CN114439648B - Gunpowder starter suitable for engine secondary starting - Google Patents
Gunpowder starter suitable for engine secondary starting Download PDFInfo
- Publication number
- CN114439648B CN114439648B CN202111669259.1A CN202111669259A CN114439648B CN 114439648 B CN114439648 B CN 114439648B CN 202111669259 A CN202111669259 A CN 202111669259A CN 114439648 B CN114439648 B CN 114439648B
- Authority
- CN
- China
- Prior art keywords
- spray pipe
- shell
- pipe seat
- main shell
- baffle
- 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.)
- Active
Links
- 239000007858 starting material Substances 0.000 title claims abstract description 31
- 239000003721 gunpowder Substances 0.000 title claims abstract description 19
- 239000007921 spray Substances 0.000 claims abstract description 44
- 238000009413 insulation Methods 0.000 claims abstract description 22
- 238000002485 combustion reaction Methods 0.000 claims abstract description 21
- 239000000843 powder Substances 0.000 claims description 22
- 238000007789 sealing Methods 0.000 claims description 19
- 239000012528 membrane Substances 0.000 claims description 17
- 239000003814 drug Substances 0.000 claims description 12
- 229940079593 drug Drugs 0.000 claims description 3
- 125000006850 spacer group Chemical group 0.000 claims description 2
- 239000007788 liquid Substances 0.000 abstract description 17
- 239000002360 explosive Substances 0.000 abstract description 4
- 239000002737 fuel gas Substances 0.000 description 10
- 239000007789 gas Substances 0.000 description 9
- 230000000903 blocking effect Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 239000004449 solid propellant Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000001154 acute effect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 230000035939 shock Effects 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
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
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 spray pipe seat which are sequentially connected along the axial direction; the total shell and the inner part of the spray pipe seat 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 spray pipe seat, so that high-temperature gas outside is partially isolated and conducted to the main shell through the spray pipe seat; in addition, the first heat insulation layer and the second heat insulation layer are respectively arranged on the inner walls of the main shell and the nozzle base, so that the temperature in the shell is ensured to be lower than the flammable temperature of the explosive column; finally, a baffle and a diaphragm are arranged at the outlet of the spray pipe seat, and a plurality of through holes are formed in the baffle, so that the effective areas of rupture of the diaphragm are different; the technical problem that a gunpowder starter for secondary starting is burnt earlier than a preset time in the primary starting and working engineering of a liquid rocket engine due to the fact that high-temperature high-pressure 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 gunpowder starter adopts solid propellant to charge, and fuel gas generated by combustion of the solid propellant is used for providing initial power energy and working medium for starting the pump-type liquid rocket engine, so that the solid propellant starter has the characteristic of disposable use. With the expansion of aerospace application and deep space exploration, a carrier rocket adopting a liquid rocket engine shows remarkable large capacity advantage and becomes a main carrier. In order to reduce the cost, a liquid rocket reuse technology is developed greatly, and one of the key technologies is secondary start of a liquid rocket engine.
In order to realize the secondary start of the liquid rocket engine, the liquid rocket engine needs to be provided with two gunpowder starters which are respectively used for the primary start and the secondary start of the engine, and the two gunpowder starters are arranged in parallel physically and work in series in time sequence. When the primary starting gunpowder starter works and the engine works, high-temperature and high-pressure fuel gas can be generated. The secondary starting gunpowder starter needs to bear the actions of the high-temperature high-pressure fuel gas in the whole process when the engine is started at one time and works stably.
The prior art powder starter does not consider the secondary starting requirement of a liquid rocket engine, lacks design in the aspect of bearing high temperature and high pressure gas for a long time, the Chinese patent application publication No. CN 112502858A discloses a powder starter suitable for long-term storage, a bowl-shaped sealing piece is adopted between a spray pipe and a shell, the problem of sealing capacity of long-term storage is mainly solved, the Chinese patent application publication No. CN 112160851A discloses a high-sealing low-combustion-temperature detachable powder starter, an inner cavity of the powder starter is isolated from the external environment by adopting an isolating device, the consistency of the environment of the powder starter when in ignition is ensured, and the problem of sealing performance is basically solved.
If no design measures for effectively isolating high-temperature high-pressure fuel gas exist, the outside fuel gas can destroy the sealing structure at the spray pipe to enter 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 charge for combustion before the preset time, the working time sequence of the liquid rocket engine is destroyed, the secondary starting function cannot be realized, and the working condition of primary starting can be influenced.
