CN106439494A - Asymmetric gas path module applied to dual-mode satellite propulsion system - Google Patents
Asymmetric gas path module applied to dual-mode satellite propulsion system Download PDFInfo
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- CN106439494A CN106439494A CN201610822166.0A CN201610822166A CN106439494A CN 106439494 A CN106439494 A CN 106439494A CN 201610822166 A CN201610822166 A CN 201610822166A CN 106439494 A CN106439494 A CN 106439494A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D1/00—Pipe-line systems
- F17D1/02—Pipe-line systems for gases or vapours
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17D—PIPE-LINE SYSTEMS; PIPE-LINES
- F17D3/00—Arrangements for supervising or controlling working operations
- F17D3/01—Arrangements for supervising or controlling working operations for controlling, signalling, or supervising the conveyance of a product
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Abstract
An asymmetric gas path module applied to a dual-mode satellite propulsion system comprises a pressure reducer, an oxygen gas path module, gas test interfaces and a fuel gas path module, wherein the pressure reducer receives upstream high-pressure gas and reduces the pressure of the high-pressure gas to pressure required by a downstream part, and an outlet of the pressure reducer is connected with inlets of the oxygen gas path module, the gas test interfaces and the fuel gas path module; an outlet of the oxygen gas path module supplies one path of pressurized gas to the downstream part; an outlet of the fuel gas path module supplies one path of pressurized gas to the downstream part; and an outlet of one gas test interface provides a test interface to outside. The asymmetric gas path module adapts to the characteristics that an oxygen propellant and a fuel propellant of the dual-mode satellite propulsion system are emitted in unequal volumes and the requirements for service lives of an oxygen gas path and a fuel gas path are inconsistent, the asymmetric oxygen gas and fuel gas paths are configured by introducing diaphragm check valves with small opening pressure difference, the problem of operating unbalance of the oxygen gas path and the fuel gas path of the dual-mode satellite propulsion system due to unequal-volume emission of the oxygen propellant and the fuel propellant is solved, and the requirement for long-time in-orbit use of the fuel gas path of the system is met.
Description
Technical field
The present invention relates to satellite propulsion system, mainly for therein double as propellant with anhydrous hydrazine and dinitrogen tetroxide
Pattern propulsion system.
Background technology
Large-scale high rail satellite typically adopts traditional bipropellant propulsion system.This propulsion system includes gases at high pressure storage mould
Block, decompression gas path module, tank, liquid-way system, thruster.This system supplies after the gas path module that reduces pressure is by high pressure air reducing
It is given to tank, extrudes tank propellant, propellant feed to thruster is produced by thrust by liquid-way system.After satellier injection,
Tank is no longer necessary to QI invigorating, and decompression gas path module is isolated by electric blasting valve, does not use.Because this system adopts methyl hydrazine and four
As propellant, achievable oxygen combustion propellant equal-volume discharges nitrous oxide, the therefore Yang Ran road gas of system decompression gas path module
Body flow is identical, and simple symmetric design can guarantee that the Yang Ran road drag balance of decompression gas path module.
In order to improve satellite propulsion system adaptability, on the basis of traditional bipropellant propulsion system, integrated single group unit pushes away
Enter and electric arc propulsion, define dual mode propulsion system.This propulsion system with anhydrous hydrazine and dinitrogen tetroxide as propellant, system
Oxygen combustion is no longer discharged with equal-volume.The non-equal-volume discharge of propellant will lead to the gas flow difference on gas path module Yang Ran road,
Therefore traditional simple symmetric gas path module is no longer applicable.In addition, this system in-orbit period needs by many to fuel tank
Secondary QI invigorating avoids fuel tank hypotony, thus affecting Arcjet performance.Therefore, after satellier injection, gas path module can not
Completely isolated, need to ensure the in-orbit for a long time available of combustion road gas circuit.
In order to solve the problems, such as conventional satellite decompression gas path module do not adapt to dual mode propulsion system use demand, need
Specific demand for dual mode propulsion system designs gas path module.
Content of the invention
Present invention solves the technical problem that being：Provide a kind of asymmetric gas path module, can solve the problem that satellite is double mode and push away
Enter gas circuit flow resistance imbalance problem, the in-orbit life-time service problem of combustion road gas circuit that system is brought due to the discharge of propellant non-equal-volume
Deng meeting the use demand of satellite dual mode propulsion system.
