CN106134391B - RBCC engine integration fuel service system based on anhydrous hydrazine - Google Patents
RBCC engine integration fuel service system based on anhydrous hydrazineInfo
- Publication number
- CN106134391B CN106134391B CN201318001253.7A CN201318001253A CN106134391B CN 106134391 B CN106134391 B CN 106134391B CN 201318001253 A CN201318001253 A CN 201318001253A CN 106134391 B CN106134391 B CN 106134391B
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- CN
- China
- Prior art keywords
- anhydrous hydrazine
- fuel
- kerosene
- thrust chamber
- supply
- Prior art date
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Abstract
The invention discloses a kind of RBCC engine integration fuel service system based on anhydrous hydrazine, rocket thrust chamber and stamping combustion chamber are realized integrated fuel oil supply and adjusting with same system; System adopts dinitrogen tetroxide, anhydrous hydrazine and three kinds of storable propellants of kerosene, drives respectively two turbine pumps by anhydrous hydrazine catalytic decomposition, and extruding is supplied to rocket thrust chamber in the time of system charge, realizes and dinitrogen tetroxide spontaneous ignition; Anhydrous hydrazine adopts the supply of single tank squash type, and Propellant Supply is realized by turbine pump in thrust chamber and combustion chamber; Thrust chamber body portion is undertaken cooling by dinitrogen tetroxide, it is cooling that stamping combustion chamber utilizes kerosene to carry out. The present invention has overcome combined engine rocket thrust chamber and stamping combustion chamber is adopted separately independently supplying system to cause system complex, is difficult to realize the problems such as integrated regeneration cooling structure design, meet the integrated fuel oil supply of combined engine and adjusting, overall system is relatively simple, easily realizes.
Description
Technical field
The invention belongs to rocket based combined cycle technical field of engines, the fuel oil supply that relates generally to a kind of RBCC engine withRegulating system, specifically a kind of RBCC engine integration fuel service system based on anhydrous hydrazine. This system is used for belonging toRBCC is to realize the system that integrated fuel oil supply is selected based on anhydrous hydrazine, also can be used as based on one of other type propellantBody fuel service system.
Background technology
Rocket based combined cycle (Rocket Based Combined Cycle, RBCC) engine is based on reusable single-stageThe one that enters orbit aerocraft and propose advanced propulsion system, combines the high thrust-weight ratio of rocket engine and punching engine high specific impulseOperating characteristic, possesses full spatial domain, All Speed Range ability to work, simple in structure, be the long-range strong mobile missile weapon of near space, canReuse the desirable power set of the weaponrys such as earth to orbit and return transportation system. The research of RBCC engine technology has been included inGeneral Armament Department " 12 " project conducts a research at present under the support of the projects such as general assembly common technology, space flight support technologyWork.
RBCC engine is mainly by air intake duct, rocket thrust chamber, stamping combustion chamber, jet pipe and fuel oil supply and regulating systemDeng composition. Because RBCC engine is established and rocket and the large core component dynamical system of punching press two, if these two kinds of assemblies are adoptedThe mode of supply separately, system complex and huge on the one hand, brings considerable restraint to the engineering application of engine; Right on the other handCombined engine, under limited propellant flow rate, supply separately, cannot realize Integral cooling structure design.
For combined cycle engine of new generation, must consider the cooling structure of global design, in this case, adopt oneThe fuel service system of changing is unique selection.
Summary of the invention
Technology of the present invention is dealt with problems and is: overcome existing combined engine rocket thrust chamber and stamping combustion chamber fuel oil is set separatelySupply and regulating system, supply separately and regulate, system complex, and can not carry out integrated cooling deficiency, a kind of base is proposedIn the integrated Propellant Supply of the RBCC of anhydrous hydrazine and regulating system, meet combined cycle engine engineering application of new generation and wantAsk.
Technical solution of the present invention is: based on anhydrous hydrazine, dinitrogen tetroxide and three kinds of storable propellants of kerosene, adopt fireArrow thrust chamber and the integrated supply of stamping combustion chamber propellant and regulating system scheme. Utilize anhydrous hydrazine catalytic decomposition to drive respectively twoIndividual turbine pump, and realize the igniting of rocket thrust chamber. Anhydrous hydrazine adopts squash type supply, thrust chamber and the combustion chamber of independent tankRealize Propellant Supply by turbine pump. Thermal protection adopts integral cooling system design, and thrust chamber body portion passes through dinitrogen tetroxideCarry out coolingly, it is cooling that stamping combustion chamber utilizes kerosene to carry out.
