CN105822459A - Novel rocket engine - Google Patents
Novel rocket engine Download PDFInfo
- Publication number
- CN105822459A CN105822459A CN201610374172.4A CN201610374172A CN105822459A CN 105822459 A CN105822459 A CN 105822459A CN 201610374172 A CN201610374172 A CN 201610374172A CN 105822459 A CN105822459 A CN 105822459A
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- CN
- China
- Prior art keywords
- oxidant
- incendiary agent
- conveyance conduit
- group assembly
- outlet
- 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.)
- Granted
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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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
-
- 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
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/56—Control
- F02K9/563—Control of propellant feed pumps
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Jet Pumps And Other Pumps (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a novel rocket engine. The problem that a liquid propellant rocket engine is low in work efficiency can be effectively solved. According to the technical scheme, a combustion chamber is arranged at the tail of a shell; a spray pipe is arranged on a fire spitting opening of the combustion chamber; an incendiary agent storage tank, an oxidizing agent storage tank, an incendiary agent conveying pump set assembly and an oxidizing agent conveying pump set assembly are arranged in the shell; an outlet of the incendiary agent storage tank is connected with an inlet of the incendiary agent conveying pump set assembly through a first incendiary agent conveying pipeline; a second incendiary agent conveying pipeline is arranged on an outlet of the incendiary agent conveying pump set assembly; an outlet of the oxidizing agent storage tank is connected with an inlet of the oxidizing agent conveying pump set assembly through a first oxidizing agent conveying pipeline; and a second oxidizing agent conveying pipeline is arranged on an outlet of the oxidizing agent conveying pump set assembly. The novel rocket engine is high in pump set conveying efficiency and low in loss, an incendiary agent and an oxidizing agent are mixed sufficiently, combustion efficiency is high, fuel losses are reduced, use is convenient, and the effect is good.
Description
Technical field
The present invention relates to electromotor, particularly a kind of novel liquid propellant rocket engine.
Background technology
At present, the Propellant System of most liquid propellant rocket motor, commonly used traditional turbine pump conveying propellant burns to combustor, and the tail gas of generation produces propulsive force from jet pipe ejection.This turbine pump Propellant System there is problems in that
1, turbine pump structure complexity, rigorous service condition, improve engine operating efficiency difficulty big.
2, the injection of this structure is short of power, and for the thrust that electromotor to be met is enough, need to carry substantial amounts of propellant and carry out spray combustion, so that the volume of electromotor and weight increase, bearing load increases, and affects its work efficiency.
3, this structure, the propelling dosage being transported to combustor is big, and Fuel Consumption is big, hot type is high-volume big, causes fuel cost increase, energy waste and pollutes environment.
4, the liquid fuel of this kind of electromotor needs can enter combustion chambers burn after overflash, thus result in engine tube line structure complexity, complex manufacturing, adds production and the use cost of electromotor.
Therefore, for above not enough, in the urgent need to developing a kind of novel liquid prpellant rocket.
Summary of the invention
For above-mentioned situation, for overcoming the defect of prior art, the purpose of the present invention is just to provide a kind of new rocket electromotor, can effectively solve that liquid prpellant rocket structure is complicated, need to first vaporize and could enter combustor, ineffective problem.