Disclosure of Invention
Aiming at the defects existing in the prior art, the invention aims to provide a gunpowder starter suitable for secondary starting of an engine, which solves the technical problem that the gunpowder starter for secondary starting burns earlier than a preset time in the primary starting and working engineering of a liquid rocket engine because high-temperature high-pressure 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 spray pipe seat which are sequentially connected along the axial direction; the total shell and the inner part of the spray pipe seat form a combustion chamber;
An electric igniter is arranged at the axial front end of the main shell; a first heat insulation layer is arranged on the inner wall of the main shell, and a second heat insulation layer is arranged on the inner wall of the nozzle seat; a heat insulation pad is arranged between the main shell and the spray pipe seat;
The ignition powder box is fixedly arranged in the first cavity, and one side of the ignition powder box is fixedly arranged on the ignition powder box bracket; the other side of the ignition cartridge is tightly attached to the inner wall of the main shell; a grain is axially arranged in the second cavity, one end of the grain is connected with the ignition medicine box bracket, and the other end of the grain is connected with the medicine blocking plate;
The inside of the spray pipe seat is detachably provided with a spray pipe with one end 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 plate is provided with a plurality of through holes.
The invention also comprises the following technical characteristics:
the main shell is connected with the spray pipe seat in a matched manner 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 forms an included angle alpha with the axial direction of the total shell, and the included angle alpha is an acute angle.
The value of the included angle alpha between the electric igniter and the axial direction of 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 cartridge support and the explosive column.
A buffer cushion is arranged between the grain and the medicine baffle.
One side of the membrane, which is close to the outlet of the nozzle seat, is provided with a notch carved with a shape like a Chinese character 'mi'.
The baffle and the membrane 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 spray pipe seat, so that high-temperature gas outside is partially isolated and conducted to the main shell through the spray pipe seat; in addition, the first heat insulation layer and the second heat insulation layer are respectively arranged on the inner walls of the main shell and the spray pipe seat, so that heat conducted by external high-temperature fuel gas through the main shell and the spray pipe seat is effectively isolated, and the temperature in the shell is ensured to be lower than the flammable temperature of the explosive column; finally, the baffle plate and the membrane are arranged at the outlet of the spray pipe seat, and the membrane rupture effective areas of the membrane are different through the plurality of through holes arranged on the baffle plate, so that the gas generated during the first starting and working of the liquid rocket engine is ensured not to break through the membrane and enter the combustion chamber, and the gas generated during the second starting of the liquid rocket engine and the combustion of the grain can reliably open the membrane to spray out from the spray pipe for doing work; the technical problem that a gunpowder starter for secondary starting is burnt earlier than a preset time in the primary starting and working engineering of a liquid rocket engine due to the fact that high-temperature high-pressure gas cannot be isolated in the prior art is solved.
(2) According to the invention, the stop block and the diaphragm are fixedly arranged on the inner wall of the nozzle seat, so that the combustion chamber is isolated from the outside, external fuel gas cannot enter the combustion chamber, and the tightness of the combustion chamber is ensured.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a schematic view of the overall structure of the baffle plate in the present invention;
FIG. 3 is a schematic cross-sectional view of a baffle in accordance with the present invention;
FIG. 4 is a schematic diagram of an assembly structure of a diaphragm and a baffle plate according to the present invention;
FIG. 5 is a schematic view of the assembled structure of the diaphragm, baffle and nozzle mount of the present invention;
FIG. 6 is a schematic diagram of a membrane according to the present invention.
The meaning of each reference numeral in the figures is: 1-shell, 2-combustion chamber, 3-electric igniter, 4-first heat insulation layer, 5-second heat insulation layer, 6-heat insulation pad, 7-ignition cartridge support, 8-baffle, 9-ignition cartridge, 10-cartridge, 11-jet pipe, 12-baffle, 13-diaphragm, 14-through hole, 15-flange, 16-fastener, 17-first sealing ring, 18-second sealing ring, 19-compensation pad, 20-cushion pad;
101-a main shell, 102-a nozzle base;
201-first cavity, 202-second cavity, 203-third cavity;
1601-self-locking nut, 1602-bolt.
The following examples illustrate the invention in further detail.
Detailed Description
All parts in the present invention are known in the art, unless otherwise specified.
The following specific embodiments of the present application are provided, and it should be noted that the present application is not limited to the following specific embodiments, and all equivalent changes made on the basis of the technical scheme of the present application fall within the protection scope of the present application.