The present invention is a kind of RBCC engine integration fuel service system based on anhydrous hydrazine, comprises engine body, startsMachine body air intake duct foremost, air intake duct incoming flow air enters stamping combustion chamber, with the combustion gas of rocket thrust chamber at stamping combustion chamberCarry out afterburning, the high-temperature fuel gas that burning produces, by jet pipe Accelerating Removal, produces thrust, the fuel oil supply of engine of the present inventionSystem is the RBCC engine integration fuel service system based on anhydrous hydrazine, and integrated fuel service system includes four oxidationsPhenodiazine, anhydrous hydrazine and three kinds of propellants of kerosene, propellant is respectively in tank separately, has kerosene tank, anhydrous hydrazine storageCase and dinitrogen tetroxide) tank, system adopts anhydrous hydrazine to divide through the single constituent element gas generator generation in oxidant road and fuel road hydrazineSeparate combustion gas, drive respectively oxidant turbine and fuel turbine, drive oxidant pump and petrolift work, realize rocket thrust chamber andThe integrated fuel oil supply of stamping combustion chamber; Dinitrogen tetroxide and kerosene, by after second depressurized, are supplied by pump pressure type, realize longTime service, dinitrogen tetroxide supply rocket thrust chamber, kerosene supply is to rocket thrust chamber and stamping combustion chamber. Anhydrous hydrazine passes throughSquash type is fed to the single constituent element gas generator in oxidant road and fuel road, and this scheme provides larger turbine pressure ratio, and performance is high.In the present invention, tank supercharging and blowing all adopt nitrogen, technology maturation, and cost is low. Rocket thrust chamber body of the present invention portion passes throughDinitrogen tetroxide carries out cooling, and it is cooling that stamping combustion chamber utilizes kerosene to carry out, integrated Cooling Design, rocket thrust chamber and punchingPressure chamber coolant system is considered every possible angle, and global optimization, is conducive to realize the reliably cooling of engine. RBCC engine is to fireArrow thrust chamber and stamping combustion chamber adopt integrated Propellant Supply and regulating system, realize whole RBCC engine propellantIntegrated supply and adjusting.
Realization of the present invention is also: the RBCC engine integration fuel service system based on anhydrous hydrazine adopts subsystem to adjustJoint, in the course of the work, regulates respectively the flow of anhydrous hydrazine by oxidant road flow regulator and fuel road flow regulator,Thereby change oxidant road and fuel road single constituent element gas generator power, turbine pump rotating speed and power output, realize four oxidations twoNitrogen and kerosene oil flow regulate. Subsystem regulates simple, and the present invention possesses Project Realization basis.
Realization of the present invention is also: anhydrous hydrazine propellant except catalytic decomposition produces gas driven turbine, a part of anhydrous hydrazineBe fed to the head of rocket thrust chamber by flow regulator and cut-off valve, realize the igniting of thrust chamber dinitrogen tetroxide and kerosene.Take full advantage of the ignition quality of dinitrogen tetroxide and anhydrous hydrazine, simplified ignition system.
The present invention compared with prior art advantage is:
(1) the invention provides a kind of RBCC based on anhydrous hydrazine, dinitrogen tetroxide and three kinds of storable propellants of kerosene sends outThe integrated fuel service system of motivation, having overcome rocket thrust chamber and stamping combustion chamber, to supply separately separately the system that fuel oil causes multipleAssorted, huge shortcoming, combines the three kinds of advantages separately that can store propellant, and density ratio is leapt high, and meets combined engine oneChange fuel oil supply and integrated cooling structure designing requirement, system working service technology maturation, system forms relatively simple, easilyRealize.
(2) combined engine rocket thrust chamber and stamping combustion chamber adopt pump pressure and the integrated supply system of extruding, utilize anhydrousHydrazine catalytic decomposition gas driven turbine pump, realizes dinitrogen tetroxide and the supply of kerosene pump pressure type, and anhydrous hydrazine adopts squeezing of independent tankPressure type supply, can meet the requirement of engine long time service.
(3) adopt anhydrous hydrazine and dinitrogen tetroxide spontaneous combustion to realize rocket thrust chamber igniting, do not need to carry extra igniter,Ignition system is simple, compact, reliable.
