CN105715409A - Annular solid-liquid catalytic ignition engine - Google Patents
Annular solid-liquid catalytic ignition engine Download PDFInfo
- Publication number
- CN105715409A CN105715409A CN201610022559.3A CN201610022559A CN105715409A CN 105715409 A CN105715409 A CN 105715409A CN 201610022559 A CN201610022559 A CN 201610022559A CN 105715409 A CN105715409 A CN 105715409A
- Authority
- CN
- China
- Prior art keywords
- solid
- spray gap
- annular
- liquid catalytic
- catalytic ignition
- 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.)
- Pending
Links
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
- F02K9/72—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid and solid propellants, i.e. hybrid rocket-engine plants
-
- 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
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/85—Starting
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/99—Ignition, e.g. ignition by warming up of fuel or oxidizer in a resonant acoustic cavity
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
The invention discloses an annular solid-liquid catalytic ignition engine. The annular solid-liquid catalytic ignition engine comprises an injector, a solid powder grain, a heat insulating layer, a catalytic net and an ignition engine shell, wherein an injection seam is formed in the injector in the circumferential direction; the catalytic net is laid at an inlet of the injection seam; thus, an oxidizing agent is fed from an oxidizing agent channel of a shell of the ignition engine, enters an annular flow path in the shell of the ignition engine, and then is catalytically decomposed through the catalytic net to generate high-temperature oxygen enriched gas; the high-temperature oxygen enriched gas is injected into a combustion chamber of the ignition engine via the injection seam, and reacts with the solid powder grain to form high-temperature fuel gas; and the high-temperature fuel gas enters the combustion chamber of the main engine via an opening formed in the heat insulating layer to ignite the main engine. The annular solid-liquid catalytic ignition engine is easy to mount, small in size and convenient to machine, can directly replace a solid powder box to be used for ignition starting of a solid-liquid rocket engine, is easily integrated to a pre-combustion chamber of the engine, and is convenient to use and good in safety.
Description
Technical field
The invention belongs to rocket engine and start field, relate to a kind of annular solid-liquid catalytic ignition electromotor, for the ignition trigger of rocket engine, be particularly suited for the repeatedly ignition trigger of solid-liquid rocket.
Background technology
Solid-liquid rocket adopts liquid oxidizer and solid fuel, structurally have both the common feature of liquid-propellant rocket engine and solid propellant rocket, have that safety is good, thrust regulates easily, the feature of environmental protection is good, powder column good stability, temperature sensitivity are low and the advantage such as good economy performance, can be used for sounding rocket, target missile, tactical missile etc..
Solid-liquid rocket getting up early adopts the hypergolic propellants combination of nitrose oxidant, but owing to energy is not high, the solid-liquid rocket of Today, most, the physical contact of fuel and oxidant is all inertia, and engine start needs igniting.
Hydrogen peroxide is used as rocket engine oxidant, has nontoxic, pollution-free, high density, easily storage, high specific heat, decomposition produce the advantage of big volumetric expansion and heat, are a kind of desirable green propellants.Solid-liquid rocket and hydrogen peroxide oxidant with the use of conventional end hydroxy butadiene (HTPB), high density polyethylene (HDPE) (HDPE), lucite (PMMA) etc..
The ignition schemes that hydrogen peroxide solid-liquid rocket is conventional has: catalytic ignition, and solid medicine box is lighted a fire, and sprays into hypergolic propellants igniting, and igniter motor is lighted a fire.
It is long that catalytic ignition has ignition delay time, and total punching loss is big, and after successful ignition, catalytic bed, still in duty, affects the working life of catalytic bed in test.Catalytic ignition droop loss is big, increases tank pressure for pressure-feed system, increases mass of system.Current catalytic ignition technology, for the restriction of catalytic bed material, is not suitable for high-strength hydrogen peroxide.
Solid medicine box is lighted a fire, poor stability, it is impossible to realizing repeatedly starting, medicine box needs to do thermal protection in front combustion indoor, and medicine box metal part easily comes off and jet pipe causes potential danger.
Suck hypergolic propellants ignition system complicated, it is necessary to extra propellant feed system.
Summary of the invention
In order to solve the problems referred to above, the present invention proposes a kind of annular solid-liquid catalytic ignition electromotor as igniter motor, including ejector filler, system for solid rocket grain, heat insulation layer, catalysis net and igniter motor shell.