The technical solution of the present invention is：A kind of asymmetric gas path module for dual mode satellite propulsion system, bag
Include decompressor, oxygen road gas path module, first gas test interface, combustion road gas path module；Decompressor receives upstream high gas, and
High pressure air reducing is become downstream desirable pressure, decompressor outlet simultaneously with oxygen road gas path module, first gas test interface, combustion
Road gas path module three partial inlet is connected；The gas path module outlet of oxygen road downstream supplies road pressurization gas；Combustion road gas path module
Outlet downstream supplies road pressurization gas；The outlet of first gas test interface externally provides test interface.
Described oxygen road gas path module includes the normally opened electric blasting valve of the first low pressure, primary diaphragm formula check valve, secondary diaphragm formula list
Add valve to valve, second gas test interface, the normally closed electric blasting valve of the first high pressure, the normally closed electric blasting valve of the second high pressure, oxygen case；First is low
Press normally opened electric detonation valve inlet as oxygen road gas path module entrance, receive the gas after decompressor decompression；The normally opened electric detonation of first low pressure
Valve, primary diaphragm formula check valve, secondary diaphragm formula check valve, the normally closed electric blasting valve of the first high pressure are sequentially connected in series by pipeline；
Separate a bye-pass branch in secondary diaphragm formula one-way valved outlet and connect second gas test interface；In the normally closed electric detonation of the first high pressure
Valve outlet port, entrance respectively separate a bye-pass branch, are connected respectively the second high pressure normally closed electric detonation valve outlet port, entrance, make second
The normally closed electric blasting valve of high pressure and the normally closed electric blasting valve of the first high pressure form parallel-connection structure；In the normally closed electric blasting valve of the second high pressure and the first high pressure
The parallel-connection structure export pipeline that normally closed electric blasting valve is formed separates two-way line branching, and a road adds valve entrance with oxygen case and is connected, separately
One tunnel carries out QI invigorating supercharging as the outlet supply gas entrance oxygen tank of oxygen road gas path module.
It is normally closed that described combustion road gas path module includes tertiary membrane chip check valve, third gas test interface, the 3rd high pressure
Electric blasting valve, combustion gas road latching valve, the normally opened electric blasting valve of the second low pressure, combustion case add valve；Tertiary membrane chip one-way valve inlet is as combustion
Road gas path module entrance, receives the gas after decompressor decompression；Tertiary membrane chip one-way valved outlet separates two-way pipeline, a road with
Third gas test interface entrance is connected, and the normally closed electric blasting valve of another Lu Yu tri- high pressure is connected；The normally closed electric blasting valve of 3rd high pressure goes out
Mouth, entrance respectively separate a road pipeline and are connected respectively the outlet of combustion gas road latching valve, entrance, make combustion gas road latching valve and the 3rd
The normally closed electric blasting valve of high pressure forms parallel-connection structure；Go out in the combustion gas road latching valve parallel-connection structure that normally closed electric blasting valve is formed with the 3rd high pressure
Mouth pipeline separates two-way line branching, and a road adds valve entrance with combustion case and is connected, and normally opened electric blasting valve enters with the second low pressure on another road
Mouth is connected；Second low pressure normally opened electric detonation valve outlet port carries out QI invigorating as the outlet supply gas entrance combustion tank of combustion road gas path module
Supercharging.
Present invention advantage compared with prior art is：
(1) present invention passes through to introduce the little diaphragm type one-way valve of starting differential pressure, solves existing bipropellant propulsion system gas
Road module may differ by excessive problem because the oxygen that check valve starting differential pressure brings greatly fires the tank QI invigorating moment；
(2) present invention passes through symmetrical arrangements check valve, solves dual mode propulsion system Yang Ran road gas circuit flow and differs
Cause the excessive problem of the Yang Ran road gas circuit differences in flow resistance that leads to.Existing symmetrical structure bipropellant propulsion system is used for double mode propulsion
System will lead to Yang Ran road gas circuit differences in flow resistance excessive, and then lead to gas path module to be supplied to the gas pressure that downstream oxygen fires tank
Difference is bigger than normal, affects system worked well；
(3) present invention passes through to fire the latching valve of road gas path module and adds valve configuration, and solving dual mode propulsion system will
The problem of the in-orbit life-time service of Qiu Ran road gas circuit.Latching valve is used for the combustion road gas circuit of open and close at any time, the height in parallel with latching valve
Press normally closed electric blasting valve for the backup do not opened as latching valve, the normally opened electric blasting valve of low pressure in latching valve downstream exists for latching valve
Rail lost efficacy when revealing cut-out gas circuit it is ensured that downstream tank safety.
(4) present invention, by normally opened for oxygen road gas circuit low pressure electric detonation valve position is advanceed to check valve upstream, solves bimodulus
Formula propulsion system is effectively isolated useless module after entering the orbit, improve the problem of system sealing reliability.Conventional satellite bipropellant propulsion
After system is entered the orbit, gas circuit does not use, and oxygen road gas path module is located at high pressure normally closed electric blasting valve downstream, for isolating upstream gas circuit mould
Block.Dual mode propulsion system enters the orbit Hou Yang road gas circuit and oxygen road fluid path does not all use, by normally opened for oxygen road gas circuit low pressure electric blasting valve
Position advances to check valve upstream it can be ensured that isolating whole oxygen road gas circuit and oxygen road fluid path.
(5) the invention provides a kind of gas path module meeting dual mode propulsion system work requirements, solve traditional gas
Road module cannot adapt to the problem of dual mode propulsion system work characteristics.
Brief description
Fig. 1 is a kind of asymmetric gas path module structure chart for dual mode satellite propulsion system of the present invention；
Fig. 2 is oxygen road of the present invention gas path module structure chart；
Fig. 3 is present invention combustion road gas path module structure chart.
Specific embodiment
For the specific demand of dual mode satellite propulsion system, the present invention proposes one kind and is used for dual mode satellite propulsion system
Asymmetric gas path module, this module can adapt to dual mode satellite propulsion system oxygen combustion propellant non-equal-volume discharge and oxygen combustion
The inconsistent two major features of road gas circuit working life demand, by introducing the little diaphragm type one-way valve of starting differential pressure, configuration Yang Ran road
The design such as asymmetric gas circuit solves dual mode satellite propulsion system and discharges, because oxygen fires the non-equal-volume of propellant, the system brought
Yang Ran road operating unbalance problem, and meet the demand that system fires road gas circuit in-orbit use for a long time.
A kind of asymmetric gas path module for dual mode satellite propulsion system includes decompressor, oxygen road gas path module, gas
Body test interface 1, combustion road gas path module.Decompressor is used for for high pressure air reducing becoming downstream desirable pressure.Oxygen road gas path module
Gas after decompression is supplied to oxygen tank, anti-block tank propellant steam swims infiltration, Bing Yang road work back up simultaneously
Whole oxygen road is cut off after being fully completed.First gas test interface 3 is used for during system test obtaining decompressor outlet pressure.Combustion
Road gas path module by reduce pressure after gas be supplied to combustion tank, prevent fire tank propellant steam back up swim infiltration it is ensured that
To combustion tank QI invigorating, combustion road gas circuit can ensure that combustion road gas circuit occurs to isolate in time during leakage failure at any time simultaneously, not under
Trip impacts.
Below according to accompanying drawing, present system is described in detail.
A kind of asymmetric gas path module for dual mode satellite propulsion system is as shown in figure 1, include：Decompressor 1, oxygen road
Gas path module 2, first gas test interface 3, combustion road gas path module 4.Decompressor 1 receive upstream high gas, outlet simultaneously with
Oxygen road gas path module 2, first gas test interface 3, combustion road gas path module 4 three partial inlet are connected.Oxygen road gas path module 2 exports
Downstream supply road pressurization gas.Combustion road gas path module 4 downstream supplies road pressurization gas.First gas test interface 3
Outlet externally provides test interface.
(1) oxygen road gas path module
Oxygen road gas path module 2 is as shown in Figure 2.The normally opened electric blasting valve of first low pressure 5 entrance receives decompression as this module inlet
Gas after device 1 decompression.The normally opened electric blasting valve of first low pressure 5, primary diaphragm formula check valve 6, secondary diaphragm formula check valve 7, first
The normally closed electric blasting valve of high pressure 9 is sequentially connected in series by pipeline.Separate a bye-pass branch in secondary diaphragm formula check valve 7 outlet even
Connect gas test interface 8.Respectively separate a bye-pass branch in the normally closed electric blasting valve of the first high pressure 9 gateway and connect the second high pressure respectively
Normally closed electric blasting valve 10 gateway, makes the second high pressure normally closed electric blasting valve 10 and the normally closed electric blasting valve of the first high pressure 9 form parallel-connection structure.?