(4) combined engine adopts integrated regeneration cooling structure, and rocket thrust chamber and stamping combustion chamber cooling system are comprehensively examinedConsider, global optimization, is conducive to realize the reliably cooling of engine.
Brief description of the drawings
Fig. 1 is the RBCC engine integration fuel service system schematic diagram that the present invention is based on anhydrous hydrazine.
Detailed description of the invention
Below in conjunction with accompanying drawing to the detailed description of the invention:
Embodiment 1
The present invention is for combined cycle engine of new generation, the cooling knot of the global design that RBCC engine promotion room carries outStructure, adopts integrated fuel service system.
The present invention, as a kind of RBCC engine integration fuel service system based on anhydrous hydrazine, referring to Fig. 1, comprises and startingMachine body, engine body is air intake duct 41 foremost, and air intake duct incoming flow air enters stamping combustion chamber 42, with rocket thrust chamber40 combustion gas is carried out afterburning at stamping combustion chamber, and the high-temperature fuel gas that burning produces, by jet pipe 43 Accelerating Removals, produces thrust,The fuel service system of engine of the present invention is the RBCC engine integration fuel service system based on anhydrous hydrazine, integrated combustionOil supply system includes dinitrogen tetroxide, anhydrous hydrazine and three kinds of propellants of kerosene, and propellant is respectively in tank separately,Have kerosene tank 9, anhydrous hydrazine tank 18 and dinitrogen tetroxide 27 tanks, three tanks are all furnished with check-valves and venting separatelyValve, kerosene tank 9 is furnished with check-valves 7 and vent valve 8, and anhydrous hydrazine tank 18 is furnished with check-valves 16 and vent valve 17, four oxygenChange phenodiazine tank 27 and be furnished with check-valves 25 and vent valve 26. All Propellant Supply pipelines are equipped with the cut-off valve of more than,In this example, in kerosene supply pipeline, be provided with 3 cut-off valves, be respectively 29,31 and 38; In dinitrogen tetroxide pipeline, be provided with oneCut-off valve 36; In anhydrous hydrazine supply line, be provided with 3 cut-off valves, be respectively 12,21 and 34. At the supply line of anhydrous hydrazineIn, oxidant road flow regulator 20 is also equipped with, be installed in series with anhydrous hydrazine supply line interrupt flow valve 21; Kerosene stockRoad flow regulator 11 is installed in series with anhydrous hydrazine supply line interrupt flow valve 12; Anhydrous hydrazine ignition path flow regulator 33, withAnhydrous hydrazine supply line interrupt flow valve 34 is installed in series. System adopts anhydrous hydrazine through oxidant road gas generator 22 and fuelThe single constituent element gas generator 13 in road produces callosity and decomposes combustion gas, drives respectively oxidant turbine 23 and fuel turbine 15, drives respectivelyOxidant pump 24 and petrolift 14 are worked, and the integrated pump pressure type fuel oil of realizing rocket thrust chamber 40 and stamping combustion chamber 42 suppliesShould, decompose the subsystem regulative mode technology maturation of gas driven turbine, easily realize by hydrazine. Most of anhydrous hydrazine propellantSupply the single constituent element gas generator of oxidant road gas generator and fuel road and rocket thrust chamber head by squash type, catalysis dividesSeparate and produce gas driven turbine, another part anhydrous hydrazine propellant and dinitrogen tetroxide propellant are realized rocket thrust chamber self-ignition pointFire, is specifically fed to the head of rocket thrust chamber 40 by flow regulator and cut-off valve, realize spontaneous ignition. Adopt nothingWater hydrazine and dinitrogen tetroxide spontaneous combustion realize rocket thrust chamber igniting, do not need to carry extra igniter, ignition system is simple,Compact, reliable.
Dinitrogen tetroxide and kerosene, by after second depressurized valve 6, are fed to engine by pump pressure type. Dinitrogen tetroxide supply fireArrow thrust chamber 40, kerosene supply is to rocket thrust chamber 40 and stamping combustion chamber 42. Three kinds of tank superchargings all adopt nitrogen with blowing down,Nitrogen is provided by gas cylinder 2. Rocket thrust chamber is undertaken cooling by dinitrogen tetroxide, it is cooling that stamping combustion chamber utilizes kerosene to carry out.
