22
- 238000009413 insulation Methods 0.000 claims abstract description 17
- 239000003814 drug Substances 0.000 claims description 32
- 239000007921 spray Substances 0.000 claims description 21
- 238000007789 sealing Methods 0.000 claims description 20
- 239000012528 membrane Substances 0.000 claims description 13
- 230000001154 acute effect Effects 0.000 claims description 3
- 239000002737 fuel gas Substances 0.000 abstract description 17
- 239000007788 liquid Substances 0.000 abstract description 17
- 239000002360 explosive Substances 0.000 abstract description 11
- 239000007789 gas Substances 0.000 description 4
- 239000007769 metal material Substances 0.000 description 4
- 239000004449 solid propellant Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 229910052755 nonmetal Inorganic materials 0.000 description 2
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 239000010949 copper Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000012634 fragment Substances 0.000 description 1
- 239000007770 graphite material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Images
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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Infusion, Injection, And Reservoir Apparatuses (AREA)
- Fire-Extinguishing By Fire Departments, And Fire-Extinguishing Equipment And Control Thereof (AREA)
Abstract
The invention discloses a gunpowder starter suitable for secondary starting of an engine, which comprises a shell, wherein the shell comprises a main shell and a nozzle base which are sequentially connected along the axial direction; the interior of the main shell and the nozzle base form a combustion chamber; an electric igniter is arranged at the axial front end of the main shell; according to the invention, the heat insulation pad is arranged between the main shell and the flange of the nozzle seat, so that part of the isolated external high-temperature fuel gas is conducted to the main shell through the nozzle seat; in addition, the first heat-insulating layer and the second heat-insulating layer are respectively arranged on the inner walls of the main shell and the nozzle seat, so that the temperature in the shell is ensured to be lower than the combustible temperature of the explosive column; finally, the invention arranges a baffle and a diaphragm at the outlet of the nozzle seat, and the effective areas of the diaphragm for breaking the diaphragm are different by arranging a plurality of through holes on the baffle; the technical problem that the powder starter for secondary starting burns earlier than the preset time in the first starting and working engineering of the liquid rocket engine due to the fact that high-temperature and high-pressure fuel gas cannot be isolated in the prior art is solved.
Description
Technical Field
The invention belongs to the technical field of liquid rocket engines, relates to a gunpowder starter, and particularly relates to a gunpowder starter suitable for secondary starting of an engine.
Background
The powder starter adopts solid propellant for charging, and uses the fuel gas generated by combustion of the solid propellant for providing initial power energy and working medium for starting the pumping pressure type liquid rocket engine, and has the characteristic of disposable use. With the development of aerospace application and deep space exploration, the carrier rocket adopting the liquid rocket engine shows a remarkable large capacity advantage and becomes a main carrier. In order to reduce the cost, a liquid rocket reuse technology is vigorously developed, and one of the key technologies is the secondary starting of a liquid rocket engine.
In order to realize the secondary starting of the liquid rocket engine, the liquid rocket engine needs to be provided with two powder starters which are respectively used for the primary starting and the secondary starting of the engine, and the two powder starters are installed in parallel physically and work in series in time sequence. When the powder starter started once works and an engine works, high-temperature and high-pressure fuel gas can be generated. The secondary starting powder starter needs to bear the action of the high-temperature and high-pressure fuel gas in the whole process of primary starting and stable working of the engine.
The existing gunpowder starter does not consider the requirement of a liquid rocket engine for secondary starting, is lack of design in the aspect of bearing long-time high-temperature and high-pressure fuel gas, and the Chinese patent with application publication number CN 112502858A discloses a gunpowder starter which is suitable for long-term storage, a bowl-shaped sealing element is adopted between a spray pipe and a shell, the problem of sealing capability of long-term storage is mainly solved, and the Chinese patent with application publication number CN 112160851A discloses a high-sealing low-combustion-temperature detachable gunpowder starter, an inner cavity of the gunpowder starter is isolated from the external environment by adopting an isolating device, the consistency of the natural environment and the ground environment when the gunpowder starter is ignited is ensured, and the problem of sealing property is still solved essentially.