The normally closed electric blasting valve of the second high pressure 10 parallel-connection structure export pipeline that normally closed electric blasting valve 9 is formed with the first high pressure separates two-way pipeline and divides
, a road adds valve 11 entrance with oxygen case and is connected, and another road enters oxygen tank as the outlet supply gas of oxygen road gas path module 2
Carry out QI invigorating supercharging.
Oxygen road gas path module 2 receives the gas after decompressor 1 decompression, and gas is input to downstream oxygen tank, and oxygen is store
Case carries out QI invigorating supercharging.The normally opened electric blasting valve of first low pressure 5 is used for oxygen road gas path module and oxygen road part downstream does not use
Shi Duiyang road gas path module and oxygen road part downstream are isolated it is ensured that it no longer affects propulsion system other parts.The
One diaphragm type one-way valve 6 and secondary diaphragm formula check valve 7 are used for preventing in the tank of downstream propellant steam inverse osmosis to gas circuit
Upstream.Gas test interface 8 is used for air-channel system is detected.First high pressure normally closed electric blasting valve 9 and the normally closed electricity of the second high pressure
Quick-fried valve 10 mutually backs up, and is provided commonly for isolation upstream gas and downstream tank before air-channel system enables, improves security of system.Oxygen
Case adds valve 11 as the aerating venting interface of downstream oxygen tank.
Traditional satellite propulsion system gas path module adopts common check valve, its starting differential pressure 0.1MPa.Unlatching bigger than normal
Pressure reduction make system work when, only the propellant expenditure of downstream tank to a certain extent, check valve when tank pressure drop is more
Can open, gas path module can start to carry out QI invigorating to tank.Conventional satellite bipropellant propulsion system oxygen fires propellant
Equal-volume consumes, and constant speed reduces tank pressure simultaneously, and therefore oxygen combustion tank can reach QI invigorating state in the almost identical moment and open
Beginning QI invigorating, whole process oxygen combustion tank pressure gap is less.For dual mode propulsion system, the oxygen combustion non-equal-volume of propellant disappears
Consumption, before QI invigorating, oxygen combustion tank pressure drop rate is inconsistent, and two tanks reach the time of the required pressure of check valve unlatching not
Unanimously.Two tank reduced pressure increase to the time difference meeting check valve unlatching requirement with the increase of air passage one-way valve starting differential pressure
Greatly.When check valve starting differential pressure is bigger than normal used by gas path module, will result in oxygen combustion tank one QI invigorating supercharging, another length
Time is not up to QI invigorating pressurized state, and larger pressure divergence for a long time in oxygen combustion tank.This state has a strong impact on system stability
Work.
Oxygen road of the present invention gas path module 2 and combustion road gas path module 4 adopt diaphragm type one-way valve, and its starting differential pressure is only
0.025MPa, much smaller than the 0.1MPa of traditional check valve, when effectively prevent dual mode propulsion system oxygen combustion tank because of QI invigorating
The oxygen combustion tank larger pressure divergence for a long time that carving has big difference causes.
Dual mode satellite propulsion system oxygen combustion propellant expenditure volume ratio is 0.7：1 about, therefore, Yang Ran road gas circuit QI invigorating
Flow is about 0.7：1.The module symmetry configuration of conventional satellite bipropellant propulsion system oxygen gas road, 0.7：1 gas flow will
Lead to oxygen road gas circuit flow resistance little, combustion road gas circuit flow resistance is big, ultimately result in gas path module and be supplied to oxygen tank gas pressure height, supply
Low to combustion tank gas pressure, cause system operating unbalance.
The present invention adopts oxygen road gas path module and combustion road gas path module symmetrical arrangements.Under same traffic, the self-locking of combustion gas road
Valve flow resistance is much smaller than a diaphragm type one-way valve.Oxygen road of the present invention gas path module configures two diaphragm type one-way valves, combustion road gas circuit
Module configures a diaphragm type one-way valve and a combustion gas road latching valve, ensure that oxygen gas road module in gas flow 0.7：
Under 1 state, oxygen gas road flow resistance is basically identical, meets system operation requirements.
Normally opened for low pressure electric blasting valve is arranged at oxygen gas road module outlet by conventional satellite bipropellant propulsion system gas path module,
When not using for air-channel system after satellier injection, isolate whole gas path module it is ensured that the sealing of propulsion system remainder
Reliability.