The invention provides a kind of RBCC engine one based on anhydrous hydrazine, dinitrogen tetroxide and three kinds of storable propellants of keroseneBody fuel service system, has overcome rocket thrust chamber and stamping combustion chamber and has supplied separately separately system complex, the Pang that fuel oil causesLarge shortcoming, combines the three kinds of advantages separately that can store propellant, and density ratio is leapt high, and meets the integrated fuel oil of combined engineSupply and integrated cooling structure designing requirement, system working service technology maturation, system forms relatively simple, easily realizes.The present invention adopts pump pressure and the integrated supply system of extruding, utilizes anhydrous hydrazine catalytic decomposition gas driven turbine pump, realizes four oxidationsPhenodiazine and the supply of kerosene pump pressure type, anhydrous hydrazine adopts the squash type supply of independent tank, can meet the requirement of engine long time service.
Work of the present invention is: pour high pressure nitrogen to gas cylinder 2 by charge valve 1. When reaching before predetermined working depth, controlSystem processed is switched on to gas cylinder release electric blasting valve 3 according to sequential, and this electric blasting valve is opened, and gases at high pressure filter through filter 4, pass throughAfter one-level pressure relief valve 5 decompressions, then continue after decompression by second depressurized valve 6, respectively to dinitrogen tetroxide and the supercharging of kerosene tank,In the time that tank pressure reaches rated pressure and stablizes, propulsion system is in treating duty. Above-mentioned supply line is three kinds of propellantsThe common sparing of supply. In the time that needs system thrust chamber is worked, oxidant tank 27 starts electric blasting valve 28, anhydrous hydrazine tank 18Startup electric blasting valve 19, kerosene tank 9 start electric blasting valve 10 switches on and opens successively, and system pipeline is carried out to filling, four oxidations twoNitrogen is filled to after oxidant pump 24, and kerosene is filled to after petrolift 14, and anhydrous hydrazine is squeezed to the combustion of oxidant road by gases at high pressureThe single constituent element gas generator 13 in gas generator 22 and fuel road, produces hot combustion gas and drives respectively oxidant turbine 23 after catalytic decompositionWork with pump 24, fuel turbine 15 and pump 14, supply propellant to rocket thrust chamber 40 and stamping combustion chamber 42. Four oxidationsPhenodiazine enters thrust chamber head after by rocket thrust chamber body portion cooling duct, tissue burning; Whole kerosene burn by punching pressBehind cooling duct, chamber, a part enters rocket thrust chamber 40 and dinitrogen tetroxide burning, and a part is fired as stamping combustion chamber 42Material and air burning, produce thrust. In the time that needs engine carries out thrust adjusting, control system is adjusted oxidant road flow respectivelyJoint device 11 and fuel road flow regulator 20 send control instruction, change adjuster aperture, the single constituent element in oxidant road and fuel roadGas generator inlet pressure changes, and the propellant flow rate of single constituent element gas generator adapts to regulating command and reaches predetermined putting downWeighing apparatus point, completion system regulates. After engine operation, start the system of blowing to all propellant tube after engine cut-off valveBlow down on road. Swept-off gases is high pressure nitrogen, is provided by gas cylinder 2. Each propellant blowing pipeline all arranges cut-off valve, keroseneBlow down road and be provided with 3 cut-off valves, be respectively 30,32 and 39; Dinitrogen tetroxide blows down road and is provided with 1 cut-off valve 37;Anhydrous hydrazine blows down road and is provided with 1 cut-off valve 35. After blowing instruction is sent, all cut-off valves are opened, and in pipeline, supply high pressureNitrogen, realizes and blowing down.
The present invention adopts dinitrogen tetroxide, anhydrous hydrazine and three kinds of storable propellant pump pressures of kerosene, pushes integrated supply system,Utilize anhydrous hydrazine catalytic decomposition gas driven turbine pump, realize dinitrogen tetroxide and the supply of kerosene pump pressure type, anhydrous callosity adopts separatelyThe squash type supply of tank, the integrated supply system of three kinds of propellants. The present invention has overcome rocket thrust chamber and stamping combustion chamberSupply separately separately the system complex that fuel oil causes, huge shortcoming, combine the three kinds of advantages separately that can store propellant, closeDegree, than leaping high, meets the integrated fuel oil supply of combined engine and integrated cooling structure designing requirement, system working service technologyMaturation, system forms relatively simple, easily realizes.