Wherein, in ejector filler circumference, uniform Design has fan-shaped spray gap A；The arrival end of each spray gap A is equipped with catalysis net.The system for solid rocket grain of loop configuration it is coaxially arranged with inside ejector filler；The design of system for solid rocket grain circumference has the fan-shaped spray gap B equal with spray gap A quantity on ejector filler, and each spray gap B connects with spray gap A respectively.System for solid rocket grain is internally provided with the heat insulation layer of loop configuration；In heat insulation layer outer wall circumference, uniform Design has perforate.Igniter motor shell is arranged on outside ejector filler, and inwall is fitted with ejector filler outer wall；Having oxidant channel and annular channel, oxidant channel and annular channel on igniter motor shell, each fan-shaped spray gap A connects with annular channel simultaneously.
Oxidant passes into from the oxidant channel igniter motor shell, enter igniting engine housing annular runner, carry out catalytic decomposition by catalysis net subsequently and produce rich, high temperature combustion gas body, via each fan-shaped spray gap A, gas is accelerated, it is injected into igniter motor combustor, lights system for solid rocket grain, form high-temperature fuel gas, enter sustainer chamber via the circumferentially distributed perforate of heat insulation layer, light sustainer.
It is an advantage of the current invention that:
1, annular solid-liquid catalytic ignition electromotor of the present invention, igniter motor adopts catalytic ignition, it is easy to accomplish repeatedly light a fire, it is possible to repeatedly start sustainer；
2, annular solid-liquid catalytic ignition electromotor of the present invention is installed easily, and volume is little, it is possible to directly substitute the solid medicine box ignition trigger for solid-liquid rocket；
3, annular solid-liquid catalytic ignition electromotor of the present invention, adopts hydrogen peroxide as oxidant, and igniter motor directly uses sustainer oxidant, it is not necessary to additionally build igniter motor induction system；
4, in annular solid-liquid catalytic ignition electromotor of the present invention, catalysis net, ejector filler, powder column, all adopt loop configuration, compact conformation, easy to process, it is easy to be integrated into combustion room before electromotor, easy to use；
5, annular solid-liquid catalytic ignition electromotor of the present invention, simple in construction, cost are low, safety good.
Accompanying drawing explanation
Fig. 1 is annular solid-liquid catalytic ignition engine structure schematic diagram of the present invention；
Fig. 2 is catalysis net and spray spray gap partial enlarged drawing in part A in accompanying drawing 1.
In figure:
1-ejector filler 2-system for solid rocket grain 3-heat insulation layer 4-catalysis net
5-igniter motor shell 101-spray gap A201-spray gap B301-perforate
501-oxidant channel 502-annular channel
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described further.
Annular solid-liquid catalytic ignition electromotor of the present invention, as igniter motor, including ejector filler 1, system for solid rocket grain 2, heat insulation layer 3, catalysis net 4 and igniter motor shell 5.
Wherein, ejector filler 1 adopts rustless steel to make, it is designed as ring-like clearance type ejector filler, concrete structure is: the fan-shaped spray gap A101 that the upper uniform Design of ejector filler 1 circumference has 80 degree or 6 radians of 4 radians to be 50 degree, spray gap A101 designs along ejector filler 1 middle section, through ejector filler 1 outboard sidewalls.The width of above-mentioned spray gap A101 is 0.1mm, and the arrival end of spray gap A101 is designed as 120 degree of contraction mouths, and outlet is 15 degree of extension mouths, is conducive to the acceleration of propellant and uniform.The arrival end of each spray gap A101 is equipped with catalysis net 4, is blocked by spray gap A101 arrival end by catalysis net 4.Catalysis net 4 can be fixedly mounted on ejector filler 1 outer wall in the groove offered.
The internal system for solid rocket grain 2 being coaxially arranged with loop configuration of ejector filler 1, system for solid rocket grain 2 outer wall and the laminating of ejector filler 1 inwall circumference.System for solid rocket grain 2 circumference design has the fan-shaped spray gap B201 equal with spray gap A101 quantity on ejector filler 1, and each spray gap B connects with spray gap A respectively, the width width more than spray gap A.Above-mentioned system for solid rocket grain 2 adopts high density polyethylene (HDPE), and polyethylene cost is low, and machining property is good, it is easy to be processed into variously-shaped.
System for solid rocket grain 2 is internally provided with the heat insulation layer 3 of loop configuration, and combustion gas heat insulation for igniter motor enters sustainer chamber.Heat insulation layer 3 outer wall circumference designs fluted, both circumferentially go up the perforate 301 that uniform Design has 15 diameters to be 1.5mm, the through groove floor in perforate 301 two ends and heat insulation layer 3 inwall.Above-mentioned heat insulation layer 3 adopts heat insulation ablation resistant material, as: high silica material, igniter motor powder column polyethylene temperature thus can be avoided too high, ensure igniter motor reliably working, it is achieved igniter motor repeatedly starts.
