CN105971768A - Self-pressurization supply system based on regenerative cooling - Google Patents
Self-pressurization supply system based on regenerative cooling Download PDFInfo
- Publication number
- CN105971768A CN105971768A CN201610402329.XA CN201610402329A CN105971768A CN 105971768 A CN105971768 A CN 105971768A CN 201610402329 A CN201610402329 A CN 201610402329A CN 105971768 A CN105971768 A CN 105971768A
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- Prior art keywords
- tank
- liquid
- valve
- supply system
- pressure
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- 238000001816 cooling Methods 0.000 title claims abstract description 39
- 230000001172 regenerating effect Effects 0.000 title abstract 3
- 239000007788 liquid Substances 0.000 claims abstract description 49
- 239000003795 chemical substances by application Substances 0.000 claims abstract description 20
- 239000002826 coolant Substances 0.000 claims abstract description 13
- 239000003380 propellant Substances 0.000 claims description 33
- 239000000956 alloy Substances 0.000 claims description 4
- 238000002485 combustion reaction Methods 0.000 claims description 4
- 229910000881 Cu alloy Inorganic materials 0.000 claims description 2
- 229910000831 Steel Inorganic materials 0.000 claims description 2
- 229910045601 alloy Inorganic materials 0.000 claims description 2
- 239000000843 powder Substances 0.000 claims description 2
- 239000010959 steel Substances 0.000 claims description 2
- 238000003466 welding Methods 0.000 claims description 2
- 229920006395 saturated elastomer Polymers 0.000 abstract description 7
- 238000000034 method Methods 0.000 abstract description 6
- 230000001141 propulsive effect Effects 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 3
- 238000002156 mixing Methods 0.000 abstract 1
- 238000009834 vaporization Methods 0.000 abstract 1
- 230000008016 vaporization Effects 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 17
- PXBRQCKWGAHEHS-UHFFFAOYSA-N dichlorodifluoromethane Chemical compound FC(F)(Cl)Cl PXBRQCKWGAHEHS-UHFFFAOYSA-N 0.000 description 6
- 235000019404 dichlorodifluoromethane Nutrition 0.000 description 6
- 238000002309 gasification Methods 0.000 description 5
- GQPLMRYTRLFLPF-UHFFFAOYSA-N Nitrous Oxide Chemical compound [O-][N+]#N GQPLMRYTRLFLPF-UHFFFAOYSA-N 0.000 description 4
- 235000009854 Cucurbita moschata Nutrition 0.000 description 2
- 240000001980 Cucurbita pepo Species 0.000 description 2
- 235000009852 Cucurbita pepo Nutrition 0.000 description 2
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 2
- 239000000567 combustion gas Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 235000020354 squash Nutrition 0.000 description 2
- 230000036962 time dependent Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- XTYUEDCPRIMJNG-UHFFFAOYSA-N copper zirconium Chemical compound [Cu].[Zr] XTYUEDCPRIMJNG-UHFFFAOYSA-N 0.000 description 1
- 230000006837 decompression Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005485 electric heating Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 239000001272 nitrous oxide Substances 0.000 description 1
- 230000036961 partial effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
- 239000011555 saturated liquid Substances 0.000 description 1
- 239000000377 silicon dioxide Substances 0.000 description 1
- 239000004449 solid propellant Substances 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/50—Feeding propellants using pressurised fluid to pressurise the 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
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
- F02K9/64—Combustion or thrust chambers having cooling arrangements
Landscapes
- 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 belongs to the technical field of spacecraft systems and is mainly applied to liquid propulsion systems or solid-liquid mixing propulsion systems adopting high-saturated vapor pressure propulsive agents. In order to solve the problems that the temperature of propulsive agents and the pressure in a storage box are seriously reduced in the working process of a self-pressurization supply system, a self-pressurization scheme based on regenerative cooling is provided. The self-pressurization supply system is composed of a safety valve, a storage box, a filling pipeline, a filling valve, a one-way valve, a cooling channel, a liquid accumulating cavity, a main supply pipeline, a coolant pipeline, a burning agent pipeline, a main valve, a pressurization pipeline and the like. Propulsive agents cool the wall of a combustor and acquire heat at the same time. The propulsive agents subjected to heat exchange and vaporization return to the storage box to pressurize the storage box. According to the self-pressurization supply system based on regenerative cooling, the pressure intensity of the storage box can be basically maintained to be stable before the liquid propulsive agents in the storage box are completely discharged, and accordingly the effect that the thrust is basically stable is ensured.