Embodiment 2
RBCC engine integration fuel service system based on anhydrous hydrazine is with embodiment 1. The integrated fuel oil supply of the present invention systemSystem adopts subsystem to regulate, and in the present invention, dinitrogen tetroxide and kerosene supply system are Propellant Supply main system, and anhydrous hydrazine advancesAgent supply system is subsystem. Subsystem is all equipped with relevant flow regulator has been installed for each main system, for keroseneSupply system is provided with fuel road flow regulator 11, for dinitrogen tetroxide supply system, oxidant road flow regulator is installed20. In the course of the work, regulate respectively anhydrous hydrazine by oxidant road flow regulator 11 and fuel road flow regulator 20Flow, thus oxidant road and fuel road single constituent element gas generator power, turbine pump rotating speed and power output changed, realize fourNitrous oxide and kerosene oil flow regulate.
Embodiment 3
RBCC engine integration fuel service system based on anhydrous hydrazine is with embodiment 1-2. System oxidant of the present invention andFuel has all adopted independent supply and regulating system, and single channel is adjustable continuously, meets wanting under combined engine different operating modeAsk.
Embodiment 4
RBCC engine integration fuel service system based on anhydrous hydrazine is with embodiment 1-3. Anhydrous hydrazine propellant of the present inventionExcept catalytic decomposition produces gas driven turbine, a part of anhydrous hydrazine is fed to rocket by flow regulator 33 and cut-off valveThe head of thrust chamber 40, realizes the igniting of thrust chamber dinitrogen tetroxide and kerosene, without carrying extra ignition system.
Embodiment 5
RBCC engine integration fuel service system based on anhydrous hydrazine is with embodiment 1-4. Propellant Supply of the present invention is adoptedWith extruding and the integrated supply of pump pressure. Anhydrous hydrazine flow is little, adopts high pressure nitrogen extruding supply oxidant gas generator 22 HesFuel list constituent element gas generator 13, has simplified system schema. Dinitrogen tetroxide and kerosene adopt pump pressure type supply, have reduced to beSystem quality, realizes engine long time service.
RBCC engine integration fuel service system based on anhydrous hydrazine of the present invention, rocket thrust chamber and stamping combustion chamber are usedSame system is realized integrated fuel oil supply and adjusting; System adopts three kinds of dinitrogen tetroxide, anhydrous hydrazine and kerosene can store propellingAgent, drives respectively two turbine pumps by anhydrous hydrazine catalytic decomposition, and extruding is supplied to rocket thrust chamber in the time of system charge, realizesWith dinitrogen tetroxide spontaneous ignition; Anhydrous hydrazine adopts the supply of single tank squash type, and thrust chamber and combustion chamber are realized and being pushed away by turbine pumpEnter agent supply; Thrust chamber body portion is undertaken cooling by dinitrogen tetroxide, it is cooling that stamping combustion chamber utilizes kerosene to carry out. The present invention gramHaving taken combined engine adopts independently supplying system to cause system complex, be difficult to realize to rocket thrust chamber and stamping combustion chamber separatelyThe problems such as integrated regeneration cooling structure design, meet the integrated fuel oil supply of combined engine and adjusting, and overall system is letter relativelySingle, easily realize.
Claims (5)
1. the RBCC engine integration fuel service system based on anhydrous hydrazine, comprises engine body, and engine originallyBody is air intake duct (41) foremost, and air intake duct incoming flow air enters stamping combustion chamber (42), with the combustion gas of rocket thrust chamber (40)Carry out afterburning at stamping combustion chamber, the high-temperature fuel gas that burning produces, by jet pipe (43) Accelerating Removal, produces thrust, its spyLevy and be: the fuel service system of engine is the RBCC engine integration fuel service system based on anhydrous hydrazine, described oneBody fuel service system includes dinitrogen tetroxide, anhydrous hydrazine and three kinds of propellants of kerosene, and propellant is respectively in separatelyIn tank, adopt anhydrous hydrazine through the single constituent element gas generator in oxidant road (22) and the single constituent element gas generator in fuel road (13)Produce hydrazine and decompose combustion gas, drive respectively oxidant turbine (23) and fuel turbine (15), drive respectively oxidant pump (24)And petrolift (14) work, realize the integrated fuel oil supply of rocket thrust chamber (40) and stamping combustion chamber (42); Gas cylinder(2) gases at high pressure in filter through filter (4), by one-level pressure relief valve (5) decompression, then by second depressurized valve(6) after decompression, respectively dinitrogen tetroxide and kerosene tank are carried out to supercharging, utilize anhydrous hydrazine catalytic decomposition gas driven turbinePump, realizes the pump pressure type supply of dinitrogen tetroxide and kerosene, dinitrogen tetroxide supply rocket thrust chamber (40), and kerosene supply arrivesRocket thrust chamber (40) and stamping combustion chamber (42); Anhydrous hydrazine is supplied the single constituent element combustion in oxidant road and fuel road by squash typeGas generator; Three kinds of propellant tank superchargings all adopt nitrogen with blowing down; Rocket thrust chamber body portion is undertaken cold by dinitrogen tetroxideBut, to utilize kerosene to carry out cooling for stamping combustion chamber (42).
