CN106014690A - Ablation-type nonmetal igniter of hybrid rocket engine - Google Patents
Ablation-type nonmetal igniter of hybrid rocket engine Download PDFInfo
- Publication number
- CN106014690A CN106014690A CN201610587616.2A CN201610587616A CN106014690A CN 106014690 A CN106014690 A CN 106014690A CN 201610587616 A CN201610587616 A CN 201610587616A CN 106014690 A CN106014690 A CN 106014690A
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- China
- Prior art keywords
- igniter
- ignition
- solid
- ignition charge
- liquid rocket
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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
- F02K9/72—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
- F05D2300/00—Materials; Properties thereof
- F05D2300/40—Organic materials
- F05D2300/43—Synthetic polymers, e.g. plastics; Rubber
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Air Bags (AREA)
Abstract
The present invention discloses an ablation-type nonmetal igniter of a hybrid rocket engine, which is applicable to single-pass ignition of the hybrid rocket engine which uses a liquid oxidizing agent and a solid fuel as a propellant combination. The igniter is mainly composed of an igniter housing, an igniter cartridge body, an ignition powder and an ignition fuse, wherein the igniter housing and the igniter cartridge body are made of a polyethylene material. A groove is formed in a circumferential direction in the igniter cartridge body, the ignition powder is placed into the groove, and the igniter cartridge body is in up and down double-thread connection with the igniter housing, so the strength of the thread connection is ensured, and by using the feature of low hardness of the polyethylene material, effective sealing is realized through thread close fit. After the hybrid rocket engine is ignited, the polyethylene igniter housing can be ablated and pyrolyzed in a high temperature environment of a combustion chamber and becomes a fuel gas to participate in combustion of the engine, thereby reducing adverse impacts on an engine internal flow field, reducing invalid loads of an air vehicle at a flight phase, making the utmost of the energy of the igniter housing, and raising the performance of the engine.
Description
Technical field
The present invention relates to the ignition trigger field of rocket engine, specifically, be that the ablation of a kind of solid-liquid rocket is non-
Metal dots firearm, it is adaptable to solid-liquid rocket single is lighted a fire, ablation non-metal shell structure is applicable to head heat protection and asks
Inscribe the most serious solid-liquid rocket.
Background technology
Solid-liquid rocket generally uses the propellant of solid fuel and liquid oxidizer to combine.Because of the physical arrangement of its uniqueness,
Solid-liquid rocket has had some traditional solid propellant rockets and the advantage of liquid-propellant rocket engine concurrently, such as safety is good,
The feature of environmental protection is good, thrust easily regulates, good economy performance, structure are reliable, be highly suitable for as middle-size and small-size sounding rocket, target,
The dynamical system of the aerospace crafts such as inferior orbital vehicle.
In solid-liquid rocket, oxidant and fuel are separately to store, non-premix, and owing to its thing is mutually different, logical
The Self-lighting of normal electromotor relatively difficult to achieve.During the ignition trigger of solid-liquid rocket, not only need to ensure liquid oxygen
Agent completes gasification after spray enters combustor, in addition it is also necessary to generation energy carries out heating to solid fuel powder column makes it be pyrolyzed generation
Fuel gas, requires the highest to the room and time of ignition energy.Therefore, firing technique becomes solid-liquid rocket
Key technology in application.
In the sparking mode of solid-liquid rocket, widely used mainly have catalysis type ignition schemes and igniter type point
Fire scheme.Catalysis type ignition schemes is to make spray enter the oxidizer catalytic decomposition of solid-liquid rocket engine combustor by catalyst
And it is gasificated as gaseous steam, heat release carries out heating and makes its temperature raise and be pyrolyzed solid fuel powder column the most in this process,
Thus realize the ignition trigger of solid-liquid rocket.Igniter type ignition schemes is then indoor by being positioned over engine combustion
Igniter blast provide energy, promote electromotor oxidant gasification decompose and by self get angry energy and oxidant decompose
Liberated heat carries out heating to solid fuel powder column makes it be pyrolyzed, thus realizes the ignition trigger of solid-liquid rocket.Catalysis
Formula ignition schemes is easier to realize the repeatedly igniting of solid-liquid rocket, but it is higher to the requirement of oxidant and catalyst,
It is not the highest for being generally only applicable to use the solid-liquid rocket of specific oxidant, versatility.And igniter type igniting side
Case then goes for the solid-liquid rocket of most propellant combination, applied widely, has the highest versatility,
It it is a kind of preferably method of ignition and starting up.
But, lighter, after solid-liquid rocket completes ignition trigger process, becomes for skimble-skamble invalid load,
In space mission highstrung to Flight Vehicle Structure quality, the momentum of a part of electromotor can be wasted, the flight to aircraft
Process produces certain adverse effect.Meanwhile, lighter also can produce phase to the flow field of solid-liquid rocket in combustor
To adverse influence, thus reduce the combustibility of solid-liquid rocket to a certain extent.Therefore, one can be complete
Become the igniter structure decomposing and discharging electromotor after ignition process voluntarily the most meaningful.
Summary of the invention
In order to solve foregoing problems, providing a kind of simple in construction in the present invention, the suitability is wide, it is possible to achieve solid-liquid rocket starts
The nonmetal lighter of ablation of the rapid reliable ignition of machine, goes for single ground igniting solid-liquid rocket and single is high
Null point fire solid-liquid rocket.
The nonmetal lighter of solid-liquid rocket ablation of the present invention, including igniter shell, ignition charge box body, ignition charge with
Ignition fuse.Annular groove is also had, set-point gunpowder in groove on the external wall of igniter cartridge.Igniter cartridge body is positioned at ignition charge
Coaxially fix between enclosure, and ignition charge shell；In igniter cartridge body, ring circumference equal space design has and annular groove simultaneously
The ignition hole of connection；Ignition fuse end is connected through ignition hole with the igniter head being embedded in ignition charge, and the other end connects solid-liquid rocket
Engine control system.
In above-mentioned igniter shell and between ignition charge box body, by igniter shell inner ring wall and igniter cartridge external circle wall
It is designed with the helicitic texture cooperated to be connected；And igniter shell all uses polythene material with ignition charge box body.
Thus after solid-liquid rocket control system sends ignition power signal, this signal is transferred in ignition charge by ignition fuse
Igniter head, the solid ignition charge in igniter head firing point firearm, ignition charge is got angry rapidly and produces high-temperature ignition flame；Igniting
It is indoor that flame sprays to engine combustion by the ignition hole 5 on ignition charge box body 2 internal ring of polythene material, and heating is passed through rapidly
Liquid oxidizer jet in lighter internal ring, gasifies rapidly after the thermal-flame heating of the ignited device of liquid oxidizer and is decomposed into
Oxidant gas；The oxidant gas of high temperature can carry out heating to the solid fuel powder column of solid-liquid rocket makes it be pyrolyzed product
Raw fuel gas also blends burning with it, it is achieved the ignition trigger of solid-liquid rocket；Can produce in engine chamber afterwards
The harsh environments of raw thermal extremes high pressure, the igniter shell of polythene material and the meeting in high-temperature hot environment of ignition charge box body
There is ablation pyrolysis, eventually become the fuel gas based on ethylene.
It is an advantage of the current invention that:
1, the nonmetal lighter of solid-liquid rocket ablation of the present invention, uses polythene material to make igniter shell and igniting
Drug cassette body；Polyethylene itself is solid fuel conventional in a kind of solid-liquid rocket, and it may also participate in after ablation is pyrolyzed
The burning of electromotor, makes full use of its energy；Can ablation gasifying after completing solid-liquid rocket igniting, it is to avoid igniting
The device structure adverse effect to engine combustion Indoor Flow Field；Decrease the invalid quality of loads during aircraft flight simultaneously,
Aircraft can be made more fully to utilize the energy of electromotor；
2, in the nonmetal lighter of solid-liquid rocket ablation of the present invention, ignition charge box body is in ignition charge installation cavity both sides
Screw connection structure, can be effectively ensured ignition charge installation cavity and the reliability threadeded in nonmetal structure, it is to avoid lighter
During self work, screw strength is relatively low causes Joint failure；Meanwhile, the hardness of polyethylene own is not the highest, threaded tight time
Can ensure to seal simultaneously, the sealing structure of lighter can be simplified, improve its reliability.
Accompanying drawing explanation
Fig. 1 one solid-liquid rocket ablation nonmetal igniter structure figure
In figure:
1-igniter shell 2-ignition charge box body 3-ignition charge
4-ignition fuse 5-gets angry hole
Detailed description of the invention
The present invention will be further described below in conjunction with the accompanying drawings.
The nonmetal lighter of solid-liquid rocket ablation of the present invention, it is adaptable to use liquid oxidizer and solid fuel powder column to push away
Enter the single ignition trigger of the solid-liquid rocket of agent combination, including igniter shell 1, ignition charge box body 2, ignition charge 3 and point
Fire lead-in wire 4, as shown in Figure 1.
Described igniter shell 1 is loop configuration with ignition charge box body 2；Wherein, igniter shell 1 inner ring wall and igniter cartridge
It is designed with, on the wall of body 2 outer ring, the helicitic texture cooperated；And on ignition charge box body 2 outer wall, also have annular groove, exist simultaneously
Ignition charge 3 outer wall circumference equal space design has the ignition hole 5 connected with annular groove.Above-mentioned ignition charge box body 2 is coaxially installed on igniting
Device shell 1, is connected with threaded engagement between igniter shell 1 inner ring wall by annular ignition charge box body 2 outer ring wall, and by solid
The annular shoulder of fixed point gunpowder box body 2 bottom design coordinates location with igniter shell 1 bottom design annular boss, it is achieved lighter
Shell 1 is fixing with ignition charge housing 1；The groove and the igniter shell 1 that realize ignition charge box body 2 enclose the point formed between wall simultaneously
The sealing of gunpowder installation cavity.
The solid ignition charge 3 of solid propellant composition it is filled with, in order to fast in lighter work process in above-mentioned ignition charge installation cavity
Speed is got angry and is burnt, and produces the thermal-flame in order to the solid-liquid rocket that ignites and energy.Ignition fuse 4 one end is through getting angry hole 5
Being connected with the igniter head being embedded in ignition charge 3, the other end connects solid-liquid rocket control system, is used for starting solid-liquid rocket
The ignition signal that machine control system sends is transferred to igniter head, igniter head ignited by solid ignition charge 3 and continued stable combustion is some
Second, produce the combustion flame of high temperature, it is ensured that solid-liquid rocket can quickly and reliably be ignited.
In the present invention, igniter shell 1, ignition charge box body 2 all use polythene material.Complete a little at hybrid rocket engine
After fire starts, in combustor, there is stable burning, and form the harsh environments of extreme high heat high pressure in a combustion chamber.?
Under the high-temperature fuel gas heat effect that engine combustion is indoor so that the igniter shell 1 of polythene material and ignition charge box body 2 temperature
Gradually rise, until polythene material generation ablation pyrolysis, produce the fuel gas based on ethylene.The fuel obtained after pyrolysis
Gas can carry out diffusion combustion with the oxidant gas in engine chamber after blending, so that originally can complete a little
The igniter case 1 becoming unnecessary invalid load after fire becomes the solid fuel that electromotor can effectively utilize, and is possible not only to improve
The capacity usage ratio of electromotor, it helps reduce the invalid quality of loads of aircraft.Meanwhile, the ablation of lighter can also subtract
Few igniter case 1 structure, at the indoor inhibition free-pouring to combustion gas of engine combustion, alleviates igniter structure to electromotor
The adverse effect of combustor flow field, thus improve the combustibility of solid-liquid rocket further.
The work process of the nonmetal lighter of solid-liquid rocket ablation of the present invention is: in solid-liquid rocket control system
After sending ignition power signal, igniter head that this signal is transferred in ignition charge by ignition fuse 4, consolidating in igniter head firing point firearm
Body ignition charge 3, ignition charge 3 is got angry rapidly and produces high-temperature ignition flame；The ignition flame ignition charge box body 2 by polythene material
It is indoor that ignition hole 5 on internal ring sprays to engine combustion, and heats rapidly by the liquid oxidizer jet in lighter internal ring, liquid
Gasify rapidly after the thermal-flame heating of the ignited device of body oxidant and be decomposed into oxidant gas；The oxidant gas of high temperature is permissible
The solid fuel powder column of solid-liquid rocket carries out heating makes it be pyrolyzed generation fuel gas and blend burning with it, it is achieved Gu
The ignition trigger of liquid rocket engine；The harsh environments of thermal extremes high pressure can be produced afterwards in engine chamber, poly-
The igniter shell 1 of vinyl material and ignition charge box body 2 can occur ablation to be pyrolyzed in high-temperature hot environment, eventually become and with ethylene are
Main fuel gas.Therefore igniter shell 1 and ignition charge box body 2 are in solid-liquid rocket engine combustor after ablation pyrolysis, go back
Oxidant gas that can be indoor with engine combustion blends reaction, participates in the combustion process that engine combustion is indoor, makes full use of
Its quality and energy.
Claims (2)
1. the nonmetal lighter of solid-liquid rocket ablation, including igniter shell, ignition charge box body, ignition charge with
Ignition fuse；Annular groove is also had, set-point gunpowder in groove on the external wall of igniter cartridge；Igniter cartridge body is positioned at ignition charge
Coaxially fix between enclosure, and ignition charge shell；In igniter cartridge body, ring circumference equal space design has and annular groove simultaneously
The ignition hole of connection；Ignition fuse end is connected through ignition hole with the igniter head being embedded in ignition charge, and the other end connects solid-liquid rocket
Engine control system；It is characterized in that: igniter shell and ignition charge box body all use polythene material.
2. a kind of nonmetal lighter of solid-liquid rocket ablation, it is characterised in that: outside lighter
In shell and between ignition charge box body, cooperate by being designed with on igniter shell inner ring wall and igniter cartridge external circle wall
Helicitic texture is connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610587616.2A CN106014690A (en) | 2016-07-22 | 2016-07-22 | Ablation-type nonmetal igniter of hybrid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610587616.2A CN106014690A (en) | 2016-07-22 | 2016-07-22 | Ablation-type nonmetal igniter of hybrid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106014690A true CN106014690A (en) | 2016-10-12 |
Family
ID=57117425
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610587616.2A Pending CN106014690A (en) | 2016-07-22 | 2016-07-22 | Ablation-type nonmetal igniter of hybrid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106014690A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107781063A (en) * | 2017-09-15 | 2018-03-09 | 北京理工大学 | The protector of harness during Cleaning by High Pressure Water Jet solid propellant rocket motor charge |
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
| 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 |
| TWI720399B (en) * | 2019-01-04 | 2021-03-01 | 台灣晉陞太空股份有限公司 | Rocket engine with improved solid fuel column |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE337142B (en) * | 1968-04-10 | 1971-07-26 | Mini Armee | |
| US5007236A (en) * | 1987-10-26 | 1991-04-16 | Morton Thiokol, Inc. | Removable rocket motor igniter |
| US20040068979A1 (en) * | 2002-10-11 | 2004-04-15 | Hy Pat Corporation | Ignition systems for hybrid and solid rocket motors |
| CN104791135A (en) * | 2015-04-03 | 2015-07-22 | 北京航空航天大学 | Hybrid rocket engine igniter |
| CN105715409A (en) * | 2016-01-14 | 2016-06-29 | 北京航空航天大学 | Annular solid-liquid catalytic ignition engine |
-
2016
- 2016-07-22 CN CN201610587616.2A patent/CN106014690A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE337142B (en) * | 1968-04-10 | 1971-07-26 | Mini Armee | |
| US5007236A (en) * | 1987-10-26 | 1991-04-16 | Morton Thiokol, Inc. | Removable rocket motor igniter |
| US20040068979A1 (en) * | 2002-10-11 | 2004-04-15 | Hy Pat Corporation | Ignition systems for hybrid and solid rocket motors |
| CN104791135A (en) * | 2015-04-03 | 2015-07-22 | 北京航空航天大学 | Hybrid rocket engine igniter |
| CN105715409A (en) * | 2016-01-14 | 2016-06-29 | 北京航空航天大学 | Annular solid-liquid catalytic ignition engine |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107781063A (en) * | 2017-09-15 | 2018-03-09 | 北京理工大学 | The protector of harness during Cleaning by High Pressure Water Jet solid propellant rocket motor charge |
| TWI720399B (en) * | 2019-01-04 | 2021-03-01 | 台灣晉陞太空股份有限公司 | Rocket engine with improved solid fuel column |
| CN110596301A (en) * | 2019-10-14 | 2019-12-20 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
| 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 |
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| PB01 | Publication | ||
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Application publication date: 20161012 |
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| RJ01 | Rejection of invention patent application after publication |