Described igniter motor shell 5 adopts rustless steel to make, and is arranged on outside ejector filler 1, and inwall is fitted with ejector filler 1 outer wall.Igniter motor shell 5 has oxidant channel 501 and annular channel 502, oxidant channel 501 and annular channel 502, makes catalysis net 4 be positioned at annular channel 502 simultaneously, make each fan-shaped spray gap A101 connect with annular channel 502.
Annular solid-liquid catalytic ignition electromotor of the present invention adopts 90% hydrogen peroxide as oxidant, and high density polyethylene (HDPE) (HDPE) is as fuel.Oxidant passes into from the oxidant channel 501 igniter motor shell 5, enter igniting engine housing annular runner, carry out catalytic decomposition by catalysis net 4 subsequently and produce high-temperature oxygen-enriched gas, via each fan-shaped spray gap A101, gas is accelerated, it is injected into igniter motor combustor, lights system for solid rocket grain 2, form high-temperature fuel gas, enter sustainer chamber via the circumferentially distributed perforate of heat insulation layer 3, light sustainer.
Patent annular solid-liquid catalytic ignition electromotor of the present invention is easily achieved repeatedly lights a fire, and after ignition path engine ignition 5s, opens sustainer supply, lights system for solid rocket grain 2 under the effect of igniter motor combustion gas, and system for solid rocket grain 2 is lighted rear igniter motor and quit work.Owing to the igniter motor single igniting catalysis net working time is short, igniting flow is little, therefore is easily achieved sustainer and repeatedly lights a fire, and is made directly catalytic ignition compared to sustainer oxidant, has big advantage.
Claims (7)
1. an annular solid-liquid catalytic ignition electromotor, it is characterised in that: include ejector filler, system for solid rocket grain, heat insulation layer, catalysis net and igniter motor shell；
Wherein, in ejector filler circumference, uniform Design has fan-shaped spray gap A；The arrival end of each spray gap A is equipped with catalysis net；The system for solid rocket grain of loop configuration it is coaxially arranged with inside ejector filler；The design of system for solid rocket grain circumference has the fan-shaped spray gap B equal with spray gap A quantity on ejector filler, and each spray gap B connects with spray gap A respectively；System for solid rocket grain is internally provided with the heat insulation layer of loop configuration；In heat insulation layer outer wall circumference, uniform Design has perforate；Igniter motor shell is arranged on outside ejector filler, and inwall is fitted with ejector filler outer wall；Having oxidant channel and annular channel, oxidant channel and annular channel on igniter motor shell, each fan-shaped spray gap A connects with annular channel simultaneously.
2. as claimed in claim 1 a kind of annular solid-liquid catalytic ignition electromotor, it is characterised in that: spray gap is 4 radians is the fan-shaped spray gap A of 80 degree.
3. as claimed in claim 1 a kind of annular solid-liquid catalytic ignition electromotor, it is characterised in that: spray gap A is 6 radians is the fan-shaped spray gap A of 50 degree.
4. a kind of annular solid-liquid catalytic ignition electromotor as claimed in claim 1, it is characterised in that: the width of spray gap A is 0.1mm.
5. a kind of annular solid-liquid catalytic ignition electromotor as claimed in claim 1, it is characterised in that: the arrival end of spray gap A is designed as 120 degree of contraction mouths, and outlet is 15 degree of extension mouths.
6. a kind of annular solid-liquid catalytic ignition electromotor as claimed in claim 1, it is characterised in that: fixing powder column adopts high density polyethylene (HDPE).