Dual mode satellite propulsion system does not use in satellier injection Hou Yang road gas path module and whole oxygen road fluid path part,
Need to be effectively isolated this two parts.Normally opened for first low pressure electric blasting valve 5 is arranged at oxygen road gas circuit entrance by the present invention, ensure that and defends
Star enter the orbit after farthest isolation from oxygen road gas path module and oxygen road fluid path part.
2 combustion road gas path module
Combustion road gas path module 4 is as shown in Figure 3.Tertiary membrane chip check valve 12 entrance receives decompressor as this module inlet
Gas after 1 decompression.Tertiary membrane chip check valve 12 outlet separates two-way pipeline, a road and third gas test interface 13 entrance
It is connected, the normally closed electric blasting valve 15 of another Lu Yu tri- high pressure is connected.3rd high pressure normally closed electric blasting valve 15 gateway respectively separates a road pipe
Road connects the gateway of combustion gas road latching valve 14 respectively, so that combustion gas road latching valve 14 and the normally closed electric blasting valve 15 of the 3rd high pressure is formed simultaneously
Connection structure.The parallel-connection structure export pipeline being formed in combustion gas road latching valve 14 and the normally closed electric blasting valve 15 of the 3rd high pressure separates two-way pipe
Road branch, a road adds valve 17 entrance with combustion case and is connected, and another road electric blasting valve 16 normally opened with the second low pressure entrance is connected.Second is low
Press the outlet supply gas that normally opened electric blasting valve 16 exports as combustion road gas path module 4 to enter combustion tank and carry out QI invigorating supercharging.
Combustion road gas path module 4 receives the gas after decompressor 1 decompression, and gas is input to downstream combustion tank, to combustion storage
Case carries out QI invigorating supercharging.Tertiary membrane chip check valve 12 is used for preventing in the tank of downstream propellant steam inverse osmosis to gas circuit
Trip.Third gas test interface 13 is used for air-channel system is detected.Combustion gas road latching valve 14 exists as combustion road gas path module
Rail carries out one switch valve of QI invigorating supercharging to combustion tank.The normally closed electric blasting valve 15 of 3rd high pressure is as combustion gas road latching valve 14 dozens
Do not open the backup of fault.Gas circuit is isolated for gas circuit, it is to avoid impact propulsion system when the normally opened electric blasting valve of second low pressure 16 breaks down
System downstream normal work.Combustion case adds the aerating venting interface that valve 17 fires tank as downstream.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (3)
1. a kind of asymmetric gas path module for dual mode satellite propulsion system it is characterised in that：Including decompressor (1), oxygen
Road gas path module (2), first gas test interface (3), combustion road gas path module (4)；Decompressor (1) receives upstream high gas,
And high pressure air reducing is become downstream desirable pressure, decompressor (1) outlet is tried with oxygen road gas path module (2), first gas simultaneously
Test interface (3), combustion road gas path module (4) three partial inlet is connected；Oxygen road gas path module (2) outlet downstream supplies a road supercharging
Gas；Combustion road gas path module (4) outlet downstream supplies road pressurization gas；First gas test interface (3) outlet externally carries
For test interface.
2. a kind of asymmetric gas path module for dual mode satellite propulsion system according to claim 1, its feature exists
In：Described oxygen road gas path module (2) includes the normally opened electric blasting valve of the first low pressure (5), primary diaphragm formula check valve (6), secondary diaphragm
Formula check valve (7), second gas test interface (8), the normally closed electric blasting valve of the first high pressure (9), the normally closed electric blasting valve of the second high pressure (10),
Oxygen case adds valve (11)；First low pressure normally opened electric blasting valve (5) entrance, as oxygen road gas path module (2) entrance, receives decompressor (1)
Gas after decompression；The normally opened electric blasting valve of first low pressure (5), primary diaphragm formula check valve (6), secondary diaphragm formula check valve (7),
The normally closed electric blasting valve of one high pressure (9) is sequentially connected in series by pipeline；Separate a bye-pass in secondary diaphragm formula check valve (7) outlet
Branch connects second gas test interface (8)；Respectively separate a bye-pass and divide in the normally closed electric blasting valve of the first high pressure (9) outlet, entrance
, it is connected respectively the normally closed electric blasting valve of the second high pressure (10) outlet, entrance, make the normally closed electric blasting valve of the second high pressure (10) and first
The normally closed electric blasting valve of high pressure (9) forms parallel-connection structure；In the normally closed electric blasting valve of the second high pressure (10) and the normally closed electric blasting valve of the first high pressure (9)
The parallel-connection structure export pipeline being formed separates two-way line branching, and a road adds valve (11) entrance with oxygen case and is connected, and another road is made
Outlet supply gas entrance oxygen tank for oxygen road gas path module (2) carries out QI invigorating supercharging.