The invention provides a gunpowder starter suitable for secondary starting of an engine, which is shown in fig. 1 to 6, and comprises a shell 1, wherein the shell 1 comprises a main shell 101 and a spray pipe seat 102 which are sequentially connected along the axial direction; the interior of the main housing 101 and the nozzle block 102 form a combustion chamber 2;
the axial front end of the main 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 spray pipe seat 102;
An ignition cartridge support 7 and a medicine blocking 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 cartridge support 7 and the medicine blocking plate 8, an ignition cartridge 9 is fixedly arranged in the first cavity 201, and one side of the ignition cartridge 9 is fixedly arranged on the ignition cartridge support 7; the other side of the ignition cartridge 9 is tightly attached to the inner wall of the main shell 101; a grain 10 is axially arranged in the second cavity 10, one end of the grain 10 is connected with the ignition medicine box bracket 7, and the other end is connected with the medicine blocking 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 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 12 and the diaphragm 13 are fixedly arranged on the inner wall of the spray pipe seat 102; the baffle plate 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 spray pipe seat, so that external high-temperature fuel gas is partially isolated and conducted to the main shell through the spray pipe seat; in addition, the first heat insulation layer and the second heat insulation layer are respectively arranged on the inner walls of the main shell and the spray pipe seat, so that heat conducted by external high-temperature fuel gas through the main shell and the spray pipe seat is effectively isolated, and the temperature in the shell is ensured to be lower than the flammable temperature of the explosive column; finally, the baffle plate and the membrane are arranged at the outlet of the spray pipe seat, and the membrane rupture effective areas of the membrane are different through the plurality of through holes arranged on the baffle plate, so that the gas generated during the first starting and working of the liquid rocket engine is ensured not to break through the membrane and enter the combustion chamber, and the gas generated during the second starting of the liquid rocket engine and the combustion of the grain can reliably open the membrane to spray out from the spray pipe for doing work; the technical problem that a gunpowder starter which cannot isolate high-temperature high-pressure gas to cause secondary starting in the prior art burns earlier than a preset time in the primary starting and working engineering of a liquid rocket engine is solved.
Specifically, the main housing 101 and the nozzle holder 102 are cooperatively connected by the flange 15 and the fastener 16, and the heat insulating mat 6 is disposed between the flanges 15.
Specifically, a first sealing ring 17 is arranged between the main casing 101 and the electric igniter 3, a second sealing ring 18 is arranged between the flanges 15, under the action of a specified tightening torque, the first sealing ring 17 can realize reliable sealing between the electric igniter 3 and the main casing 101, and the second sealing ring 18 can realize reliable sealing between the main casing 101 and the nozzle seat 102 and is resistant to high temperature.
The first sealing ring and the second sealing ring are made of flexible graphite materials or soft metal materials, and the soft metal materials comprise, but are not limited to, aluminum and copper.
Specifically, the electric igniter 3 forms an included angle α with the axial direction of the main housing 101, and the included angle α is an acute angle, so that compared with the electric igniter in the prior art, the electric igniter in the same direction along the central axis of the front end socket can reduce the axial size of the powder starter.
Specifically, the value of the included angle alpha between the electric igniter 3 and the axial direction of the main shell 101 is 15-30 degrees, and the size of the gunpowder starter in the axial direction can be reduced by 3-13%.
Specifically, the fastener 16 includes a self-locking nut 1601 and a bolt 1602 to ensure that loosening does not occur under vibration, shock, or impact loads.
Specifically, a compensation spacer 19 is arranged between the ignition cartridge support 7 and the grain 10, so that the problem of mismatching of deformation of each component caused by environmental temperature change can be compensated.
The compensation gasket is made of elastic nonmetallic materials, such as aviation sponge rubber materials.
Specifically, a cushion pad 20 is provided between the grain 10 and the drug baffle 8 to cushion vibration, shock and impact load between the grain 10 and the drug baffle 8.
The cushion pad is made of elastic nonmetallic materials, such as aviation sponge rubber materials.
Specifically, the membrane 13 is provided with a notch carved with a shape like a Chinese character 'mi' on one side close to the outlet of the nozzle seat 102, so that the membrane can be more easily broken through by the fuel gas of the combustion chamber.
Specifically, the baffle 12 and the diaphragm 13 are both concave, and the diaphragm is arranged in a concave shape, so that fragments cannot fall off when the diaphragm is broken, and damage to downstream components is avoided.