If no design measure for effectively isolating high-temperature and high-pressure gas exists, the external gas can damage the sealing structure at the spray pipe to enter the cavity of the combustion chamber, and meanwhile, the high temperature can be conducted to the whole combustion chamber along the metal shell, so that the solid propellant is initiated to be combusted earlier than the preset time, the working time sequence of the liquid rocket engine is damaged, the secondary starting function cannot be realized, and the working condition of primary starting can also be influenced.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a powder starter suitable for secondary starting of an engine, and solve the technical problem that the powder starter for secondary starting burns earlier than a preset time in the first starting and working engineering of a liquid rocket engine because high-temperature and high-pressure fuel gas cannot be isolated in the prior art.
In order to solve the technical problems, the invention adopts the following technical scheme:
the gunpowder starter suitable for the secondary starting of the engine comprises a shell, wherein the shell comprises a main shell and a nozzle base which are sequentially connected along the axial direction; the interior of the main shell and the nozzle base forms a combustion chamber;
an electric igniter is arranged at the axial front end of the main shell; the inner wall of the main shell is provided with a first heat insulation layer, and the inner wall of the spray pipe seat is provided with a second heat insulation layer; a heat insulation pad is arranged between the main shell and the nozzle seat;
an ignition medicine box support and a medicine baffle plate are arranged in the combustion chamber, the combustion chamber is divided into a first cavity, a second cavity and a third cavity by the ignition medicine box support and the medicine baffle plate, an ignition medicine box is fixedly arranged in the first cavity, and one side of the ignition medicine box is fixedly arranged on the ignition medicine box support; the other side of the ignition medicine box is tightly attached to the inner wall of the main shell; a powder column is axially arranged in the second cavity, one end of the powder column is connected with the ignition powder box bracket, and the other end of the powder column is connected with the powder baffle plate;
the spray pipe is detachably arranged in the spray pipe seat, one end of the spray pipe is communicated with the third cavity, the other end of the spray pipe is sequentially provided with a baffle and a diaphragm which are fixedly connected along the axial direction, and the baffle and the diaphragm are fixedly arranged on the inner wall of the spray pipe seat; the baffle is provided with a plurality of through holes.
The invention also comprises the following technical features:
the main shell and the nozzle base are connected in a matching mode through flanges and fasteners, and the heat insulation pad is arranged between the flanges.
A first sealing ring is arranged between the main shell and the electric igniter; and a second sealing ring is arranged between the flanges.
The electric igniter and the axial direction of the main shell form an included angle alpha, and the included angle alpha is an acute angle.
The axial included angle alpha between the electric igniter and the total shell is 15-30 degrees.
The fastener comprises a self-locking nut and a bolt.
And a compensation gasket is arranged between the ignition medicine box bracket and the medicine column.
A buffer cushion is arranged between the explosive column and the explosive baffle plate.
And notches carved with a shape like a Chinese character 'mi' are arranged on one side of the membrane close to the outlet of the nozzle holder.
The baffle and the diaphragm are both concave.
Compared with the prior art, the invention has the beneficial technical effects that:
(1) according to the invention, the heat insulation pad is arranged between the main shell and the flange of the nozzle seat, so that part of the isolated external high-temperature fuel gas is conducted to the main shell through the nozzle seat; in addition, the first heat-insulating layer and the second heat-insulating layer are respectively arranged on the inner walls of the main shell and the nozzle seat, so that heat conducted by external high-temperature fuel gas through the main shell and the nozzle seat is effectively isolated, and the temperature in the main shell is ensured to be lower than the combustible temperature of the explosive column; finally, the baffle and the membrane are arranged at the outlet of the nozzle seat, and the membrane breaking effective areas of the membrane are different by arranging a plurality of through holes on the baffle, so that the fuel gas generated when the liquid rocket engine is started and works for the first time can not break the membrane and enter a combustion chamber, and the fuel gas generated by the combustion of the explosive column can reliably open the membrane to spray out from the nozzle to do work when the liquid rocket engine is started for the second time; the technical problem that the powder starter for secondary starting burns earlier than the preset time in the first starting and working engineering of the liquid rocket engine due to the fact that high-temperature and high-pressure fuel gas cannot be isolated in the prior art is solved.
