CN108708801A - The novel Propellant Management scheme of space propulsion system - Google Patents
The novel Propellant Management scheme of space propulsion system Download PDFInfo
- Publication number
- CN108708801A CN108708801A CN201810554881.XA CN201810554881A CN108708801A CN 108708801 A CN108708801 A CN 108708801A CN 201810554881 A CN201810554881 A CN 201810554881A CN 108708801 A CN108708801 A CN 108708801A
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- China
- Prior art keywords
- propellant
- diaphragm
- fluid path
- tank
- normally closed
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
-
- 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
- F02K9/58—Propellant feed valves
-
- 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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/605—Reservoirs
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a kind of novel Propellant Management scheme of space propulsion system, using by gas circuit isolation diaphragm, tank, cut through the normally closed gas explosion valve group of diaphragm, low pressure fluid path at novel storage unit propellant is managed；1 gas circuit isolation diaphragm is arranged in the tank upstream, and steam and upstream component are isolated during being stored for realizing propellant, ensure that upstream component is not contaminated；The fluid path outlet end of the tank is arranged 1 and cuts through diaphragm, is sealed in tank for realizing propellant；Described to cut through the diaphragm downstream setting normally closed gas explosion valve of 1 low pressure fluid path, under the action of low-pressure gas, the piston cutter movement in the normally closed gas explosion valve of low pressure fluid path cuts through rupture of diaphragm, propellant outflow.The present invention achieve space propulsion system Propellant Management it is safe and reliable, it is at low cost under double effects.
Description
Technical field
The present invention relates to a kind of novel Propellant Management schemes of space propulsion system, especially suitable for there is propellant receptacle
Deposit and the spacecraft propulsion system of supply requirement on.
Background technology
The energy of the propellant as space propulsion system engine, reliable administrative relationships the success or failure of system work.
There are three types of typical Propellant Management schemes：1) drive of high-pressure gas technical solution；2) electric detonation actuation techniques scheme；
3) tank, rupture disc combine low-pressure gas actuation techniques scheme.
Drive of high-pressure gas technical solution is shown in that Fig. 1,1 downstream of tank are arranged the normally closed gas explosion valve 5 of 1 high pressure fluid path and realize propulsion
Agent is sealed up for safekeeping, and the normally closed gas explosion valve of drive of high-pressure gas high pressure fluid path is opened when system works, to realize system Propellant Supply.
Electric detonation actuation techniques scheme is shown in that Fig. 2,1 downstream of tank are arranged the normally closed electric blasting valve 6 of 1 fluid path and realize that propellant is sealed up for safekeeping,
Control system sends out work order and provides high-current supply when system works, and the normally closed electric blasting valve of fluid path is opened, and is to realize
System Propellant Supply；
Tank, rupture disc combination low-pressure gas actuation techniques scheme are shown in that 1 rupture disc 7 is arranged in Fig. 3,1 downstream of tank
Realize that propellant is sealed up for safekeeping, rupture disc ruptures under the action of low-pressure gas when system works, to realize that system propellant supplies
It answers.
Said program cannot be satisfied space propulsion system and be grown to Propellant Management low cost, high safety, period of storage
It is required that.
Invention content
In view of the above technical problems, the present invention proposes a kind of novel Propellant Management scheme of space propulsion system.
The present invention a kind of space propulsion system novel Propellant Management scheme, using by gas circuit isolation diaphragm, tank,
Cut through the normally closed gas explosion valve group of diaphragm, low pressure fluid path at novel storage unit propellant is managed；
1 gas circuit isolation diaphragm is arranged in the tank upstream, steam and upstream group during being stored for realizing propellant
The isolation of part ensures that upstream component is not contaminated；
The fluid path outlet end of the tank is arranged 1 and cuts through diaphragm, is sealed in tank for realizing propellant；
It is described to cut through the diaphragm downstream setting normally closed gas explosion valve of 1 low pressure fluid path, under the action of low-pressure gas, low pressure fluid path
Piston cutter movement in normally closed gas explosion valve cuts through rupture of diaphragm, propellant outflow.
