CN106194500A - A kind of tridyne pressure charging system being applied to liquid rocket - Google Patents
A kind of tridyne pressure charging system being applied to liquid rocket Download PDFInfo
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- CN106194500A CN106194500A CN201610743677.3A CN201610743677A CN106194500A CN 106194500 A CN106194500 A CN 106194500A CN 201610743677 A CN201610743677 A CN 201610743677A CN 106194500 A CN106194500 A CN 106194500A
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- 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
- F02K9/50—Feeding propellants using pressurised fluid to pressurise the propellants
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- 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
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- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
A kind of tridyne pressure charging system being applied to liquid rocket, including helium hydrogen cylinder (1), oxygen cylinder (2), flow controlling unit and catalytic bed (5)；Helium hydrogen cylinder (1) prestores the mixed gas of helium and hydrogen；Storage oxygen in oxygen cylinder (2)；Two gas cylinders are by the flow of gas output in flow controlling unit control gas cylinder, the mixed gas of helium, hydrogen and the oxygen of output carries out catalytic reaction by catalytic bed (5), generate steam and discharge heat after oxygen and hydrogen reaction, tank supercharging will be entered after remaining to helium, steam and reaction oxygen warming.
Description
Technical field
The present invention relates to the technical scheme of the liquid launch vehicle propellant tank pressure charging system of a kind of efficient and light weight and set
Meter method.
Background technology
Carrier rocket is in flight course, along with the engine combustion that is transported to of propellant, the gas in propellant tank
Pillow is gradually increased, if gas flow does not increases in pneumatic die cushion, pneumatic die cushion pressure can be gradually lowered.And propellant enters rocket engine and needs
The certain pressure wanted, and the demand of the Rocket tank certain rigidity of maintenance, need to carry out lasting QI invigorating to propellant tank pneumatic die cushion,
To maintain the pressure of tank, here it is the task that carrier rocket pressure charging system is completed.Common carrier rocket tank supercharging system
Unite and can be divided into two big classes by medium sources, the medium beyond a class employing propellant, the usually noble gas such as helium or nitrogen,
This kind of pressure charging system generally need to carry single medium basin, such as gas cylinder or liquid storage tank, the gas in gas cylinder
Body to tank supercharging, is to reduce medium carrying amount, by utilizing rocket engine by decompression entrance propellant tank sometimes
Energy heats to medium to improve medium energy；Product after another kind of employing propellant self or propellant combustion is to tank
Supercharging, commonly referred to Autogeneous pressurization formula, sub-fraction propellant is heated by the heat exchanger in electromotor, generates High Temperature High Pressure gas
Body, enters corresponding propellant tank and carries out supercharging, or directly draws a part of combustion gas and lowered the temperature by heat exchanger, enters tank and increases
Pressure.
According to rocket performance requirement, the propellant type that particularly rocket is selected, carrier rocket would generally use above one
Plant or multiple supercharging mode.Gas cylinder air storage supercharging is not by propellant patterns affect, applied widely.But the room temperature without heating
Gas cylinder pressure charging system, owing to gas density is low, the gas cylinder quantity of needs is many, and system structure quality is big.And through heating
Gas pressurization system compares normal temperature high voltage gas cylinder, and gas cylinder carries quantity to be reduced, but heating need to be by rocket engine, and system is multiple
Miscellaneous, between system, degree of coupling is high, and reliability is relatively low.Autogenous pressurization system is applicable to cryogenic propellant such as liquid hydrogen, liquid oxygen and hydrazine
The room temperature propellant such as class and dinitrogen tetroxide.Equally, between autogenous pressurization system, degree of coupling is high, although do not have the extra of gas cylinder etc.
Quality, but in addition to the propellant liquid hydrogen of small-molecular-weight, the pressurization gas quality after the gasification of remaining propellant is all much larger than on rocket
Conventional pressurising medium helium, the propellant total amount therefore consumed is big, and total quality is inefficient, but system adds relative to gas cylinder
The system of hot supercharging is the simplest.It addition, either Autogeneous pressurization is still by the gas cylinder supercharging of engine warm-up, due to rocket
Electromotor is all located at rocket rearmost end, and gas cylinder and pressurization gas entrance are generally at tank top, and pressure charging system needs to cross over whole
Individual rocket propellent tank, span is big, and pipeline moves towards complicated.Simultaneously as heating system or heat exchanger are integrated within the engine,
Pressure charging system cannot be carried out subsystem test when developing, pressure charging system design correctness was difficult to pass through ground in the system development stage
Verify.