(2) The stop block and the diaphragm are fixedly arranged on the inner wall of the nozzle base, so that the combustion chamber is isolated from the outside, external gas cannot enter the combustion chamber, and the sealing property of the interior of the combustion chamber is ensured.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of the overall structure of the baffle plate of the present invention;
FIG. 3 is a schematic cross-sectional view of a baffle plate in the present invention;
FIG. 4 is a schematic view of an assembly structure of the diaphragm and the baffle according to the present invention;
FIG. 5 is a schematic view of the assembled structure of the diaphragm, the baffle plate and the nozzle holder of the present invention;
fig. 6 is a schematic structural view of the diaphragm of the present invention.
The meaning of the individual reference symbols in the figures is: 1-housing, 2-combustion chamber, 3-electric igniter, 4-first thermal insulation layer, 5-second thermal insulation layer, 6-thermal insulation pad, 7-ignition medicine box support, 8-medicine baffle, 9-ignition medicine box, 10-medicine column, 11-spray pipe, 12-baffle, 13-diaphragm, 14-through hole, 15-flange, 16-fastener, 17-first sealing ring, 18-second sealing ring, 19-compensation gasket, 20-buffer pad;
101-total shell, 102-nozzle seat;
201-a first cavity, 202-a second cavity, 203-a third cavity;
1601-self-locking nut, 1602-bolt.
The present invention will be explained in further detail with reference to examples.
Detailed Description
All parts in the present invention are those known in the art, unless otherwise specified.
The following embodiments of the present invention are provided, and it should be noted that the present invention is not limited to the following embodiments, and all equivalent changes based on the technical solutions of the present invention are within the protection scope of the present invention.
The invention provides a gunpowder starter suitable for secondary starting of an engine, which comprises a shell 1, wherein the shell 1 comprises a main shell 101 and a nozzle base 102 which are sequentially connected along the axial direction; the interior of the main housing 101 and the nozzle holder 102 forms a combustion chamber 2;
the axial front end of the general shell 101 is provided with an electric igniter 3; the inner wall of the main shell 101 is provided with a first heat insulation layer 4, and the inner wall of the spray pipe seat 102 is provided with a second heat insulation layer 5; a heat insulation pad 6 is arranged between the main shell 101 and the nozzle seat 102;
an ignition medicine box support 7 and a medicine baffle plate 8 are arranged in the combustion chamber 2, the combustion chamber 2 is divided into a first cavity 201, a second cavity 202 and a third cavity 203 by the ignition medicine box support 7 and the medicine baffle plate 8, an ignition medicine box 9 is fixedly arranged in the first cavity 201, and one side of the ignition medicine box 9 is fixedly arranged on the ignition medicine box support 7; the other side of the ignition medicine box 9 is tightly attached to the inner wall of the general shell 101; a powder column 10 is axially arranged in the second cavity 10, one end of the powder column 10 is connected with the ignition powder box bracket 7, and the other end is connected with the powder baffle plate 8;
a spray pipe 11 with one end communicated with the third cavity 203 is detachably arranged in the spray pipe seat 102, a baffle plate 12 and a diaphragm 13 which are fixedly connected are sequentially arranged at the other end of the spray pipe 11 along the axial direction, and the baffle plate 12 and the diaphragm 13 are fixedly arranged on the inner wall of the spray pipe seat 102; the baffle 12 is provided with a plurality of through holes 14.