Compared with other typical Propellant Management schemes, the invention has the advantages that：
1) compared with drive of high-pressure gas technical solution, novel Propellant Management scheme proposed by the present invention is effectively evaded
The normally closed gas explosion valve upstream high pipeline of high pressure fluid path can not carry out the problem of operating pressure airtight test, while avoid due to height
Pressure air leakage and lead to the hidden danger of tank high pressure explosion, high safety；
2) compared with the technical solution of electric detonation driving, work order and high-current supply are provided without control system, it is only sharp
Propellant Supply can be realized with the self-contained extruding gas of system, it is at low cost；
3) technical solution that low-pressure gas driving is combined with tank, rupture disc is compared, and cutting through diaphragm thickness can be according to reality
Border demand is designed, and propellant period of storage is flexible；
4) gas circuit isolation diaphragm can effectively prevent pollution of the steam of propellant volatilization in storage process to upstream component.
Novel Propellant Management scheme proposed by the present invention uses for the first time in new model.
Description of the drawings
Fig. 1 is the schematic diagram of drive of high-pressure gas technical solution.
Fig. 2 is the schematic diagram of electric detonation actuation techniques scheme.
Fig. 3 is tank, rupture disc combines the schematic diagram of low-pressure gas actuation techniques scheme.
Fig. 4 is the schematic diagram of the novel Propellant Management scheme of space propulsion system proposed by the present invention.
In figure：1- gas circuit isolation diaphragms；2- tanks；3- cuts through diaphragm；The normally closed gas explosion valve of 4- low pressure fluid path；5- high pressure fluid path
Normally closed gas explosion valve；The normally closed electric blasting valve of 6- fluid path；7- rupture discs.
Specific implementation mode
In the following with reference to the drawings and specific embodiments, the utility model Propellant Management scheme is expanded on further.These embodiments are answered
It is interpreted as being merely to illustrate the present invention rather than limit the scope of the invention.Read the content of the invention recorded it
Afterwards, those skilled in the art can make various modifications or changes to the present invention, these equivalence changes and modification equally fall into this hair
Bright claim limited range.
As shown in figure 4, an embodiment of the present invention provides a kind of novel Propellant Management scheme of space propulsion system, use
By gas circuit isolation diaphragm 1, tank 2, novel storage unit that the normally closed gas explosion valve of diaphragm 3, low pressure fluid path 4 forms is cut through to propellant
It is managed；
1 gas circuit isolation diaphragm 1 is arranged in 2 upstream of the tank, steam and upstream during being stored for realizing propellant
The isolation of component ensures that upstream component is not contaminated；The fluid path outlet end of the tank 2 is arranged 1 and cuts through diaphragm 3, for real
Existing propellant is sealed in tank；It is described to cut through 3 downstream of the diaphragm setting normally closed gas explosion valve 4 of 1 low pressure fluid path, in low-pressure gas
Under effect, the piston cutter movement in the normally closed gas explosion valve of low pressure fluid path 4 cuts through rupture of diaphragm, propellant outflow.
This specific implementation fills 8.5L propellants, evacuated pressure size control into tank 2 by vacuumizing dosing method
System does not rupture in range ensuring gas circuit isolation diaphragm 1 and cut through diaphragm 3.The normally closed gas explosion valve of low pressure fluid path 4 is constantly in closing
State, i.e. valve inner carrier cutter keep original state, to ensure that propellant is reliably sealed in tank.
Under normal mode of operation, the 2.5MPa low-pressure gases that system upstream provides are used for cutting for gas circuit isolation diaphragm all the way
Broken, to make constantly to be pressurized in tank, it is broken to cut through diaphragm for the normally closed gas explosion valve inner carrier cutter movement of low pressure fluid path for another way
It splits, propellant flows to the downstream pipeline, to meet space propulsion system engine work requirements.
As described above, novel Propellant Management scheme proposed by the present invention achieves, Propellant Management is safe and reliable, cost
Low double effects.The present invention is especially suitable on the spacecraft propulsion system for having propellant storage and supply requirement.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited in above-mentioned
Particular implementation, those skilled in the art can make various deformations or amendments within the scope of the claims, this not shadow
Ring the substantive content of the present invention.