Claims (6)
1. The gunpowder starter suitable for the secondary starting of the engine comprises a shell (1), and is characterized in that the shell (1) comprises a main shell (101) and a spray pipe seat (102) which are sequentially connected along the axial direction; the total shell (101) and the inner part of the spray pipe seat (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 spray pipe seat (102);
The ignition powder box is characterized in that an ignition powder box support (7) and a powder 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 powder box support (7) and the powder baffle plate (8), an ignition powder box (9) is fixedly arranged in the first cavity (201), and one side of the ignition powder box (9) is fixedly arranged on the ignition powder box support (7); the other side of the ignition cartridge (9) is tightly attached to the inner wall of the main shell (101); a grain (10) is axially arranged in the second cavity (10), one end of the grain (10) is connected with the ignition medicine box bracket (7), and the other end is connected with the medicine baffle (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 (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 (12) and the diaphragm (13) are fixedly arranged on the inner wall of the spray pipe seat (102); the baffle plate (12) is provided with a plurality of through holes (14);
one side of the membrane (13) close to the outlet of the nozzle seat (102) is provided with a notch carved with a shape like a Chinese character 'mi'; the baffle (12) and the membrane (13) are both concave;
The value of the included angle alpha between the axial direction of the electric igniter (3) and the axial direction of the total shell (101) is 15-30 degrees.
2. A powder starter for engine secondary starting as defined in claim 1, wherein said main housing (101) and nozzle block (102) are cooperatively connected by means of flanges (15) and fasteners (16), said heat insulating mat (6) being disposed between said flanges (15).
3. A powder starter suitable for engine secondary starting as claimed in claim 2, characterized in that a first sealing ring (17) is arranged between the main housing (101) and the electric igniter (3); a second sealing ring (18) is arranged between the flanges (15).
4. A powder starter for engine restart as in claim 2 wherein the fastener (16) comprises a self-locking nut (1601) and a bolt (1602).
5. A powder starter for engine secondary starting as claimed in claim 1, characterized in that a compensating spacer (19) is arranged between the cartridge holder (7) and the cartridge (10).
6. A powder starter for engine secondary starting according to claim 1, characterized in that a cushion (20) is arranged between the cartridge (10) and the drug stop plate (8).
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 CN114439648A (en) | 2022-05-06 |
| CN114439648B true 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114439648B (en) |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4999997A (en) * | 1985-11-18 | 1991-03-19 | Thiokol Corporation | Radial pulse motor igniter-sustain grain |
| WO2000015549A1 (en) * | 1998-09-14 | 2000-03-23 | Congxiao Li | A self-heating methanol cracker |
| JP2005171970A (en) * | 2003-12-15 | 2005-06-30 | Nof Corp | Two-stage thrust type rocket motor |
| KR20130054744A (en) * | 2011-11-17 | 2013-05-27 | 국방과학연구소 | Temperature sensing initiator, temperature sensing auto-initiated igniter and aircraft having the same |
| CN203349268U (en) * | 2013-06-17 | 2013-12-18 | 刘树平 | Liquid fuel heating gasification combustion engine |
| CN103967653A (en) * | 2014-04-28 | 2014-08-06 | 北京航空航天大学 | Axial injection end combustion solid-liquid rocket engine structure |
| CN105527370A (en) * | 2015-11-03 | 2016-04-27 | 西北工业大学 | Apparatus for simulating insulation ablation under condition of particle deposition in cavity in back wall of submerged nozzle |
| CN106050476A (en) * | 2016-07-11 | 2016-10-26 | 湖北三江航天江河化工科技有限公司 | Liquid-propellant rocket engine ignition device and ignition method thereof |
| CN107044362A (en) * | 2016-12-07 | 2017-08-15 | 西安近代化学研究所 | A kind of low plumage flame feature engine |
| CN107269424A (en) * | 2017-07-25 | 2017-10-20 | 南京理工大学 | A kind of solid propellant rocket regnition structure |
| CN109595099A (en) * | 2018-11-19 | 2019-04-09 | 西北工业大学 | Hybrid motor is used in a kind of ground run experiment |
| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