Description
Technical field
The invention belongs to Space radiation technical field, particularly to a kind of based on re-generatively cooled from supercharging supply system.
Background technology
Currently used chemical rocket propulsion system has: liquid propelling system, solid propellant propulsion system, gas propulsive system and solid-liquid mixed propulsion system.
In above-mentioned all kinds of propulsion systems, liquid propelling system, solid-liquid propulsion system and gas propulsion system are required for propellant booster transportation apparatus, this kind of
Pressurizer is divided into again pump pressure type and the big class of squash type two.The major advantage of pump pressure type system is that propellant tank need not bear high pressure, can use lighter
The tank of quality, but owing to using turbine pump to add system complexity and cost, it is generally only used for high thrust, long-life Large Launch Vehicle.
For the system that the propellant mass such as aircraft secondary propulsion system (SPS) and Upper Stage Attitude and orbit control system are less, generally employing squash type Propellant Supply system
System.Pressure-feed system simple in construction, reliable, it is divided into again constant pressure type and the pressure type two schemes that falls, it is permanent that the former relies on gas cylinder to pass through air relief valve
Fixed output, for tank supercharging, but pressurization gas and the parts such as gas cylinder and air relief valve considerably increase the quality of system；The latter relies on tank gas
The pressure duty of pad, the requirement to tank pressure-bearing is higher, and its pressure will be gradually lowered, and thrust output is non-constant.
Being that one falls pressure type scheme from supercharging, it utilizes and seals the energy of saturated liquid in container and extruded from container by liquid.Its implementation is as follows:
Propellant is when tank flows out, and the pressure in tank will reduce, and when pressure is less than the saturated vapour pressure of propellant, in tank, remaining liquid advances
Agent will partial gasification, the steam of generation maintains the pressure almost constant in tank.This supercharging mode need not additionally arrange gas cylinder and decompression
Valve, the advantage of existing gas cylinder-tank type pressure-feed system simple in construction, have again that turbopump-feed system tank quality is little, chamber pressure is high concurrently
Premium properties.Lot of experiments demonstrates the feasibility of this supercharging mode, but also indicates that simultaneously, in supercharging supply system work process, by
In air cushion acting and liquid gasification, in tank, the temperature of propellant will reduce, and pressure declines serious so that supply system can not be with constant-quality stream
Amount supply propellant.For solving this problem, simpler method is that propellant tank is carried out thermal compensation.The Electric heating structure generally used
Simply, heating power scalable, but shortcoming is to need to consume to play power resource valuable on arrow/satellite.
Summary of the invention
It is an object of the invention to: decline serious at tradition pressure in supercharging supply system work process, it is impossible in the case of maintaining tank pressure constant,
A kind of propellant is proposed from supercharging supply system.This system uses the method for similar re-generatively cooled, arranges cooling duct at combustor locular wall, allows propelling
Agent flows through cooling duct as coolant and carries out heat exchange, and while cooling chamber wall, propellant obtains heat thus gasified, vaporized
Propellant is sent back to tank, to tank supercharging, reaches the purpose making tank pressure basicly stable.
The present invention " a kind of based on re-generatively cooled from supercharging supply system " is realized by following proposal:
This system includes relief valve 1, tank 2, charging line 3, fill valve 4, check valve 5, cooling duct 6, liquid collecting cavity 7, main supply line
8, coolant line 8a, incendiary agent pipeline 8b, main valve 9, pressure piping 10, combustor 11, propellant 12.
Relief valve 1 is arranged on tank 2, is positioned at tank air cushion end.Charging line 3 connects with tank 2, during filling, and liquid propellant 12 warp
Fill valve 4 is entered tank by charging line 3.Main supply line 8 connects with tank 2, and main supply line 8 arranges main valve 9.Main valve 9 times
Trip, main supply line 8 is divided into coolant line 8a and two branch roads of incendiary agent pipeline 8b, and wherein coolant line 8a connects with liquid collecting cavity 7,
Being also provided with check valve 5 on this branch road, incendiary agent pipeline 8b directly connects with combustor 11.Groove ribbed cooling duct 6 is arranged on combustor 11
Inside and outside wall between, the arrival end of cooling duct 6 is connected with liquid collecting cavity 7, and the port of export is connected with the arrival end of pressure piping 10.Pressure piping 10
Connection cooling duct 6 and tank 2, its port of export is positioned at tank air cushion end.Described air cushion end refers to tank top one end of gas.
Propellant 12 as coolant must be liquid, and requires that it has higher saturated vapor pressure (higher than 1MPa under room temperature, such as, N2O
Saturated vapor pressure when 287.15K is 4.58MPa, and the saturated vapor pressure when 298.15K is about 5.38MPa), it is not easily decomposed under heating condition,
With cooling duct chamber wall materials, there is the preferable compatibility.
The operation principle of cooling duct 6 is identical with common re-generatively cooled mode, (outer by internal groove ribbed structure (inwall) and external supporting structure
Wall) constitute, inwall uses the Cu alloy material that thermal conductivity is higher, mills out rectangular duct and fin by machining and flows for coolant；Outer wall is adopted
With rustless steel or high temperature alloy to bear the high temperature and high pressure in combustor 11.Welding manner is used to seal between external and internal compositions.
Before starting working, open fill valve 4, liquid propellant is filled in tank 2 by charging line 3.After having filled, closedown adds
Note valve 4, leaves the air cushion of certain volume in tank 2, after reaching balance, air-cushion pressure is the saturated vapor pressure of propellant.
When electromotor is started working, opening main valve 9, the liquid propellant in tank 2 flows out from main supply line 8 under air cushion pressure effect, storage
Pressure in case 2 will reduce, and according to phase equilibrium relationship, in tank, a part of liquid will gasify, the gas phase vacated to make up liquid propellant to discharge
Volume.Along with the continuation of work, air cushion volume increases, and the pressure and temperature in tank 2 is all by reduction.
The liquid propellant 12 flowed out by tank 2, after flowing through main valve 9, a part is directly entered combustor 11 through incendiary agent pipeline 8b, fires
Burn reaction and produce high-temperature fuel gas, thus produce thrust.Cooled dose of pipeline 8a of another fraction, flows through check valve 5, enters in liquid collecting cavity 7, by
Liquid collecting cavity 7 is assigned in the outer groove ribbed cooling duct 6 arranged of combustor 11.As this partially liq propellant of coolant in cooling duct 6
The heat that interior absorption combustion gas is transmitted through combustor 11 inwall, temperature raises and gasifies, and cools combustor locular wall simultaneously.Propellant after gasification
After being flowed out by cooling duct 6 in pressure piping 10 returns to tank 2, it is achieved pressure compensation and the thermal compensation to tank 2, thus maintain tank 2
Pressure substantially constant in the course of the work, until tank 2 in liquid propellant all empty, system stalls.
Wherein relief valve 1 is opened when the pressure of tank 2 is higher than secure threshold, discharges portion gas to guarantee that tank pressure will not be too high；Tank 2
Pressure less than secure threshold time, relief valve 1 remains turned-off.
Wherein check valve 5 prevents propellant reverse flow, it is ensured that the gas in cooling duct 6 is entered tank 2 by pressure piping 10.
Described cooling duct 6, can be arranged in a section in front combustion room, powder charge section, afterburner or the jet pipe of solid-liquid hybrid rocket engine or several sections,
Its arrangement can be specifically determined with arranged in series or be arranged in parallel according to the demand of cooling and supercharging.Described cooling duct 6 also can be used for liquid and pushes away
Enter agent rocket engine from supercharging, can be arranged in the combustor of liquid prpellant rocket one or more snippets；Can with arranged in series or
It is arranged in parallel.