Along with development and the carrier rocket diversified demand of China's Space Industry, rocket pressure charging system should meet height can
Lean on, high efficiency performance requirement, also to possess lightweight, the feature of low cost, the design of pressure charging system is brought completely newly by this
Challenge.Traditional supercharging mode the most all cannot meet efficient low-quality feature, more low-quality while of seeking more efficient
The supercharging mode of amount, is one of the demand of following low cost height transport power booster system scheme.
Summary of the invention
The technology of the present invention solves problem: overcome the deficiencies in the prior art, it is provided that a kind of be applied to the three of liquid rocket
Close gas pressure charging system.
The technical solution of the present invention is: a kind of tridyne pressure charging system being applied to liquid rocket: include gaseous mixture
Bottle, oxygen cylinder, flow controlling unit and catalytic bed；
Mixing gas cylinder prestores the mixed gas of noble gas and hydrogen；Oxygen cylinder stores oxygen；Two gas cylinders
By the flow of gas output in flow controlling unit control gas cylinder, the mixed gas of the helium of output, hydrogen and oxygen is led to
Cross catalytic bed and carry out catalytic reaction, generate steam and discharge heat after oxygen and hydrogen reaction, by noble gas, steam and
Tank supercharging is entered after reacting remaining oxygen warming.
The design procedure of described flow controlling unit is as follows:
The first step, according to the demand of tank boost pressure in rocket flight, calculates supercharging helium gas flow and the temperature of demand
Degree state；
Second step, according to the pressurized inert gas flow needed for calculating and state of temperature and noble gas initial storage state
Difference, calculate and add heat needed for noble gas；
3rd step, according to calculating the heat that adds obtained, the thermal discharge of contrast hydrogen-oxygen catalytic reaction, calculate and obtain hydrogen and oxygen
Air demand；
4th step, according to the noble gas calculated, hydrogen, oxygen air demand, determines the mixing ratio of noble gas, hydrogen
Example, selects noble gas hydrogen mixed gas, oxygen respective storage pressure according to structure design requirement；
5th step, according to noble gas hydrogen, the storage pressure of oxygen and traffic demand, determines and meets above-mentioned flow-control
Flow controlling unit.
Helium hydrogen cylinder is immersed in liquid oxygen propellant, and oxygen cylinder room temperature stores.
Described flow controlling unit includes filter, electromagnetic valve, orifice plate, pressure transducer, control unit；Electromagnetic valve and
An orifice plate supply path in series, mixed gas and the quantity of oxygen supply path and orifice plate size are according to gaseous mixture
The control accuracy of body, the storage pressure of oxygen and traffic demand and boost pressure band determines；Multiple supply path in parallel are constituted
The supply path of mixed gas or oxygen；The upstream of supply path connects corresponding gas cylinder by filter, downstream into catalysis
Bed；Pressure transducer measures the pneumatic die cushion pressure in tank, and control unit is according to pneumatic die cushion Stress control each supply path electromagnetic valve
Be turned on and off, make the gas flow of entrance catalytic bed, pressure meet requirement.
Catalytic bed is arranged on tank and is internally located on liquid level.
Silver-plated spherical catalyst particles is used to fill in described catalytic bed.
Catalyst granules uses hollow ceramic ball.
The principle of the present invention is: tridyne catalysis its operation principle of pressure charging system is that (or nitrogen etc. is as supercharging using helium
The noble gas of medium) and a small amount of oxygen and hydrogen be stored in advance in gas cylinder, owing to oxygen, hydrogen content are little, storage
Safety can be guaranteed, three kinds of gases mix in tank pressurization merga pass catalytic bed, and to carry out catalysis anti-
Should, generate steam and discharge substantial amounts of heat after a small amount of oxygen and hydrogen reaction, helium, oxygen, hydrogen, steam are heated
Rear entrance tank supercharging.Whole pressure charging system is all placed in propellant receptacle box top, compact conformation.Tridyne supercharging is compared spontaneous
Pressure charging system degree of independence is high, does not couples with engine system, it is to avoid crossing over the complex pipeline trend of tank, reliability is high, increases
Pressure mass of medium, much smaller than the autogenous pressurization system outside dehydrogenation gas Autogeneous pressurization, is suitable for room temperature and other cryogenic propellants.Meanwhile,
Compared to room temperature gas cylinder supercharging, gas consumption is little, and architecture quality is low, compares and crosses, with gas cylinder air storage, the supercharging mode that electromotor heats,
Heating source is from internal system, and heat exchange efficiency is high, independent of external system, is beneficial to carry out the checking examination of pressure charging system on ground
Test, reduce rocket developing risk and development cost.
The present invention compared with prior art provides the benefit that:
(1) the invention provides a kind of new helium to heat the Rocket tank supercharging mode of supercharging, use hydrogen and oxygen to urge
Changing reaction and blend heating with helium, the efficiency of heating surface is high, and mass of system is little, compares the helium of engine heat exchanger with tradition rocket
Heating, heat exchange efficiency is high, and pressure charging system independence is high, improves the reliability of rocket.
(2) helium hydrogen mixed gas gas cylinder is soaked in liquid oxygen tank and stores by the present invention, and gas density is high, and available use is less
Gas cylinder, reduce architecture quality；
(3) use multipath electrovalve to add the staged flow control mode of orifice plate parallel connection supply, compare decompressor and add orifice plate
Single channel blowing model, flow-control scope is big, and product is simple, it is provided that the reliability of supercharging, multi-channel parallel is the most superfluous simultaneously
Remaining, improve the reliability of rocket pressure charging system further；
(4) catalytic bed is installed with in tank pneumatic die cushion, and catalytic bed heat dissipation capacity is that tank pneumatic die cushion absorbs, and improves thermal effect further
Rate；The dispersibility of catalytic bed exiting exhaust gas, replaces the effect of the gas sinker at tradition Rocket tank top, alleviates the knot of rocket
Structure quality and number of components, improve the reliability of rocket；
(5) catalyst uses the lighting design object of hollow ceramic particle-matrix, beneficially rocket.
Accompanying drawing explanation
Fig. 1 is principle of the invention schematic diagram；
Fig. 2 is that the present invention realizes schematic diagram；
The boost pressure needed in Fig. 3 flight course requires curve.
Detailed description of the invention
Below in conjunction with the accompanying drawings and the present invention is described in further details by example.
The present invention proposes a kind of tridyne pressurization gas technical scheme, it may not be necessary to engine warm-up device is by supercharging gas
Body is heated up to more than 300 DEG C, by regulating the mixed proportion of tridyne, it is achieved the adjustment of warm temperature controls.Its system principle
As it is shown in figure 1, be the hydrogen mixing using helium (or nitrogen etc. is as noble gas of pressurising medium) and a certain amount of ratio, in advance
Being stored in helium hydrogen cylinder 1, oxygen is individually stored in oxygen cylinder 2, according to the demand of Rocket tank 6 supercharging, designs in system
Time design helium hydrogen gaseous mixture and the flow controlling unit 3 and 4 of oxygen (quantity of flow controlling unit can be 1, by a stream
Two-way gas is controlled by amount control unit unification), make helium, hydrogen and oxygen reach suitable ratio, three kinds of gases mix
Merga pass catalytic bed 5 generates steam and discharges substantial amounts of heat after carrying out catalytic reaction, a small amount of oxygen and hydrogen reaction, will
Helium, steam and enter tank supercharging after reacting remaining oxygen warming.Above-mentioned gas ratio, flow etc. control to pass through
Following step is determined:
The first step, according to the demand of tank boost pressure in rocket flight, calculates supercharging helium gas flow and the temperature of demand
Degree state；
Second step, according to the supercharging helium gas flow needed for calculating and state of temperature and the difference of helium initial storage state,
Calculate and add heat needed for helium；
3rd step, according to calculating the heat that adds obtained, the thermal discharge of contrast hydrogen-oxygen catalytic reaction, calculate and obtain hydrogen and oxygen
Air demand；
4th step, according to the helium calculated, hydrogen, oxygen air demand, determines the mixed proportion of helium, hydrogen, according to knot
Structure design requirement selects helium hydrogen mixed gas, oxygen respective storage pressure；
5th step, according to helium hydrogen, the storage pressure of oxygen and traffic demand, determines the stream meeting above-mentioned flow-control
Amount control unit.
For the tridyne supercharging technology scheme of certain carrier rocket LOX tank boost demand design, as shown in Figure 2.Helium
Being stored in gas cylinder group 1 with hydrogen mixed gas, for improving air storage density, gas cylinder group is soaked in the liquid oxygen propellant of LOX tank 6
In, oxygen storage is in oxygen cylinder 2.Helium hydrogen mixed gas flow and oxygen flux control all use electromagnetic valve group to divide with orifice plate
Section controls.
The sequential that wherein helium hydrogen gaseous mixture supply is made up of sequential electromagnetic valve 10 and orifice plate 13 is for gas circuit, and regulation electromagnetism
The regulation of valve I 11 and regulating orifice plate I 14 composition supplies gas circuit I and electromagnetic valve for adjusting II 12 and the regulation of regulating orifice plate II 15 composition
Constitute for gas circuit II.Sequential terminates from the initial supercharging that works of tank supercharging always for gas circuit, and sequential electromagnetic valve 10 is always on.
And regulate and open and close by the control unlatching of LOX tank pressure feedback for electromagnetic valve of gas circuit, LOX tank pressure is surveyed by pressure transducer 26
Amount, force value feeds back to control module 25.When tank pressure is less than the regulation supply gas pressure band of program setting, control module 25
Control and regulation electromagnetic valve 11 or 12 is opened, and increases helium and the air demand of hydrogen, meets tank boost demand, when tank pressure is high
In time regulating supply gas pressure band, close electromagnetic valve for adjusting.Electromagnetic valve for adjusting I 11 and electromagnetic valve for adjusting II 12 control press belt not
With.Three road helium hydrogen gaseous mixtures are transported in catalytic bed 5 by collecting conduit 28 after collecting.
The oxygen sequential that oxygen supply is made up of oxygen sequential electromagnetic valve 20 and orifice plate 22 is for gas circuit and oxygen electromagnetic valve for adjusting 19
Oxygen regulation with regulating orifice plate 21 composition is constituted for gas circuit.Oxygen sequential initiates, from tank supercharging, the boosted junction that always works for gas circuit
Bundle, sequential electromagnetic valve 20 is always on.When control module 25 according to tank pressure judge need to open helium hydrogen electromagnetic valve for adjusting I 11 or
During helium hydrogen electromagnetic valve for adjusting II 12, control oxygen electromagnetic valve for adjusting 19 simultaneously and open, oxygen regulation road supply, improves oxygen air demand.
Oxygen sequential is transported in catalytic bed 5 by collecting conduit 29 after collecting for gas circuit for gas circuit and oxygen regulation.
Catalytic bed 5 entrance is respectively connected to helium hydrogen air supply pipe 28 and oxygen air supply pipe 29, adopts silver-plated spherical urge in catalytic bed
Catalyst particles is filled, and for alleviating catalyst quality, particle-matrix uses hollow ceramic ball.Catalytic bed is installed on inside LOX tank
Top, is placed in tank pneumatic die cushion, catalytic bed outlet tank pneumatic die cushion, through helium, water vapour and reaction residue that catalysis is heated
The gaseous mixture of oxygen is directly entered tank pneumatic die cushion, for tank supercharging.For preventing fifth wheel from entering air supply system to system valve
Can adversely affect with down-stream system, hydrogen helium tank group and oxygen cylinder outlet are respectively arranged filter 9 and filter 23, to confession
Gas filters.
Embodiment
According to tank Boost-Pressure-Desired during rocket flight, carry out tridyne pressure charging system conceptual design and supercharging calculate,
Meeting boost demand, completion system designs.It is embodied as situation as follows:
A) according to Boost-Pressure-Desired, pneumatic die cushion temperature and the tank volume of certain type rocket, tentatively count with the equation of gas state
Calculate the total amount obtaining pressurization gas helium.According to the temperature reached needed for supercharging helium, helium specific heat and hydrogen and oxygen react
Thermal discharge primary Calculation obtains hydrogen and the mixed proportion of oxygen and consumption.On this basis, select storage pressure, design gas cylinder
Volume.Owing to using electromagnetic valve to add the stage flow controlling unit of orifice plate, for ensureing boosted flow, generally select 2～4 tunnels in parallel
Supply, the pressure control range of tank supercharging is the narrowest, and the way being generally selected parallel connection is the highest, and air demand is divided into several strands, can be right
Gas supply flow carries out more precise control.According to gas cylinder volume and the quantity of confession gas circuit, divide each gas cylinder for gas circuit for air pressure
Power band, calculates the orifice plate size on each road, selects pipeline bore, according to actual rocket body structure arrangement system, it is thus achieved that system flow resistance
Characteristic, carries out system boost calculating, revises initial designs by result of calculation, adjusts and opens the tank pressure that electromagnetic valve for adjusting is corresponding
Power band, iteration obtains final system scheme.
B) helium hydrogen mixed gas uses 15 high pressure titanium alloy cylinders 1 to form, gas cylinder volume 30L, operating pressure
35MPa；Oxygen uses 1 carbon fiber winding composites gas cylinder 2 to store, gas cylinder volume 40L, operating pressure 35MPa；Gas cylinder group
Outlet collects conduit 27 latus rectum 10mm, collects supply conduit 28 and 29 latus rectum 20mm.Hydrogen helium mix gas hydrogen quality ratio is
0.8%, the mixed proportion of oxygen and hydrogen is 28～34.Catalytic bed 5 outlet is for pressurization gas temperature range 483K～523K.
C) the rocket launching preparatory stage, before tank repropellenting, ground air supply system is mixed for helium by inflation valve 8
Close gas cylinder group and fill room temperature helium hydrogen gaseous mixture to 20MPa, fill room temperature oxygen to operating pressure by inflation valve 24 for oxygen cylinder 2
35MPa；After propellant liquid oxygen fills, again fill 90K helium hydrogen gaseous mixture to gas cylinder group operating pressure for helium mix gas cylinder group
35MPa。
D) require (see Fig. 3) at rocket flight 0s～180s voltage-controlled for case system according to the boost pressure needed in flight course
In the range of 0.35MPa～0.380MPa, after 180s, oxygen case pressure was gradually reduced with the flight time.According to boost pressure
Requirement, the pressurization control sequential of tridyne pressure charging system is as shown in table 1, during rocket engine starts active section, respectively supplies
It is as follows that road controls logic.
Helium hydrogen mixed gas presses feedback to carry out open and close controlling, specifically for gas circuit 3 way solenoid valve by sequential and case
Control logic be:
Sequential gas supply electromagnetic valve 10 is normally opened, until engine cutoff；
When case forces down in 0.355MPa, open electromagnetic valve for adjusting I 11, close higher than during 0.375MPa.
When case forces down in 0.345MPa, open electromagnetic valve for adjusting II 12, close higher than during 0.365MPa.
Gas oxygen presses feedback to carry out open and close controlling, concrete control logic for gas circuit 2 way solenoid valve by sequential and case
For:
Sequential gas supply electromagnetic valve 20 is normally opened, until engine cutoff；
When case forces down in 0.350MPa, open electromagnetic valve for adjusting 19, close higher than during 0.375MPa.
Table 1 pressure charging system controls time-scale
The present invention is unspecified partly belongs to general knowledge as well known to those skilled in the art.
Claims (7)
1. the tridyne pressure charging system being applied to liquid rocket, it is characterised in that: include mixing gas cylinder (1), oxygen cylinder
(2), flow controlling unit and catalytic bed (5)；
Mixing gas cylinder (1) prestores the mixed gas of noble gas and hydrogen；Storage oxygen in oxygen cylinder (2)；Two gas
Bottle is by the flow of gas output, the mixed gas of the helium of output, hydrogen and oxygen in flow controlling unit control gas cylinder
Generate steam and discharge heat, by noble gas, water after carrying out catalytic reaction, oxygen and hydrogen reaction by catalytic bed (5)
Tank supercharging is entered after steam and the remaining oxygen warming of reaction.
