CN205638727U - Novel rocket engine - Google Patents
Novel rocket engine Download PDFInfo
- Publication number
- CN205638727U CN205638727U CN201620512930.XU CN201620512930U CN205638727U CN 205638727 U CN205638727 U CN 205638727U CN 201620512930 U CN201620512930 U CN 201620512930U CN 205638727 U CN205638727 U CN 205638727U
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- CN
- China
- Prior art keywords
- oxidant
- incendiary agent
- conveyance conduit
- group assembly
- outlet
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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.)
- Withdrawn - After Issue
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- Jet Pumps And Other Pumps (AREA)
Abstract
The utility model relates to a novel rocket engine, can effectively solve the problem that liquid propellant rocket engine work efficiency is low, existing in a fixed tray, the afterbody of casing is provided with the combustion chamber, be provided with the spray tube on the bocca of combustion chamber, be provided with the incendiary agent conduit head in the casing respectively, the oxidant conduit head, pump package assembly and oxidant transport pump package assembly are carried to the incendiary agent, the export of incendiary agent conduit head links to each other with the import of incendiary agent transport pump package assembly through first incendiary agent pipeline, second incendiary agent pipeline is equipped with in the export of incendiary agent transport pump package assembly, the export of oxidant conduit head links to each other with the import of oxidant transport pump package assembly through the first oxidative agent pipeline, second oxidant pipeline is equipped with in the export of oxidant transport pump package assembly, the utility model discloses pump package transport efficiency is high, and the loss is low, and incendiary agent and oxidant mix fully, and combustion efficiency is high, reduces the fuel loss, and convenient to use is effectual.
Description
Technical field
This utility model 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.
Utility model content
For above-mentioned situation, for overcoming the defect of prior art, the purpose of this utility model 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 this utility model 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.
This utility model novel structure 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 cross-sectional view of the present utility model.
Fig. 2 is the structural representation of this utility model incendiary agent delivery pump group.
Fig. 3 is the structural representation of this utility model oxidant delivery pump group.
Detailed description of the invention
Below in conjunction with accompanying drawing, detailed description of the invention of the present utility model is described in further detail.
nullBe given by Fig. 1-3，This utility model 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 this utility model 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, this utility model has the advantage 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, this utility model 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.
- 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 |
|---|---|---|---|
| CN201620512930.XU CN205638727U (en) | 2016-05-31 | 2016-05-31 | Novel rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620512930.XU CN205638727U (en) | 2016-05-31 | 2016-05-31 | Novel rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205638727U true CN205638727U (en) | 2016-10-12 |
Family
ID=57051370
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620512930.XU Withdrawn - After Issue CN205638727U (en) | 2016-05-31 | 2016-05-31 | Novel rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205638727U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105822459A (en) * | 2016-05-31 | 2016-08-03 | 河南海力特装备工程有限公司 | Novel rocket engine |
| CN111594349A (en) * | 2020-06-04 | 2020-08-28 | 中国人民解放军战略支援部队航天工程大学 | High-reliability liquid rocket engine system |
-
2016
- 2016-05-31 CN CN201620512930.XU patent/CN205638727U/en not_active Withdrawn - After Issue
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105822459A (en) * | 2016-05-31 | 2016-08-03 | 河南海力特装备工程有限公司 | Novel rocket engine |
| CN105822459B (en) * | 2016-05-31 | 2017-10-31 | 河南海力特装备工程有限公司 | Rocket engine |
| CN111594349A (en) * | 2020-06-04 | 2020-08-28 | 中国人民解放军战略支援部队航天工程大学 | High-reliability liquid rocket engine system |
| CN111594349B (en) * | 2020-06-04 | 2021-05-18 | 中国人民解放军战略支援部队航天工程大学 | High-reliability liquid rocket engine system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20161012 Effective date of abandoning: 20171031 |