In the technical scheme, the heat insulation pad is arranged between the main shell and the flange of the nozzle seat, so that part of the isolated external high-temperature fuel gas is conducted to the main shell through the nozzle seat; in addition, the first heat-insulating layer and the second heat-insulating layer are respectively arranged on the inner walls of the main shell and the nozzle seat, so that heat conducted by external high-temperature fuel gas through the main shell and the nozzle seat is effectively isolated, and the temperature in the main shell is ensured to be lower than the combustible temperature of the explosive column; finally, the baffle and the membrane are arranged at the outlet of the nozzle seat, and the membrane breaking effective areas of the membrane are different by arranging a plurality of through holes on the baffle, so that the fuel gas generated when the liquid rocket engine is started and works for the first time can not break the membrane and enter a combustion chamber, and the fuel gas generated by the combustion of the explosive column can reliably open the membrane to spray out from the nozzle to do work when the liquid rocket engine is started for the second time; the technical problem that the powder starter which cannot isolate high-temperature and high-pressure fuel gas to cause secondary starting in the prior art burns in the first starting and working engineering of the liquid rocket engine earlier than the preset time is solved.
Specifically, the main housing 101 and the nozzle base 102 are coupled by the flanges 15 and the fasteners 16, and the insulation blanket 6 is disposed between the flanges 15.
Specifically, a first sealing ring 17 is arranged between the main shell 101 and the electric igniter 3, a second sealing ring 18 is arranged between the flanges 15, the first sealing ring 17 can realize reliable sealing between the electric igniter 3 and the main shell 101 under the action of specified tightening torque, and the second sealing ring 18 can realize reliable sealing between the main shell 101 and the nozzle seat 102 and is high-temperature resistant.
The first sealing ring and the second sealing ring are made of flexible graphite materials or soft metal materials, and the soft metal materials include, but are not limited to, aluminum and copper.
Specifically, the electric igniter 3 and the axial direction of the main shell 101 form an included angle α, which is an acute angle, and compared with the electric igniter in the prior art, the size of the powder starter in the axial direction can be reduced compared with the electric igniter along the central axis of the front end socket in the same direction.
Specifically, the axial included angle alpha between the electric igniter 3 and the total shell 101 is 15-30 degrees, and the axial size of the powder starter can be reduced by 3-13 percent.
Specifically, the fastener 16 comprises a self-locking nut 1601 and a bolt 1602, and it is ensured that looseness cannot occur under the action of vibration, shock and impact load.
Specifically, a compensation gasket 19 is arranged between the ignition medicine box support 7 and the medicine column 10, so that the problem of mismatching of deformation of each component caused by environmental temperature change can be compensated.
The compensating pad is made of elastic non-metal material, such as aviation sponge rubber material.
Specifically, a buffer pad 20 is arranged between the explosive column 10 and the explosive baffle 8 to buffer the vibration, vibration and impact load between the explosive column 10 and the explosive baffle 8.
The cushion pad is made of elastic non-metal materials, such as aviation sponge rubber materials.
Specifically, the side of the diaphragm 13 close to the outlet of the nozzle holder 102 is provided with a nick engraved with a shape like a Chinese character 'mi', so that the diaphragm can be more easily broken by the gas in the combustion chamber.
Specifically, the baffle 12 and the diaphragm 13 are both in a concave shape, and the diaphragm is arranged in the concave shape, so that fragments can not fall off when the diaphragm is broken, and downstream parts are prevented from being damaged.