| CN112160851A (en) * | 2020-09-24 | 2021-01-01 | 西安航天动力研究所 | High-sealing low-combustion-temperature detachable gunpowder starter |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090205313A1 (en) * | 2008-02-14 | 2009-08-20 | Cavalleri Robert J | Fast Response Solid Fuel Rocket Motor |
-
2021
- 2021-12-31 CN CN202111669259.1A patent/CN114439648B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4999997A (en) * | 1985-11-18 | 1991-03-19 | Thiokol Corporation | Radial pulse motor igniter-sustain grain |
| WO2000015549A1 (en) * | 1998-09-14 | 2000-03-23 | Congxiao Li | A self-heating methanol cracker |
| JP2005171970A (en) * | 2003-12-15 | 2005-06-30 | Nof Corp | Two-stage thrust type rocket motor |
| KR20130054744A (en) * | 2011-11-17 | 2013-05-27 | 국방과학연구소 | Temperature sensing initiator, temperature sensing auto-initiated igniter and aircraft having the same |
| CN203349268U (en) * | 2013-06-17 | 2013-12-18 | 刘树平 | Liquid fuel heating gasification combustion engine |
| CN103967653A (en) * | 2014-04-28 | 2014-08-06 | 北京航空航天大学 | Axial injection end combustion solid-liquid rocket engine structure |
| CN105527370A (en) * | 2015-11-03 | 2016-04-27 | 西北工业大学 | Apparatus for simulating insulation ablation under condition of particle deposition in cavity in back wall of submerged nozzle |
| CN106050476A (en) * | 2016-07-11 | 2016-10-26 | 湖北三江航天江河化工科技有限公司 | Liquid-propellant rocket engine ignition device and ignition method thereof |
| CN107044362A (en) * | 2016-12-07 | 2017-08-15 | 西安近代化学研究所 | A kind of low plumage flame feature engine |
| CN107269424A (en) * | 2017-07-25 | 2017-10-20 | 南京理工大学 | A kind of solid propellant rocket regnition structure |
| CN109595099A (en) * | 2018-11-19 | 2019-04-09 | 西北工业大学 | Hybrid motor is used in a kind of ground run experiment |
| CN111122767A (en) * | 2019-11-29 | 2020-05-08 | 南京理工大学 | Detachable solid rocket engine jet pipe throat lining ablation test device |
| CN112160851A (en) * | 2020-09-24 | 2021-01-01 | 西安航天动力研究所 | High-sealing low-combustion-temperature detachable gunpowder starter |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114439648A (en) | 2022-05-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109595099B (en) | Solid-liquid mixing engine for ground test car experiment | |
| CN107269424B (en) | Secondary ignition structure of solid rocket engine | |
| CN104975985A (en) | Solid rocket engine igniting test device | |
| CN110749536B (en) | Solid rocket engine thermal protection material ablation experimental device | |
| CN106050476A (en) | Liquid-propellant rocket engine ignition device and ignition method thereof | |
| CN112160851A (en) | High-sealing low-combustion-temperature detachable gunpowder starter | |
| CN114439648B (en) | Gunpowder starter suitable for engine secondary starting | |
| CN110985237A (en) | Connecting and fixing device for failure at high temperature based on memory alloy technology and application method | |
| CN112502858A (en) | Gunpowder starter suitable for long-term storage | |
| CN111502859B (en) | Initiating explosive-free gas-solid hybrid rocket engine | |
| CN111927652B (en) | Double-pulse solid rocket engine interlayer ablation carbonization controllable experimental device | |
| CN111022217B (en) | Interstage isolation and conduction device for double-pulse igniter | |
| CN110596180B (en) | Ablation simulation fixing device for engine interstage protective material | |
| CN110566367B (en) | Combustion chamber for reducing interlayer strain of double-pulse solid engine | |
| CN115142981A (en) | Solid rocket engine without heat insulation structure | |
| CN114320667A (en) | Extrusion type oxidant supply solid-liquid mixing engine | |
| KR101063793B1 (en) | Promotion Organization | |
| CN217176759U (en) | High-temperature-resistant anti-vibration structure of ignition electric nozzle | |
| CN113958424B (en) | Rocket boosting engine with inner trajectory curve free of tail warping phenomenon | |
| RU2076937C1 (en) | Solid-propellant rocker engine | |
| CN217602792U (en) | Solid rocket engine without heat insulation structure | |
| CN215057795U (en) | Solid gas generator | |
| CN110595782A (en) | Shaft-diameter mixed double-pulse soft interlayer work simulation device | |
| CN216240964U (en) | Electric nozzle mounting structure for aircraft engine | |
| CN220912131U (en) | Unmanned miniaturized flaming device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant |