CN102996284A - Solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide - Google Patents
Solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide Download PDFInfo
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- CN102996284A CN102996284A CN2012104914205A CN201210491420A CN102996284A CN 102996284 A CN102996284 A CN 102996284A CN 2012104914205 A CN2012104914205 A CN 2012104914205A CN 201210491420 A CN201210491420 A CN 201210491420A CN 102996284 A CN102996284 A CN 102996284A
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Abstract
The invention discloses a solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide, which is arranged in a front combustion chamber. The solid-liquid rocket engine annular igniter comprises a shell, an ignition fuel and an ignition wire, wherein the shell is an annular containing cavity, and the ignition fuel which is ignite by the ignition wire is filled in the shell; and a fire transfer hole is formed in the inner ring sidewall of the shell. Therefore, the ignition wire is electrified to ignite the ignition fuel, and the generated ignition fuel is jetted along the radial direction of the front combustion chamber through the fire transfer hole; and then an oxidant is supplied into the injector liquid collection cavity, and the oxidant is sprayed into the front combustion chamber through a jetting hole and is heated and gasified by the ignition fuel, to generate high-temperature oxygen-enriched fuel, in order to heat the surface of the grain, so the grain is decomposed and gasified and is burnt in a manner of mixing with the high-temperature oxygen-enriched gas, to ignite to start up the engine. The solid-liquid rocket engine annular igniter suitable for the head jet of the hydrogen peroxide has the advantages that the igniter is applicable to jet of large flow of liquid oxidant, in order to rapidly start the engine; the igniter is compact in structure and low in influence on the other structures of the engine, and meets the demands of heating and gasifying the liquid oxidant and the solid fuel in the process of igniting to start up the solid-liquid engine.
Description
Technical field
The present invention relates to the ignition trigger technical field of rocket motor, specifically, be a kind of igniter of solid-liquid rocket, be particularly useful for from the high-strength hydrogen peroxide of engine head spray, such as the single igniting of 90% concentration hydrogen peroxide as the solid-liquid rocket of liquid oxidizer.
Background technique
Solid-liquid rocket is as a kind of chemical rocket engine, compared to liquid propellant rocket engine and the solid propellant rocket of development comparative maturity, good but the characteristics that ignition trigger is relatively difficult of Security arranged.Liquid propellant rocket engine has the requirement that repeatedly starts usually, and except spontaneous ignition, common mode has a plurality of pyrotechnic igniters of employing or is provided with the extra ignition system that can repeatedly start; The former is column structure normally, is installed on outside the firing chamber of motor, by leading flame tube the flame that igniter produces is introduced the firing chamber; And latter's complex structure.Solid propellant rocket generally can not be realized repeatedly ignition trigger, commonly used all is to adopt the mode of igniter pad or igniter motor to light a fire, usually it is indoor to be installed on engine combustion, most column or annulus etc. of adopting can burn structure, and the solid propellant grain jet surface is aimed in the combustion gas that igniter produces.Because solid-liquid rocket has the solid fuel powder column similar to solid engines, the liquid oxidizer spray similar to liquid propellant rocket engine arranged, in the ignition trigger process of motor, gasify after should making the liquid oxidizer spray, make again the heating of solid fuel powder column decompose gasification, the input of ignition energy is had living space and temporal requirement, so its igniter design and use and need satisfy the condition on position and opportunity.
Make up for nonhypergolic propellant, the ignition trigger technology of solid-liquid rocket, used for reference the thinking of solid or liquid propellant rocket engine, the independent igniter of most employings, because oxygenant enters motor in the motor front portion usually, so the energy input position of igniter is usually in the front portion of motor, namely in the space of front firing chamber.And because motor adopts different oxygenants/solid fuel combination, igniter is different on form and effective object.For gaseous oxidant, such as gas oxygen, perhaps very easily liquid oxidizer such as the nitrous oxide of gasification can adopt instantaneous (≤50ms) energy releasing device, carry out ignition trigger such as spherical or columniform gunpowder bag, this mode is widely adopted in the small-scale test motor.In addition, can utilize independent igniter fuel supply system, produce torch such as alcohol, methane, hydrogen etc. and oxygenant igniting independent or motor itself, solid-liquid rocket is lighted a fire, this firing mode is similar to the torch type ignition system of liquid propellant rocket engine, adaptability to motor is wider, no matter is that gaseous oxidant or liquid oxidizer can be suitable for, and therefore applies to more widely in all kinds of test engines.But because its complex structure does not adopt in product-level motor usually.
To using hydrogen peroxide to be the solid-liquid rocket of oxygenant, in the process of its ignition trigger, combustion chamber environment is normal temperature and pressure (low latitude) or low-temp low-pressure (high-altitude) state, and the hydrogen peroxide saturated vapour forces down, and is difficult for gasification under normal temperature or the low temperature.But hydrogen peroxide decomposes can produce amount of heat, and for example 90% hydrogen peroxide decomposes fully, and the product temperature is 1028K, and decomposition product is the oxygen G﹠W, but this energy shortage is so that the rapid ignition trigger of motor.Generally, hydrogen peroxide all can carry out catalysis makes its decomposition, makes its gaseous decomposition product enter firing chamber and solid fuel ignition.Its common firing mode is extra spray or igniter fuel is set and the burning of catalytic decomposition product, produces higher energy, and engine ignition is started.This mode not only single can be used, and can also realize repeatedly lighting a fire.But it is larger that its ignition trigger postpones, usually more than 1s, and its structure is complicated owing to the existence of catalytic bed and igniter fuel supply system, reliability and Security reduce, and the danger of oxygenant blast appears being detained during engine cutoff easily, the motor that particularly starts for single only, system is too burdensome.These factors have limited the application of catalytic ignition mode on the hydrogen peroxide solid-liquid rocket.
Summary of the invention
In order to address the above problem, it is reliable rapidly to the invention provides a kind of ignition trigger, simple and compact for structure, safety of structure is good, be applicable to the solid-liquid rocket single igniter of head spray hydrogen peroxide, and its using method in solid-liquid rocket is proposed, realize the rapidly reliable ignition trigger of motor.
The present invention is applicable to the solid-liquid rocket annular igniter of head spray hydrogen peroxide, comprises housing, igniter fuel and ignition wire.Wherein, housing is the ring-shaped chamber structure with inside and outside annular sidewall; Enclosure interior is filled with the igniter fuel by ignition material and fuel mix; Ring-side wall week upwards have flash hole in the housing; Interior ring-side wall internal surface also is equipped with sealing strip, by sealing strip flash hole is sealed; Described ignition wire one end produces pyrophoric firing head for energising, is embedded in the ignition material that is arranged in enclosure interior; The other end is electric lead, and draw at the place by flash hole.
Above-mentioned housing end face is fixed on the ejector filler panel lower surface in the motor; The conducting end of ignition wire is drawn from engine jet pipe after passing successively the front firing chamber, powder column passage of motor.
Thereby by the work of said structure ignition wire energising initial igniter; After the ignition wire energising, the ignition material in the lead fire fuel, the rapidly burning thereby fuel is ignited, the igniting combustion gas of generation; The igniting combustion gas break through sealing strip, by flash hole along the radially spray of front firing chamber; Behind the certain hour of interval, beginning feed fluid oxygenant in the ejector filler liquid collecting cavity, liquid oxidizer is in ejector filler liquid collecting cavity inner accumulated, produce certain pressure, and then spray into the liquid oxidizer jet in the firing chamber forward by the spray orifice on the ejector filler panel, liquid oxidizer through in the igniter during ring passage by the gas heating of lighting a fire, realize that the liquid oxidizer spray advances behind the front firing chamber immediately pyrolysing gasification, realize the rapid startup of motor.Liquid oxidizer after the heating decomposes the high-temperature oxygen-enriched combustion gas of generation, and the powder column passage that enters subsequently in the firing chamber heats grain surface, makes powder column decompose gasification and high-temperature oxygen-enriched combustion gas mixing burning, thus the ignition trigger of realization motor.
The invention has the advantages that:
1, igniter of the present invention is close to the installation form of ejector filler panel by igniter case, is pyrolysing gasification so that front firing chamber is entered in the spray of all liq oxygenant, and motor can be started rapidly;
2, igniter of the present invention by igniter radially flash hole the igniting combustion gas is sprayed diametrically, the energy that the igniting combustion gas discharges is concentrated in the plane and is discharged, and can be used for the spray of large flow liquid oxygenant;
3, igniter of the present invention adopts the loop configuration housing, and be installed on the ejector filler panel, make igniter be positioned at the low temperature area of front firing chamber, having avoided simultaneously oxygenant washes away the front of igniter structure, make igniter case have good thermal protection and structural integrity, in the engine long time service, do not threaten the stable operation of motor; And so that igniter can adopt common low-cost material;
4, igniter of the present invention is installed on the ejector filler panel by bolt, takes full advantage of the space of front firing chamber, makes whole igniter structure compact, little on the impact of other structures of motor;
5, igniter of the present invention makes igniter can adapt to by designing different inside/outside diameter sizes the advantage of different size of engine by igniter case and the coupling design dimensionally of the front firing chamber of motor cylindrical structural;
6, the energy of igniter release of the present invention does not directly act on the solid fuel powder column, but by heating liquid oxygenant jet, it is decomposed produce high-temperature oxygen-enriched combustion gas, by high-temperature oxygen-enriched gas heating solid fuel grain surface, make solid fuel surface decompose gasification, with high-temperature oxygen-enriched combustion gas mixing burning, solved simultaneously in the solid-liquid engine ignition start-up course, to the demand of liquid oxidizer and solid fuel heating and gasifying.
Description of drawings
Fig. 1 igniter structure and the igniter mounting type schematic representation in motor;
The work of Fig. 2 igniter and engine ignition process schematic representation.
Among the figure:
1-motor 2-igniter 3-mounting screw 4-seal ring
The front firing chamber of the 5-igniting combustion gas 6-high-temperature oxygen-enriched combustion gas 101-of liquid oxidizer 7-
102-ejector filler liquid collecting cavity 103-ejector filler panel 104-powder column path 10 5-powder column
106-engine jet pipe 107-spray orifice 201-housing 202-igniter fuel
203-ignition wire 204-flash hole
Embodiment
The present invention will be further described below in conjunction with accompanying drawing.
The present invention is applicable to the annular igniter 2 of the solid-liquid rocket of head spray hydrogen peroxide, the hydrogen peroxide solid-liquid rocket that is applied to; Be installed in the front firing chamber of motor 1 101, as shown in Figure 1, comprise housing 201, igniter fuel 202 and ignition wire 203.
Described housing 201 adopts carbon steel material to make for having the ring-shaped chamber structure of inside and outside annular sidewall; Whole cavity volume has certain structural strength, the pressure in the time of can bearing igniter 2 work in the cavity volume.Housing 201 inside of igniter 2 are filled with the igniter fuel 202 by ignition material and fuel mix; Wherein, the material of getting angry is the material that can realize that moment gets angry, as: black gunpowder; And fuel can be realized sustained combustion, such as solid propellant; The filling dose of igniter fuel 202 is decided according to the liquid oxidizer uninterrupted in the ejector filler liquid collecting cavity 102 of motor 1, satisfies the requirement of igniter continuous working period t1 and t2; Wherein, t1 is the blanking time that oxygenant spray and igniter 2 starts work, the moment poor that namely to be igniter 2 moment of starting working enter front firing chamber 101 with the liquid oxidizer jet, and the t1 value is greater than 0; T2 is that the combustion gas of igniter 2 releases is to the continuous heating time of oxygenant jet, what be liquid oxidizer jet moment of entering front firing chamber 101 with the 2 out-of-work moment of igniter is poor, t2 decides on the mass flow rate of the oxygenant spray jet of concrete motor 1 and the jet-flow mass flow rate of igniter 2 releases, generally more than 100ms.
201 interior ring-side wall weeks of housing at igniter 2 upwards evenly have flash hole 204, are used for the jet ignition combustion gas; The energy that igniter fuel 202 is discharged is concentrated in the plane and is discharged, and can be used for the spray of the ejector filler liquid collecting cavity 102 interior large flow liquid oxygenants of motor 1.The interior ring-side wall internal surface of igniter 2 is equipped with sealing strip, with flash hole 204 sealings, prevents that when lighting a fire the igniter fuel 202 in the housing 201 is leaked by flash hole 204 places by sealing strip; And when igniter 2 work, igniting combustion gas 202 can be broken through sealing strip and be sprayed into front firing chamber 101; Described sealing strip adopts tin foil paper.