System the most according to claim 1, it is characterised in that: the design procedure of described flow controlling unit is as follows:
The first step, according to the demand of tank boost pressure in rocket flight, calculates supercharging helium gas flow and the temperature shape of demand
State；
Second step, according to the pressurized inert gas flow needed for calculating and state of temperature and the difference of noble gas initial storage state
Different, calculate and add heat needed for noble gas；
3rd step, according to calculating the heat that adds obtained, the thermal discharge of contrast hydrogen-oxygen catalytic reaction, calculate the confession obtaining hydrogen and oxygen
Tolerance；
4th step, according to the noble gas calculated, hydrogen, oxygen air demand, determines the mixed proportion of noble gas, hydrogen, root
Noble gas hydrogen mixed gas, oxygen respective storage pressure is selected according to structure design requirement；
5th step, according to noble gas hydrogen, the storage pressure of oxygen and traffic demand, determines the stream meeting above-mentioned flow-control
Amount control unit.
System the most according to claim 1, it is characterised in that: helium hydrogen cylinder (1) is immersed in liquid oxygen propellant, oxygen cylinder
(2) room temperature storage.
System the most according to claim 2, it is characterised in that: described flow controlling unit include filter, electromagnetic valve,
Orifice plate, pressure transducer, control unit；
Electromagnetic valve and an orifice plate supply path in series, mixed gas and the quantity of oxygen supply path and orifice plate size
Control accuracy according to mixed gas, the storage pressure of oxygen and traffic demand and boost pressure band determines；Multiple supply lead to
Road parallel connection constitutes mixed gas or the supply path of oxygen；The upstream of supply path connects corresponding gas cylinder by filter, under
Trip enters catalytic bed；Pressure transducer measures the pneumatic die cushion pressure in tank, and control unit is according to each supply of pneumatic die cushion Stress control
Being turned on and off of path electromagnetic valve, makes the gas flow of entrance catalytic bed, pressure meet requirement.
System the most according to claim 1, it is characterised in that: catalytic bed is arranged on tank and is internally located on liquid level.
System the most according to claim 1 or 5, it is characterised in that: use silver-plated spheric catalyst in described catalytic bed
Particles filled.
System the most according to claim 6, it is characterised in that: catalyst granules uses hollow ceramic ball.
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| CN201610743677.3A CN106194500B (en) | 2016-08-26 | 2016-08-26 | A kind of tridyne pressure charging system applied to liquid rocket |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106917699A (en) * | 2017-01-19 | 2017-07-04 | 北京航空航天大学 | Hydrogen peroxide solid-liquid rocket is from pressurizing transmission system |
| CN109322764A (en) * | 2018-10-17 | 2019-02-12 | 北京宇航系统工程研究所 | A kind of controllable gas injection type accumulator of low temperature liquid level |
| CN110671232A (en) * | 2019-09-27 | 2020-01-10 | 北京宇航系统工程研究所 | Cold helium pressurization system for liquid oxygen temperature zone |
| CN112664352A (en) * | 2020-12-29 | 2021-04-16 | 上海空间推进研究所 | Solid-liquid mixed type fuel gas pressurization system and control method thereof |
| CN112985813A (en) * | 2021-01-19 | 2021-06-18 | 中国人民解放军63921部队 | Ground full-size equivalent test method for low-temperature pressurized conveying system of carrier rocket |
| CN116006358A (en) * | 2022-12-30 | 2023-04-25 | 北京天兵科技有限公司 | Cold helium pressurization ground test system and method |
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| CN105156231A (en) * | 2015-09-10 | 2015-12-16 | 中国航天科技集团公司第四研究院第四十一研究所 | Gas self-pressurization hybrid rocket engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106917699A (en) * | 2017-01-19 | 2017-07-04 | 北京航空航天大学 | Hydrogen peroxide solid-liquid rocket is from pressurizing transmission system |
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| CN112664352B (en) * | 2020-12-29 | 2022-10-18 | 上海空间推进研究所 | Solid-liquid mixed type fuel gas pressurization system and control method thereof |
| CN112985813A (en) * | 2021-01-19 | 2021-06-18 | 中国人民解放军63921部队 | Ground full-size equivalent test method for low-temperature pressurized conveying system of carrier rocket |
| CN116006358A (en) * | 2022-12-30 | 2023-04-25 | 北京天兵科技有限公司 | Cold helium pressurization ground test system and method |
| CN116006358B (en) * | 2022-12-30 | 2024-06-11 | 北京天兵科技有限公司 | Cold helium pressurization ground test system and method |
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|---|---|
| CN106194500B (en) | 2018-01-05 |
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