2. a kind of RBCC engine integration fuel service system based on anhydrous hydrazine according to claim 1, its spyLevy and be: described integrated fuel service system adopts subsystem to regulate, in the course of the work, by oxidant road Flow-rate adjustmentDevice and fuel road flow regulator regulate respectively the flow of anhydrous hydrazine, occur thereby change the single constituent element combustion gas in oxidant road and fuel roadDevice power, turbine pump rotating speed and power output, realize dinitrogen tetroxide and kerosene oil flow and regulate.
3. a kind of RBCC engine integration fuel service system based on anhydrous hydrazine according to claim 2, its spyLevy and be: anhydrous hydrazine and dinitrogen tetroxide are realized rocket thrust chamber spontaneous ignition, anhydrous hydrazine propellant fires except catalytic decomposition producesOutside the moving turbine of gas drive, a part of anhydrous hydrazine propellant is fed to the head of rocket thrust chamber (40) by flow regulator and cut-off valvePortion, realizes the igniting of thrust chamber dinitrogen tetroxide and kerosene.
4. a kind of RBCC engine integration fuel service system based on anhydrous hydrazine according to claim 3, its spyLevy and be: RBCC engine adopts integrated regeneration cooling structure, rocket thrust chamber adopts dinitrogen tetroxide cooling, punching press combustionBurning chamber adopts whole kerosene cooling.
5. a kind of RBCC engine integration fuel service system based on anhydrous hydrazine according to claim 4, its spyLevy and be: described RBCC Propulsion on Overall Rocket thrust chamber and stamping combustion chamber adopt integrated Propellant Supply and regulate systemSystem, realizes integrated supply and the adjusting of whole RBCC engine propellant.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201318001253.7A CN106134391B (en) | 2013-03-15 | 2013-03-15 | RBCC engine integration fuel service system based on anhydrous hydrazine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201318001253.7A CN106134391B (en) | 2013-03-15 | 2013-03-15 | RBCC engine integration fuel service system based on anhydrous hydrazine |
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| CN106134391B true CN106134391B (en) | 2015-07-01 |
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| CN201318001253.7A Expired - Fee Related CN106134391B (en) | 2013-03-15 | 2013-03-15 | RBCC engine integration fuel service system based on anhydrous hydrazine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106321284A (en) * | 2016-08-19 | 2017-01-11 | 西北工业大学 | Integrated propellant supply system of rocket based combined circulating engine |
| CN110406699A (en) * | 2019-06-19 | 2019-11-05 | 上海空间推进研究所 | Propulsion and generating integration device and its operating method for space power system |
| CN112628016A (en) * | 2020-12-16 | 2021-04-09 | 西安航天动力研究所 | RBCC engine supply system |
-
2013
- 2013-03-15 CN CN201318001253.7A patent/CN106134391B/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106321284A (en) * | 2016-08-19 | 2017-01-11 | 西北工业大学 | Integrated propellant supply system of rocket based combined circulating engine |
| CN106321284B (en) * | 2016-08-19 | 2018-12-11 | 西北工业大学 | A kind of rocket based combined cycle engine propellant integration supply system |
| CN110406699A (en) * | 2019-06-19 | 2019-11-05 | 上海空间推进研究所 | Propulsion and generating integration device and its operating method for space power system |
| CN112628016A (en) * | 2020-12-16 | 2021-04-09 | 西安航天动力研究所 | RBCC engine supply system |
| CN112628016B (en) * | 2020-12-16 | 2022-03-04 | 西安航天动力研究所 | RBCC engine supply system |
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Granted publication date: 20150701 Termination date: 20190315 |