Above-mentioned ignition material ignites by ignition wire 203; Described ignition wire 203 1 ends produce pyrophoric firing head for energising, are embedded in the ignition material that is arranged in housing 201 inside; The other end is electric lead, is drawn by flash hole 204 places on the igniter.
The mounting point of igniter 2 according to the present invention, housing 201 external diameters of igniter 2 are made with front firing chamber 101 internal diameters be complementary, and be complementary the external diameter of housing 201 internal diameters of igniter 2 and spray orifice 107 overlay areas on the ejector filler panel 103 (being the ring that spray orifice 107 on the motor 1 ejector filler panel 103 is positioned at housing 201 projection on ejector filler panel 103), can take full advantage of the space of front firing chamber 101 by this kind structure, be complementary from firing chamber size and the spray scope of different motors 2.
As shown in Figure 2, adopt the motor 1 of igniter 2 of the present invention when ignition trigger, igniter 2 startup work by ignition wire 203 energisings; After ignition wire 203 energisings, the ignition material in the lead fire fuel 202, the rapidly burning thereby fuel is ignited, the igniting combustion gas 5 of generation; The igniting combustion gas 5 break through sealing strip, by flash hole 204 along the radially spray of front firing chamber 101; Behind the certain hour t1 of interval, beginning is to ejector filler liquid collecting cavity 102 interior feed fluid oxygenants 6, liquid oxidizer 6 is in ejector filler liquid collecting cavity 102 inner accumulated, produce certain pressure, and then spray into liquid oxidizer 6 jets in firing chamber 101 forward by the spray orifice 107 on the ejector filler panel 103, liquid oxidizer 6 combustion gas 5 heating of being lighted a fire during through igniters 2 interior ring passage realize that liquid oxidizer 6 sprays advance behind the front firing chamber 101 immediately pyrolysing gasification, realize the rapid startup of motor 1.Liquid oxidizer after the heating decomposes the high-temperature oxygen-enriched combustion gas 7 of generation, and heat on 4 pairs of powder column 105 surfaces of powder column path 10 that enter subsequently in the firing chamber, makes powder column 105 decompose gasification and high-temperature oxygen-enriched combustion gas 7 mixed combustions, thereby realizes the ignition trigger of motor 1.To enter front firing chamber be pyrolysing gasification to 6 sprays of all liq oxygenant thus, and motor 1 is started rapidly.The process of above-mentioned motor 1 ignition trigger, because the energy that igniter 2 discharges does not directly act on solid fuel powder column 105, but by heating liquid oxygenant 6 jets, it is decomposed produce high-temperature oxygen-enriched combustion gas 7, by high-temperature oxygen-enriched combustion gas 7 heat solid fuel powder columns 105 surfaces, make solid fuel surface decompose gasification, with high-temperature oxygen-enriched combustion gas 7 mixed combustions, solved simultaneously in the solid-liquid motor 1 ignition trigger process, to the demand of liquid oxidizer 6 and solid fuel heating and gasifying.
Igniter 2 by said structure, and the mounting point of igniter 2, flame mode cooperate the setting of time with the oxygenant spray, large flow liquid hydrogen peroxide solid-liquid rocket 1 ignition trigger that makes is quick, about 100ms ~ the 300ms of ignition delay time far is shorter than the 1s magnitude of hydrogen peroxide catalyzed igniting.
Claims (10)
1. be applicable to the solid-liquid rocket annular igniter of head spray hydrogen peroxide, it is characterized in that: comprise housing, igniter fuel and ignition wire;
Described housing is the ring-shaped chamber structure with inside and outside annular sidewall; Enclosure interior is filled with the igniter fuel by ignition material and fuel mix; Ring-side wall week upwards has flash hole in housing; Interior ring-side wall internal surface also is equipped with sealing strip, by sealing strip flash hole is sealed; Described ignition wire one end produces pyrophoric firing head for energising, is embedded in the ignition material that is arranged in enclosure interior; The other end is electric lead, and draw at the place by flash hole;
Above-mentioned housing end face is fixed on the ejector filler panel lower surface in the motor; The conducting end of ignition wire is drawn from engine jet pipe after passing successively the front firing chamber, powder column passage of motor.