Claims (10)
1. A powder starter suitable for the secondary starting of an engine, comprising a housing (1), characterized in that the housing (1) comprises a main shell (101) and a nozzle holder (102) which are sequentially connected along the axial direction; the interior of the main shell (101) and the nozzle base (102) form a combustion chamber (2);
an electric igniter (3) is arranged at the axial front end of the main shell (101); a first heat insulation layer (4) is arranged on the inner wall of the main shell (101), and a second heat insulation layer (5) is arranged on the inner wall of the spray pipe seat (102); a heat insulation pad (6) is arranged between the main shell (101) and the nozzle seat (102);
an ignition medicine box support (7) and a medicine baffle plate (8) are arranged in the combustion chamber (2), the ignition medicine box support (7) and the medicine baffle plate (8) divide the combustion chamber (2) into a first cavity (201), a second cavity (202) and a third cavity (203), an ignition medicine box (9) is fixedly installed in the first cavity (201), and one side of the ignition medicine box (9) is fixedly installed on the ignition medicine box support (7); the other side of the ignition medicine box (9) is tightly attached to the inner wall of the main shell (101); a powder column (10) is axially arranged in the second cavity (10), one end of the powder column (10) is connected with the ignition powder box bracket (7), and the other end is connected with the powder baffle plate (8);
a spray pipe (11) with one end communicated with the third cavity (203) is detachably arranged in the spray pipe seat (102), a baffle plate (12) and a diaphragm (13) which are fixedly connected are sequentially arranged at the other end of the spray pipe (11) along the axial direction, and the baffle plate (12) and the diaphragm (13) are fixedly arranged on the inner wall of the spray pipe seat (102); the baffle (12) is provided with a plurality of through holes (14).
2. Gunpowder starter suitable for the secondary start of an engine as claimed in claim 1, wherein said main housing (101) and nozzle holder (102) are cooperatively connected by flanges (15) and fasteners (16), said insulating blanket (6) being disposed between said flanges (15).
3. A powder starter suitable for the secondary starting of an engine as claimed in claim 2, characterised in that a first sealing ring (17) is arranged between the main housing (101) and the electric igniter (3); and a second sealing ring (18) is arranged between the flanges (15).
4. Powder starter suitable for the secondary starting of an engine as claimed in claim 1, characterised in that the electric igniter (3) forms an angle α with the axial direction of the main housing (101), said angle α being acute.
5. Gunpowder starter suitable for the secondary starting of an engine as claimed in claim 4, wherein the angle α between the electric igniter (3) and the axial direction of the main housing (101) is 15 ° to 30 °.
6. A powder starter adapted for use in connection with the secondary start of an engine as set forth in claim 1, wherein said fastener (16) comprises a self-locking nut (1601) and bolt (1602).
7. Gunpowder starter suitable for the secondary starting of an engine as claimed in claim 1, wherein a shim (19) is provided between the ignition cartridge holder (7) and the charge (10).
8. Gunpowder starter suitable for the secondary starting of an engine as claimed in claim 1, characterised in that a buffer pad (20) is provided between the cartridge (10) and the baffle (8).
9. Powder starter suitable for the secondary starting of an engine, as in claim 1, characterized in that the side of the membrane (13) close to the outlet of the nozzle holder (102) is provided with notches engraved with the shape of a "mi".
10. Powder starter suitable for the secondary starting of an engine, as in claim 1, characterized in that said shutter (12) and said membrane (13) are both "concave".
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111669259.1A CN114439648B (en) | 2021-12-31 | 2021-12-31 | Gunpowder starter suitable for engine secondary starting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111669259.1A CN114439648B (en) | 2021-12-31 | 2021-12-31 | Gunpowder starter suitable for engine secondary starting |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114439648A true CN114439648A (en) | 2022-05-06 |
| CN114439648B CN114439648B (en) | 2024-04-30 |
Family
ID=81365277
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111669259.1A Active CN114439648B (en) | 2021-12-31 | 2021-12-31 | Gunpowder starter suitable for engine secondary starting |
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| Country | Link |
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| CN (1) | CN114439648B (en) |
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| CN112282971A (en) * | 2020-10-29 | 2021-01-29 | 西安航天动力研究所 | Solid gas starter for gas self-pressurization |
| CN112502858A (en) * | 2020-11-30 | 2021-03-16 | 西安航天动力研究所 | Gunpowder starter suitable for long-term storage |
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2021
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Also Published As
| Publication number | Publication date |
|---|---|
| CN114439648B (en) | 2024-04-30 |
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