Claims (3)
1. the novel Propellant Management scheme of space propulsion system, which is characterized in that using by gas circuit isolation diaphragm (1), tank
(2), the novel storage unit for cutting through normally closed gas explosion valve (4) composition of diaphragm (3), low pressure fluid path is managed propellant；It is described
1 gas circuit isolation diaphragm (1) is arranged in tank (2) upstream；The fluid path outlet end of the tank (2) is arranged 1 and cuts through diaphragm (3),
It is described to cut through diaphragm (3) downstream setting normally closed gas explosion valve (4) of 1 low pressure fluid path.
2. the novel Propellant Management scheme of space propulsion system according to claim 1, which is characterized in that the gas circuit
Steam and upstream component are isolated during isolation diaphragm (1) is stored for realizing propellant, ensure that upstream component is not contaminated.
3. the novel Propellant Management scheme of space propulsion system according to claim 1, which is characterized in that in low pressure gas
Under the action of body, the piston cutter movement in the normally closed gas explosion valve (4) of low pressure fluid path cuts through rupture of diaphragm, propellant outflow.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810554881.XA CN108708801A (en) | 2018-06-01 | 2018-06-01 | The novel Propellant Management scheme of space propulsion system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810554881.XA CN108708801A (en) | 2018-06-01 | 2018-06-01 | The novel Propellant Management scheme of space propulsion system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108708801A true CN108708801A (en) | 2018-10-26 |
Family
ID=63870115
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810554881.XA Pending CN108708801A (en) | 2018-06-01 | 2018-06-01 | The novel Propellant Management scheme of space propulsion system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108708801A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112224449A (en) * | 2020-10-16 | 2021-01-15 | 上海空间推进研究所 | Energy storage type propellant storage tank |
| CN112284658A (en) * | 2020-09-17 | 2021-01-29 | 沈阳航天新光集团有限公司 | Method for enhancing vibration resistance of non-metal diaphragm storage tank and test method |
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| CN107098059A (en) * | 2017-03-16 | 2017-08-29 | 上海空间推进研究所 | A kind of propellant tank height is fine and close, corrosion-resistant rupture disc sealing structure |
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| US10072610B2 (en) * | 2012-11-06 | 2018-09-11 | Arianegroup Sas | Method and a device for feeding a rocket engine |
| US10180118B2 (en) * | 2015-12-31 | 2019-01-15 | The Curators Of The University Of Missouri | Electrical/chemical thruster using the same monopropellant and method |
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- 2018-06-01 CN CN201810554881.XA patent/CN108708801A/en active Pending
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| CN101539068A (en) * | 2009-04-17 | 2009-09-23 | 北京航空航天大学 | Filling device of liquid propellant and method thereof |
| US10072610B2 (en) * | 2012-11-06 | 2018-09-11 | Arianegroup Sas | Method and a device for feeding a rocket engine |
| US20160222918A1 (en) * | 2013-09-30 | 2016-08-04 | Snecma | Device for self-pressurization of a tank |
| CN203614880U (en) * | 2013-11-18 | 2014-05-28 | 北京宇航系统工程研究所 | Pneumatic cutting type propellant isolation valve |
| CN104648696A (en) * | 2014-12-11 | 2015-05-27 | 上海空间推进研究所 | Metal propellant storage tank for spaceflight and manufacturing method thereof |
| US10180118B2 (en) * | 2015-12-31 | 2019-01-15 | The Curators Of The University Of Missouri | Electrical/chemical thruster using the same monopropellant and method |
| CN106439494A (en) * | 2016-09-13 | 2017-02-22 | 北京控制工程研究所 | Asymmetric gas path module applied to dual-mode satellite propulsion system |
| CN106742074A (en) * | 2016-12-20 | 2017-05-31 | 江苏豪然喷射成形合金有限公司 | Ultra lightweighting spacecraft propulsion agent tank |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112284658A (en) * | 2020-09-17 | 2021-01-29 | 沈阳航天新光集团有限公司 | Method for enhancing vibration resistance of non-metal diaphragm storage tank and test method |
| CN112224449A (en) * | 2020-10-16 | 2021-01-15 | 上海空间推进研究所 | Energy storage type propellant storage tank |
| CN112224449B (en) * | 2020-10-16 | 2022-06-14 | 上海空间推进研究所 | Energy storage type propellant storage tank |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181026 |