2. be applicable to as claimed in claim 1 the solid-liquid rocket annular igniter of head spray hydrogen peroxide, it is characterized in that: described housing external diameter and the front firing chamber of motor internal diameter are complementary, and the external diameter of the spray orifice overlay area on internal diameter and the motor ejector filler panel is complementary.
3. be applicable to as claimed in claim 1 the solid-liquid rocket annular igniter of head spray hydrogen peroxide, it is characterized in that: the filling dose of described igniter fuel need satisfy the requirement of igniter continuous working period t1 and t2; Wherein, t1 is the blanking time of oxygenant spray and igniter startup work, and t1 is greater than 0; T2 be the combustion gas that discharges of igniter to the continuous heating time of oxygenant jet, t2 is greater than 100ms.
4. be applicable to as claimed in claim 1 the solid-liquid rocket annular igniter of head spray hydrogen peroxide, it is characterized in that: described flash hole is evenly arranged.
5. be applicable to as claimed in claim 1 the solid-liquid rocket annular igniter of head spray hydrogen peroxide, it is characterized in that: described ignition material is black gunpowder; Seed material is solid propellant.
6. be applicable to as claimed in claim 1 the solid-liquid rocket annular igniter of head spray hydrogen peroxide, it is characterized in that: described sealing strip is tin foil paper.
7. be applicable to as claimed in claim 1 the solid-liquid rocket annular igniter of head spray hydrogen peroxide, it is characterized in that: described housing is connected by the housing end face that the ejector filler panel upper surface passes ejector filler panel and igniter by construction bolt, makes the housing upper surface be close to ejector filler panel lower surface.
8. be applicable to as claimed in claim 8 the solid-liquid rocket annular igniter of head spray hydrogen peroxide, it is characterized in that: the seal ring by the nitrile rubber material between described construction bolt and ejector filler panel seals.
9. be applicable to as claimed in claim 8 the solid-liquid rocket annular igniter of head spray hydrogen peroxide, it is characterized in that: the decontamination of need deoiling before installation of described mounting screw is processed.
10. as being applicable to the solid-liquid rocket annular igniter of head spray hydrogen peroxide as described in claim 1 or 8, it is characterized in that: the equal carbon steel material of described housing and construction bolt is made.
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| CN201210491420.5A CN102996284B (en) | 2012-11-27 | 2012-11-27 | Solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide |
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| CN201210491420.5A CN102996284B (en) | 2012-11-27 | 2012-11-27 | Solid-liquid rocket engine annular igniter suitable for head jet of hydrogen peroxide |
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| CN102996284B CN102996284B (en) | 2015-02-25 |
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| CN103644047A (en) * | 2013-11-21 | 2014-03-19 | 北京动力机械研究所 | Igniting and starting device of solid rocket engine |
| CN103993984A (en) * | 2014-05-23 | 2014-08-20 | 清华大学深圳研究生院 | Hydrogen-peroxide-assisted ignition device |
| CN104632467A (en) * | 2015-01-12 | 2015-05-20 | 葛明龙 | Rocket thrust chamber provided with acoustic cavity and applied to supersonic airliner and supply system thereof |
| CN104791135A (en) * | 2015-04-03 | 2015-07-22 | 北京航空航天大学 | Hybrid rocket engine igniter |
| CN104806381A (en) * | 2015-04-03 | 2015-07-29 | 北京航空航天大学 | Solid-liquid rocket engine igniter and head wire-outgoing method thereof |
| CN105003357A (en) * | 2015-07-17 | 2015-10-28 | 南京理工大学 | Pasty propellant fuel gas generator ignition device based on solid rocket engine |
| CN105804889A (en) * | 2016-02-04 | 2016-07-27 | 北京航空航天大学 | Method for starting main engine by solid-liquid ignition engine through multiple times of catalysis and ignition control device thereof |
| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
| CN106194501A (en) * | 2016-07-08 | 2016-12-07 | 北京航空航天大学 | Spiral Types of Medicine solid-liquid rocket |
| CN107035568A (en) * | 2017-03-29 | 2017-08-11 | 北京航空航天大学 | Hydrogen peroxide solid-liquid rocket subregion quick response catalytic bed |
| CN108688829A (en) * | 2018-05-28 | 2018-10-23 | 北京航空航天大学 | Solid-liquid power sub-orbital booster |
| CN108869100A (en) * | 2018-07-03 | 2018-11-23 | 北京航空航天大学 | Separation pushes away solid-liquid rocket and rocket auxiliary braking system with counter |
| CN111256543A (en) * | 2020-01-16 | 2020-06-09 | 西北工业大学 | Small solid-liquid sounding rocket for teaching science popularization |
| CN112177801A (en) * | 2020-08-31 | 2021-01-05 | 西北工业大学 | Hydrogen peroxide/kerosene rocket engine thrust chamber based on third fluid |
| CN112392629A (en) * | 2021-01-04 | 2021-02-23 | 北京航空航天大学 | Solid-liquid-solid co-combustion chamber combined power rocket engine and aircraft |
| CN113663633A (en) * | 2021-08-17 | 2021-11-19 | 合肥中科重明科技有限公司 | Novel hydrogen peroxide multistage catalytic decomposition type gas generator |
| CN109798202B (en) * | 2019-04-04 | 2023-08-22 | 北京宇航推进科技有限公司 | Liquid rocket engine injector integrating electric igniter |
| 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 |
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| CN103644047A (en) * | 2013-11-21 | 2014-03-19 | 北京动力机械研究所 | Igniting and starting device of solid rocket engine |
| CN103644047B (en) * | 2013-11-21 | 2015-09-23 | 北京动力机械研究所 | A kind of ignition initiation devices of solid propellant rocket |
| CN103993984A (en) * | 2014-05-23 | 2014-08-20 | 清华大学深圳研究生院 | Hydrogen-peroxide-assisted ignition device |
| CN103993984B (en) * | 2014-05-23 | 2016-07-13 | 清华大学深圳研究生院 | A kind of hydrogen peroxide auxiliary ignition device |
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| CN104806381A (en) * | 2015-04-03 | 2015-07-29 | 北京航空航天大学 | Solid-liquid rocket engine igniter and head wire-outgoing method thereof |
| CN105003357A (en) * | 2015-07-17 | 2015-10-28 | 南京理工大学 | Pasty propellant fuel gas generator ignition device based on solid rocket engine |
| CN105804889A (en) * | 2016-02-04 | 2016-07-27 | 北京航空航天大学 | Method for starting main engine by solid-liquid ignition engine through multiple times of catalysis and ignition control device thereof |
| CN106194501A (en) * | 2016-07-08 | 2016-12-07 | 北京航空航天大学 | Spiral Types of Medicine solid-liquid rocket |
| CN106121864A (en) * | 2016-07-22 | 2016-11-16 | 北京航空航天大学 | A kind of head body portion combines multizone and is centrifuged spray solid-liquid rocket |
| CN107035568A (en) * | 2017-03-29 | 2017-08-11 | 北京航空航天大学 | Hydrogen peroxide solid-liquid rocket subregion quick response catalytic bed |
| CN107035568B (en) * | 2017-03-29 | 2018-08-10 | 北京航空航天大学 | Hydrogen peroxide solid-liquid rocket subregion quick response catalytic bed |
| CN108688829A (en) * | 2018-05-28 | 2018-10-23 | 北京航空航天大学 | Solid-liquid power sub-orbital booster |
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| CN109798202B (en) * | 2019-04-04 | 2023-08-22 | 北京宇航推进科技有限公司 | Liquid rocket engine injector integrating electric igniter |
| CN111256543A (en) * | 2020-01-16 | 2020-06-09 | 西北工业大学 | Small solid-liquid sounding rocket for teaching science popularization |
| CN112177801A (en) * | 2020-08-31 | 2021-01-05 | 西北工业大学 | Hydrogen peroxide/kerosene rocket engine thrust chamber based on third fluid |
| CN112392629A (en) * | 2021-01-04 | 2021-02-23 | 北京航空航天大学 | Solid-liquid-solid co-combustion chamber combined power rocket engine and aircraft |
| CN113663633A (en) * | 2021-08-17 | 2021-11-19 | 合肥中科重明科技有限公司 | Novel hydrogen peroxide multistage catalytic decomposition type gas generator |
| CN113663633B (en) * | 2021-08-17 | 2022-10-04 | 合肥中科重明科技有限公司 | Novel hydrogen peroxide multistage catalytic decomposition type gas generator |
| 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 |
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| CN102996284B (en) | 2015-02-25 |
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