nullThe technical scheme that the present invention solves is，A kind of new rocket electromotor，Including housing，The afterbody of housing is provided with combustor，It is provided with jet pipe on the bocca of combustor，Incendiary agent tank it is respectively arranged with in housing、Oxidant tank、Incendiary agent delivery pump group assembly and oxidant delivery pump group assembly，The outlet of incendiary agent tank is connected through the import of the first incendiary agent conveyance conduit with incendiary agent delivery pump group assembly，Equipped with the second incendiary agent conveyance conduit in the outlet of incendiary agent delivery pump group assembly，The port of export of the second incendiary agent conveyance conduit stretches into combustor，Equipped with the first high-pressure water mist spray head on the end stretched into，The outlet of oxidant tank is connected through the import of the first oxidant conveyance conduit with oxidant delivery pump group assembly，Equipped with the second oxidant conveyance conduit in the outlet of oxidant delivery pump group assembly，The port of export of the second oxidant conveyance conduit stretches into combustor，Equipped with the second high-pressure water mist spray head on the end stretched into，Constitute incendiary agent and the heavy pressure fine spray injection structure of oxidant，The incendiary agent being contained in incendiary agent tank is delivered to the second incendiary agent conveyance conduit through incendiary agent delivery pump group assembly，And spray after the first high-pressure water mist spray head atomization，Oxidized dose of delivery pump group assembly of the oxidant being contained in oxidant tank is delivered to the second oxidant conveyance conduit，And spray after the second high-pressure water mist spray head atomization，Incendiary agent and oxidant after atomization are sufficiently mixed in combustor，The gas that ignition, combustion produces is derived by jet pipe and is produced propulsive force.
Described incendiary agent delivery pump group assembly includes the first lithium battery and the first centrifugal pump of series connection, the first high-pressure plunger pump, the power output end of the first lithium battery is connected respectively at the power input of the first centrifugal pump, the first high-pressure plunger pump, the import of the first centrifugal pump is connected with the outlet of incendiary agent tank through the first incendiary agent conveyance conduit, equipped with the second incendiary agent conveyance conduit on the first high-pressure plunger delivery side of pump；
Described oxidant delivery pump group assembly includes the second lithium battery and the second centrifugal pump of series connection, the second high-pressure plunger pump, the power output end of the second lithium battery is connected respectively at the power input of the second centrifugal pump, the second high-pressure plunger pump, the import of the second centrifugal pump is connected with the outlet of oxidant tank through the first oxidant conveyance conduit, equipped with the second oxidant conveyance conduit on the second high-pressure plunger delivery side of pump.
Present configuration novelty is unique, and advantages of simple easily produces, and pump group transfer efficiency is high, is lost low, and fully, efficiency of combustion is high for incendiary agent and oxidant mixing, reduces fuel consumption, easy to use, effective, is the innovation on liquid prpellant rocket.
Accompanying drawing explanation
Fig. 1 is the cross-sectional view of the present invention.
Fig. 2 is the structural representation of incendiary agent delivery pump group of the present invention.
Fig. 3 is the structural representation of oxidant delivery pump group of the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing, the detailed description of the invention of the present invention is described in further detail.
nullBe given by Fig. 1-3，The present invention includes housing 1，The afterbody of housing 1 is provided with combustor 11，Jet pipe 12 it is provided with on the bocca of combustor 11，Incendiary agent tank 3 it is respectively arranged with in housing 1、Oxidant tank 5、Incendiary agent delivery pump group assembly 7 and oxidant delivery pump group assembly 8，The outlet of incendiary agent tank 3 is connected through the import of the first incendiary agent conveyance conduit 4a with incendiary agent delivery pump group assembly 7，Equipped with the second incendiary agent conveyance conduit 4b in the outlet of incendiary agent delivery pump group assembly 7，The port of export of the second incendiary agent conveyance conduit 4b stretches into combustor 11，Equipped with the first high-pressure water mist spray head 9 on the end stretched into，The outlet of oxidant tank 5 is connected through the import of the first oxidant conveyance conduit 6a with oxidant delivery pump group assembly 8，Equipped with the second oxidant conveyance conduit 6b in the outlet of oxidant delivery pump group assembly 8，The port of export of the second oxidant conveyance conduit 6b stretches into combustor 11，Equipped with the second high-pressure water mist spray head 10 on the end stretched into，Constitute incendiary agent and the heavy pressure fine spray injection structure of oxidant，The incendiary agent being contained in incendiary agent tank is delivered to the second incendiary agent conveyance conduit through incendiary agent delivery pump group assembly，And spray after the first high-pressure water mist spray head atomization，Oxidized dose of delivery pump group assembly of the oxidant being contained in oxidant tank is delivered to the second oxidant conveyance conduit，And spray after the second high-pressure water mist spray head atomization，Incendiary agent and oxidant after atomization are sufficiently mixed in combustor，The gas that ignition, combustion produces is derived by jet pipe and is produced propulsive force.
Described incendiary agent delivery pump group assembly 7 includes the first lithium battery 13 and first centrifugal pump the 14, first high-pressure plunger pump 15 of series connection, the power output end of the first lithium battery 13 is connected respectively at the power input of first centrifugal pump the 14, first high-pressure plunger pump 15, the import of the first centrifugal pump 14 is connected with the outlet of incendiary agent tank 3 through the first incendiary agent conveyance conduit 4a, equipped with the second incendiary agent conveyance conduit 4b in the outlet of the first high-pressure plunger pump 15；
Described oxidant delivery pump group assembly 8 includes the second lithium battery 16 and second centrifugal pump the 17, second high-pressure plunger pump 18 of series connection, the power output end of the second lithium battery 16 is connected respectively at the power input of second centrifugal pump the 17, second high-pressure plunger pump 18, the import of the second centrifugal pump 17 is connected with the outlet of oxidant tank 5 through the first oxidant conveyance conduit 6a, equipped with the second oxidant conveyance conduit 6b in the outlet of the second high-pressure plunger pump 18；
Lighter (not being given in figure) it is provided with in described combustor 11；
It is provided with controller 2 in described housing 1, controller is connected with oxidant delivery pump group assembly 8 respectively at incendiary agent delivery pump group assembly 7, its overall work is controlled comprehensively, it should be noted that, controller is commercially available prod (prior art), if PLC, model are the singlechip controller of 8051, being i.e. adjusted the duty of two pump groups, this technology is the technological means that those skilled in the art are usual.
First described centrifugal pump the 14, first high-pressure plunger pump the 15, second centrifugal pump 17 and the second high-pressure plunger pump 18 all use resistant material to make, there is corrosion resistance, it is prevented effectively from the erosion that propellant causes, it is ensured that its performance and functional reliability, increases the service life.
Described incendiary agent and oxidant are the commercially available propellant of liquid；
The first described high-pressure water mist spray head 9 and the super fine mist spraying head of Patent No. " 200610017940.7 " that the second high-pressure water mist spray head 10 is applicant's earlier application.
When the present invention uses, the incendiary agent being contained in incendiary agent tank is delivered to the second incendiary agent conveyance conduit through incendiary agent delivery pump group assembly, and spray after the first high-pressure water mist spray head atomization, oxidized dose of delivery pump group assembly of the oxidant being contained in oxidant tank is delivered to the second oxidant conveyance conduit, and spray after the second high-pressure water mist spray head atomization, incendiary agent and oxidant after atomization are sufficiently mixed in combustor, the gas that ignition, combustion produces is derived by jet pipe and is produced propulsive force, compared with prior art, the invention have the advantages that
1, use brand-new centrifugal pump add high pressure plunger pump structure conveying liquid propellant, it is advantageous in that, centrifugal pump is for being provided with the incendiary agent of pressure, oxidant for plunger displacement pump, play the effect of pre-supercharging, reduce the flow loss of the liquid propellant of conveying, it is ensured that the suction of plunger displacement pump, be effectively improved efficiency 30%-40% of plunger displacement pump, technical advanced person, uniqueness, have novelty；
2, owing to using high-pressure water mist spray head directly to spray ultra-fine vaporific incendiary agent, oxidant, mist particle diameter is 1～100 μm, the two is the mixing after-combustion of a kind of state between liquids and gases at combustor, efficiency of combustion improves 95%-99%, in the case of ensureing motor power, considerably reduce usage amount and the carrying amount of propellant, correspondingly reduce the bearing load of electromotor, thus improve the work efficiency of electromotor, also reduce the cost of fuel simultaneously；
3, stability is high, controls accurately；
4, simple in construction and be easy to produce and safeguard, greatly reduce the cost of electromotor.
In sum, the present invention is on the basis of tradition rocket engine, the Propellant System of rocket engine is improved, technical advanced person, uniqueness, simple and reasonable for structure, improve work efficiency and the economy of electromotor, be the technological innovation to existing rocket engine, will be with a wide range of applications at space industry, Social and economic benef@is notable.
Claims (5)
- null1. a new rocket electromotor，Including housing (1)，The afterbody of housing (1) is provided with combustor (11)，Jet pipe (12) it is provided with on the bocca of combustor (11)，It is characterized in that，Incendiary agent tank (3) it is respectively arranged with in housing (1)、Oxidant tank (5)、Incendiary agent delivery pump group assembly (7) and oxidant delivery pump group assembly (8)，The outlet of incendiary agent tank (3) is connected with the import of incendiary agent delivery pump group assembly (7) through the first incendiary agent conveyance conduit (4a)，Equipped with the second incendiary agent conveyance conduit (4b) in the outlet of incendiary agent delivery pump group assembly (7)，The port of export of the second incendiary agent conveyance conduit (4b) stretches into combustor (11)，Equipped with the first high-pressure water mist spray head (9) on the end stretched into，The outlet of oxidant tank (5) is connected with the import of oxidant delivery pump group assembly (8) through the first oxidant conveyance conduit (6a)，Equipped with the second oxidant conveyance conduit (6b) in the outlet of oxidant delivery pump group assembly (8)，The port of export of the second oxidant conveyance conduit (6b) stretches into combustor (11)，Equipped with the second high-pressure water mist spray head (10) on the end stretched into，Constitute incendiary agent and the heavy pressure fine spray injection structure of oxidant；The incendiary agent being contained in incendiary agent tank is delivered to the second incendiary agent conveyance conduit through incendiary agent delivery pump group assembly, and spray after the first high-pressure water mist spray head atomization, oxidized dose of delivery pump group assembly of the oxidant being contained in oxidant tank is delivered to the second oxidant conveyance conduit, and spray after the second high-pressure water mist spray head atomization, incendiary agent and oxidant after atomization are sufficiently mixed in combustor, and the gas that ignition, combustion produces is derived by jet pipe and produced propulsive force.
- New rocket electromotor the most according to claim 1, it is characterized in that, described incendiary agent delivery pump group assembly (7) includes the first lithium battery (13) and first centrifugal pump (14) of series connection, first high-pressure plunger pump (15), the power output end of the first lithium battery (13) is respectively at the first centrifugal pump (14), the power input of the first high-pressure plunger pump (15) is connected, the import of the first centrifugal pump (14) is connected with the outlet of incendiary agent tank (3) through the first incendiary agent conveyance conduit (4a), equipped with the second incendiary agent conveyance conduit (4b) in the outlet of the first high-pressure plunger pump (15).
- New rocket electromotor the most according to claim 1, it is characterized in that, described oxidant delivery pump group assembly (8) includes the second lithium battery (16) and second centrifugal pump (17) of series connection, second high-pressure plunger pump (18), the power output end of the second lithium battery (16) is respectively at the second centrifugal pump (17), the power input of the second high-pressure plunger pump (18) is connected, the import of the second centrifugal pump (17) is connected with the outlet of oxidant tank (5) through the first oxidant conveyance conduit (6a), equipped with the second oxidant conveyance conduit (6b) in the outlet of the second high-pressure plunger pump (18).
- New rocket electromotor the most according to claim 1, it is characterised in that be provided with lighter in described combustor (11).