3. a kind of asymmetric gas path module for dual mode satellite propulsion system according to claim 1, its feature exists
In：Described combustion road gas path module (4) includes tertiary membrane chip check valve (12), third gas test interface (13), three-hypers
Normally closed electric blasting valve (15), combustion gas road latching valve (14), the normally opened electric blasting valve of the second low pressure (16), combustion case is pressed to add valve (17)；3rd
Diaphragm type one-way valve (12) entrance, as combustion road gas path module (4) entrance, receives the gas after decompressor (1) decompression；Tertiary membrane
Chip check valve (12) outlet separates two-way pipeline, and a road is connected with third gas test interface (13) entrance, another Lu Yu
The normally closed electric blasting valve of three high pressure (15) are connected；It is right respectively that the normally closed electric blasting valve of 3rd high pressure (15) exports, entrance respectively separates a road pipeline
Outlet, the entrance on combustion gas road latching valve (14) should be connected, make combustion gas road latching valve (14) and the normally closed electric blasting valve of the 3rd high pressure (15)
Form parallel-connection structure；The parallel-connection structure export pipeline being formed with the normally closed electric blasting valve of the 3rd high pressure (15) on combustion gas road latching valve (14)
Separate two-way line branching, a road adds valve (17) entrance with combustion case and is connected, another road and the normally opened electric blasting valve of the second low pressure (16)
Entrance is connected；The normally opened electric blasting valve of second low pressure (16) outlet enters combustion storage as the outlet supply gas of combustion road gas path module (4)
Case carries out QI invigorating supercharging.
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| CN201610822166.0A CN106439494B (en) | 2016-09-13 | 2016-09-13 | A kind of asymmetric gas path module for dual mode satellite propulsion system |
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| CN201610822166.0A CN106439494B (en) | 2016-09-13 | 2016-09-13 | A kind of asymmetric gas path module for dual mode satellite propulsion system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108708801A (en) * | 2018-06-01 | 2018-10-26 | 上海空间推进研究所 | The novel Propellant Management scheme of space propulsion system |
| CN109515759A (en) * | 2018-11-15 | 2019-03-26 | 中国空间技术研究院 | A kind of stationary orbit telecommunication satellite propulsion system of craftsmanship optimization |
| CN111911808A (en) * | 2020-06-16 | 2020-11-10 | 西安航天动力研究所 | Integrated pressure reducing device |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6488237B1 (en) * | 2001-09-28 | 2002-12-03 | The Boeing Company | Propellant cross-feed system and method |
| CN106134390B (en) * | 2012-06-18 | 2014-10-22 | 上海空间推进研究所 | A kind of implementation method of space propulsion system |
| CN102926889B (en) * | 2012-10-31 | 2015-05-27 | 北京控制工程研究所 | Method for using bipropellants efficiently |
| CN103213692B (en) * | 2013-04-09 | 2015-05-27 | 北京控制工程研究所 | Method of actively adjusting balanced discharging of parallel connection tanks of satellite two component propelling system |
| CN103950554B (en) * | 2014-04-10 | 2016-05-04 | 中国运载火箭技术研究院 | A kind of spacecraft propulsion agent loading system and method in-orbit |
-
2016
- 2016-09-13 CN CN201610822166.0A patent/CN106439494B/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108708801A (en) * | 2018-06-01 | 2018-10-26 | 上海空间推进研究所 | The novel Propellant Management scheme of space propulsion system |
| CN109515759A (en) * | 2018-11-15 | 2019-03-26 | 中国空间技术研究院 | A kind of stationary orbit telecommunication satellite propulsion system of craftsmanship optimization |
| CN109515759B (en) * | 2018-11-15 | 2020-11-10 | 中国空间技术研究院 | Static orbit communication satellite propulsion system with optimized manufacturability |
| CN111911808A (en) * | 2020-06-16 | 2020-11-10 | 西安航天动力研究所 | Integrated pressure reducing device |
| CN111911808B (en) * | 2020-06-16 | 2022-05-10 | 西安航天动力研究所 | Integrated pressure reducing device |
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| CN106439494B (en) | 2018-08-21 |
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