7. a kind of annular solid-liquid catalytic ignition electromotor as claimed in claim 1, it is characterised in that: heat insulation layer adopts high silica material.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610022559.3A CN105715409A (en) | 2016-01-14 | 2016-01-14 | Annular solid-liquid catalytic ignition engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610022559.3A CN105715409A (en) | 2016-01-14 | 2016-01-14 | Annular solid-liquid catalytic ignition engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105715409A true CN105715409A (en) | 2016-06-29 |
Family
ID=56147098
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610022559.3A Pending CN105715409A (en) | 2016-01-14 | 2016-01-14 | Annular solid-liquid catalytic ignition engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105715409A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014690A (en) * | 2016-07-22 | 2016-10-12 | 北京航空航天大学 | Ablation-type nonmetal igniter of hybrid rocket engine |
| CN106762228A (en) * | 2017-01-19 | 2017-05-31 | 北京航空航天大学 | The high-strength hydrogen peroxide catalytic bed that solid-liquid rocket works long hours |
| CN109162832A (en) * | 2018-10-09 | 2019-01-08 | 北京航空航天大学 | Engine head structure, hybrid rocket engine and rocket |
| CN117869126A (en) * | 2024-03-12 | 2024-04-12 | 西安航天动力研究所 | Direct-current ignition structure of rocket engine combustion chamber |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3943706A (en) * | 1973-01-10 | 1976-03-16 | Messerschmitt-Bolkow-Blohm Gmbh | Ignition system for rocket engine combustion chambers operated by non-hypergolic propellant components |
| JPH0978052A (en) * | 1995-09-08 | 1997-03-25 | Hosoya Kako Kk | Gelated oxidizing agent |
| US6253539B1 (en) * | 1996-09-24 | 2001-07-03 | Boeing North America Inc. | Convective and turbulent shear mixing injector |
| US20110167793A1 (en) * | 2010-01-11 | 2011-07-14 | Korea Advanced Institute Of Science And Technology | Hybrid rocket using catalytic decomposition of oxidizer |
| CN103557094A (en) * | 2013-09-18 | 2014-02-05 | 北京航空航天大学 | High-concentration hydrogen peroxide catalysis bed structure used for ground test of solid-liquid hybrid rocket motor |
-
2016
- 2016-01-14 CN CN201610022559.3A patent/CN105715409A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3943706A (en) * | 1973-01-10 | 1976-03-16 | Messerschmitt-Bolkow-Blohm Gmbh | Ignition system for rocket engine combustion chambers operated by non-hypergolic propellant components |
| JPH0978052A (en) * | 1995-09-08 | 1997-03-25 | Hosoya Kako Kk | Gelated oxidizing agent |
| US6253539B1 (en) * | 1996-09-24 | 2001-07-03 | Boeing North America Inc. | Convective and turbulent shear mixing injector |
| US20110167793A1 (en) * | 2010-01-11 | 2011-07-14 | Korea Advanced Institute Of Science And Technology | Hybrid rocket using catalytic decomposition of oxidizer |
| CN103557094A (en) * | 2013-09-18 | 2014-02-05 | 北京航空航天大学 | High-concentration hydrogen peroxide catalysis bed structure used for ground test of solid-liquid hybrid rocket motor |
Non-Patent Citations (1)
| Title |
|---|
| 宋志兵等: ""提高固液混合火箭发动机燃面后退速率的方法"", 《火***学报》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106014690A (en) * | 2016-07-22 | 2016-10-12 | 北京航空航天大学 | Ablation-type nonmetal igniter of hybrid rocket engine |
| CN106762228A (en) * | 2017-01-19 | 2017-05-31 | 北京航空航天大学 | The high-strength hydrogen peroxide catalytic bed that solid-liquid rocket works long hours |
| CN109162832A (en) * | 2018-10-09 | 2019-01-08 | 北京航空航天大学 | Engine head structure, hybrid rocket engine and rocket |
| CN117869126A (en) * | 2024-03-12 | 2024-04-12 | 西安航天动力研究所 | Direct-current ignition structure of rocket engine combustion chamber |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112879178B (en) | Solid rocket ramjet based on detonation combustion | |
| US6820412B2 (en) | Hybrid rocket motor having a precombustion chamber | |
| CN102996284B (en) | Solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide | |
| US2433943A (en) | Operation of jet propulsion motors with nitroparaffin | |
| US3240010A (en) | Rotary detonation power plant | |
| CN106134417B (en) | Low-thrust rocket | |
| CN105715409A (en) | Annular solid-liquid catalytic ignition engine | |
| CN106194502A (en) | A kind of solid-liquid Attitude rocket engine | |
| CN103967653B (en) | A kind of axially injection end combustion solid-liquid rocket structure | |
| US8024918B2 (en) | Rocket motor having a catalytic hydroxylammonium (HAN) decomposer and method for combusting the decomposed HAN-based propellant | |
| US3535881A (en) | Combination rocket and ram jet engine | |
| CN110469426B (en) | Solid rocket engine with continuously adjustable thrust and solid rocket | |
| CN104791135B (en) | Solid-liquid rocket lighter | |
| CN109653903A (en) | A kind of repeatable igniter for solid-liquid rocket | |
| US3771313A (en) | Generation of motive power with metal and water as fuel | |
| CN105804889A (en) | Method for starting main engine by solid-liquid ignition engine through multiple times of catalysis and ignition control device thereof | |
| CN109162831A (en) | Solid-liquid power engine and the rocket for applying it | |
| CN107701331A (en) | A kind of solid-liquid hybrid rocket engine and its method of work | |
| US6739121B2 (en) | Flame holder for a hybrid rocket motor | |
| JP3717002B2 (en) | Solid rocket engine | |
| WO2022100531A1 (en) | Auxiliary propulsion device for aerospace liquid propeller | |
| US3345822A (en) | Burning rate control of solid propellants | |
| US3182445A (en) | Liquid-solid propellant rocket case and method | |
| CN114776482B (en) | Liquid rocket engine propulsion system utilizing resonance ignition | |
| GB1220287A (en) | Combined ram jet and rocket engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160629 |