- New rocket electromotor the most according to claim 1, it is characterised in that being provided with controller (2) in described housing (1), controller is connected with oxidant delivery pump group assembly (8) respectively at incendiary agent delivery pump group assembly (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610374172.4A CN105822459B (en) | 2016-05-31 | 2016-05-31 | Rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610374172.4A CN105822459B (en) | 2016-05-31 | 2016-05-31 | Rocket engine |
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| Publication Number | Publication Date |
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| CN105822459A true CN105822459A (en) | 2016-08-03 |
| CN105822459B CN105822459B (en) | 2017-10-31 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610374172.4A Active CN105822459B (en) | 2016-05-31 | 2016-05-31 | Rocket engine |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106555707A (en) * | 2016-11-30 | 2017-04-05 | 西北工业大学 | Electricity drives propellant-feed system liquid-propellant rocket engine |
| CN108590887A (en) * | 2018-03-27 | 2018-09-28 | 北京零壹空间科技有限公司 | Cryogenic propulsion system based on steam cooling screen |
| CN108590888A (en) * | 2018-03-27 | 2018-09-28 | 北京零壹空间科技有限公司 | Cryogenic propulsion system |
| CN108915898A (en) * | 2018-07-11 | 2018-11-30 | 苏州频聿精密机械有限公司 | A kind of rocket engine reducing fuel consumption |
| CN109057994A (en) * | 2018-07-25 | 2018-12-21 | 苏州频聿精密机械有限公司 | One kind mentioning high performance composite rocket engine |
| CN109139299A (en) * | 2018-09-10 | 2019-01-04 | 北京航空航天大学 | Double pump solid-liquid rocket |
| CN109268169A (en) * | 2018-11-21 | 2019-01-25 | 贵州智慧能源科技有限公司 | A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system |
| CN109373351A (en) * | 2018-11-21 | 2019-02-22 | 贵州智慧能源科技有限公司 | Straight pipe type rocket chamber and power drive unit |
| CN109736971A (en) * | 2018-12-13 | 2019-05-10 | 西安航天动力研究所 | A kind of electronic turbopump-fed liquid rocket engine |
| CN110107427A (en) * | 2019-04-30 | 2019-08-09 | 湖北航天化学技术研究所 | A kind of slurry dosed expelling device and method for solid trust engine powder charge |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106555707A (en) * | 2016-11-30 | 2017-04-05 | 西北工业大学 | Electricity drives propellant-feed system liquid-propellant rocket engine |
| CN108590887A (en) * | 2018-03-27 | 2018-09-28 | 北京零壹空间科技有限公司 | Cryogenic propulsion system based on steam cooling screen |
| CN108590888A (en) * | 2018-03-27 | 2018-09-28 | 北京零壹空间科技有限公司 | Cryogenic propulsion system |
| CN108915898A (en) * | 2018-07-11 | 2018-11-30 | 苏州频聿精密机械有限公司 | A kind of rocket engine reducing fuel consumption |
| CN109057994A (en) * | 2018-07-25 | 2018-12-21 | 苏州频聿精密机械有限公司 | One kind mentioning high performance composite rocket engine |
| CN109139299A (en) * | 2018-09-10 | 2019-01-04 | 北京航空航天大学 | Double pump solid-liquid rocket |
| CN109268169A (en) * | 2018-11-21 | 2019-01-25 | 贵州智慧能源科技有限公司 | A kind of clean energy resource water circulation zero-discharging rocket engine burner electricity generation system |
| CN109373351A (en) * | 2018-11-21 | 2019-02-22 | 贵州智慧能源科技有限公司 | Straight pipe type rocket chamber and power drive unit |
| CN109736971A (en) * | 2018-12-13 | 2019-05-10 | 西安航天动力研究所 | A kind of electronic turbopump-fed liquid rocket engine |
| CN109736971B (en) * | 2018-12-13 | 2021-05-04 | 西安航天动力研究所 | Electric pump pressure type liquid rocket engine |
| CN110107427A (en) * | 2019-04-30 | 2019-08-09 | 湖北航天化学技术研究所 | A kind of slurry dosed expelling device and method for solid trust engine powder charge |
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| CN105822459B (en) | 2017-10-31 |
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