The present invention is based on re-generatively cooled is mainly used in liquid propelling system or solid-liquid mixed propulsion system from supercharging supply system, has an advantage in that:
(1) based on re-generatively cooled need not pressurized gas cylinder and turbine pump from supercharging supply system and just propellant can be produced higher boost pressure,
Quality and the complexity of supply system is reduced while ensureing certain boost performance；
(2) based on re-generatively cooled need not, from supercharging supply system, the parts that pressurized gas cylinder, air relief valve and turbine pump etc. involve great expense, reduce
The cost of supply system；
(3) based on re-generatively cooled the cooling to combustion chamber wall surface can be realized while supercharging from supercharging supply system, it is adaptable to liquid advances system
System；For solid-liquid mixed propulsion system, need not arrange the expensive insulating inner linings such as high silica at cooling section, cost-saved, it is ensured that safety.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to required in embodiment or description of the prior art
The accompanying drawing used is briefly described, it should be apparent that, the accompanying drawing in describing below is only some embodiments of the present invention, common for this area
From the point of view of technical staff, on the premise of not paying creative work, it is also possible to obtain other accompanying drawing according to these accompanying drawings.
From the schematic diagram of pressure charging system in Fig. 1 present invention；
The 3 dimensional drawing of groove ribbed cooling duct in Fig. 2 embodiment of the present invention；
The curve chart that in Fig. 3 embodiment of the present invention, tank pressure changed with the working time.
Marginal data:
1-relief valve；2-tank；3-charging line；4-fill valve；5-check valve；6-cooling duct；7-liquid collecting cavity；The main supply line of 8-；8a-is cold
But agent pipeline；8b-incendiary agent pipeline；9-main valve；10-pressure piping；11-combustor；12-liquid propellant；61-internal face of combustion chamber, 62-fires
Burn outdoor wall, 63-groove rib structure.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is clearly and completely described, it is clear that institute
The embodiment described is only a part of embodiment of the present invention rather than whole embodiments.Based on the embodiment in the present invention, the common skill in this area
The every other embodiment that art personnel are obtained under not making creative work premise, broadly falls into the scope of protection of the invention.
The present invention " a kind of based on re-generatively cooled from supercharging supply system " including: relief valve 1, tank 2, charging line 3, fill valve 4, list
To valve 5, cooling duct 6, liquid collecting cavity 7, main supply line 8, coolant line 8a, incendiary agent pipeline 8b, main valve 9, pressure piping 10,
Combustor 11, propellant 12.
In the present embodiment, nitrous oxide N is used2O is as liquid propellant.
Before starting working, open fill valve 4, liquid propellant is filled in tank 2 by charging line 3.After having filled, closedown adds
Note valve 4, leaves the air cushion of certain volume in tank 2, after reaching balance, air-cushion pressure is the saturated vapor pressure of propellant.Ambient temperature is 287K
Time, the pressure in tank is about 4.58MPa.
When electromotor is started working, opening main valve 9, the liquid propellant in tank 2 flows out from main supply line 8 under air cushion pressure effect, with
Time tank 2 in a part of liquid will gasification, air cushion volume increase, pressure and temperature all decreases.
The liquid propellant 12 flowed out by tank 2, after flowing through main valve 9, a part enters combustor 11 through incendiary agent pipeline 8b, carries out burning anti-
High-temperature fuel gas should be produced, thus produce thrust.Cooled dose of pipeline 8a of another part, flows through check valve 5, enters in liquid collecting cavity 7, by liquid collecting cavity
7 are assigned in the outer groove ribbed cooling duct 6 arranged of combustor 11.Wherein the structure of groove ribbed cooling duct 6 is as in figure 2 it is shown, internal face uses
Zirconium copper product, outside wall surface uses 30CrMnSi material.
As it is shown on figure 3, horizontal axis representing time, the longitudinal axis represents tank pressure, and solid line represents that the re-generatively cooled rate of discharge when having 4.1% is used as from supercharging
During gas, the time dependent curve of pressure in tank；When dotted line indicates without re-generatively cooled system, the time dependent curve of pressure in tank.Can
To see, the pressure in tank in the present invention is at 0～about 3500 second period, kept stable.Its principle is: liquid propellant is logical in cooling
Absorbing the heat of combustion gas transmission in road 6, temperature raises and gasifies, simultaneously cooling combustor locular wall.Propellant after gasification is flowed out by cooling duct 6
After, intensified pipeline 10 returns in tank 2, it is achieved pressure compensation and the thermal compensation to tank 2, thus maintains the pressure in tank 2 in work
During constant, be always held at about 4.5MPa, until tank 2 in liquid propellant emptying, system stalls.And without re-generatively cooled
During system, in tank, pressure drastically declines, substantially without stable section.
If in work process, the pressure of tank 2 is higher than secure threshold, and relief valve 1 will be opened, and discharges portion gas to guarantee that tank pressure will not
Too high；When the pressure of tank 2 is less than safety value, relief valve 1 remains turned-off.Wherein check valve 5 prevents propellant reverse flow, it is ensured that cooling is logical
Gas in road 6 is entered tank 2 by pressure piping 10
The above, the only detailed description of the invention of the present invention, but protection scope of the present invention is not limited thereto, any it is familiar with the art
Technical staff in the technical scope that the invention discloses, the change that can readily occur in or replacement, all should contain within protection scope of the present invention.Cause
This, protection scope of the present invention should be as the criterion with the protection domain of claims.
Claims (5)
1. based on re-generatively cooled from a supercharging supply system, it is characterized in that: it includes relief valve (1), tank (2), charging line (3), adds
Note valve (4), check valve (5), cooling duct (6), liquid collecting cavity (7), main supply line (8), coolant line (8a), incendiary agent pipeline (8b), main valve (9),
Pressure piping (10), combustor (11), propellant (12)；
Described relief valve (1) is arranged on the air cushion end of tank (2), and charging line (3) connects with tank (2), and fill valve (4) is arranged on charging line (3)；
Main supply line (8) connects with tank (2)；Main valve (9) is set on main supply line (8)；In main valve (9) downstream, main supply line (8) is divided into coolant hose
Road (8a) and two branch roads of incendiary agent pipeline (8b), wherein coolant line (8a) connects with liquid collecting cavity (7), and described coolant line (8a) is also provided with
Check valve (5a)；Incendiary agent pipeline (8b) directly connects with combustor (11)；Described cooling duct (6) is groove rib structure, and cooling duct (6) are arranged on burning
Between room (11) inside and outside wall, the arrival end of cooling duct (6) is connected with liquid collecting cavity (7), and the port of export is connected with the arrival end of pressure piping (10)；Pressure inlet
Road (10) connection cooling duct (6) and tank (2), its port of export is positioned at the air cushion end of tank (2).
The most according to claim 1 based on re-generatively cooled from supercharging supply system, it is characterized in that: described propellant (12) uses under room temperature full
With the vapour pressure liquid propellant higher than 1MPa.
The most according to claim 1 based on re-generatively cooled from supercharging supply system, it is characterized in that: described cooling duct (6) are by inwall and outer
Wall is constituted, and inwall is milled with rectangular duct and fin towards the side of outer wall；Inwall uses the Cu alloy material that thermal conductivity is higher, and outer wall uses rustless steel
Or high temperature alloy；Welding manner is used to seal between inside and outside wall.
The most according to claim 1 based on re-generatively cooled from supercharging supply system, it is characterized in that: described cooling duct (6) can be arranged in
One or more snippets in front combustion room, afterburner, powder charge section or the jet pipe of solid-liquid hybrid rocket engine；Can be with arranged in series or be arranged in parallel.
The most according to claim 1 based on re-generatively cooled from supercharging supply system, it is characterized in that: described cooling duct (6) can be arranged in
One or more snippets in the combustor of liquid prpellant rocket；Can be with arranged in series or be arranged in parallel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610402329.XA CN105971768B (en) | 2016-06-10 | 2016-06-10 | A kind of supercharging supply system certainly based on re-generatively cooled |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610402329.XA CN105971768B (en) | 2016-06-10 | 2016-06-10 | A kind of supercharging supply system certainly based on re-generatively cooled |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105971768A true CN105971768A (en) | 2016-09-28 |
| CN105971768B CN105971768B (en) | 2017-09-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610402329.XA Expired - Fee Related CN105971768B (en) | 2016-06-10 | 2016-06-10 | A kind of supercharging supply system certainly based on re-generatively cooled |
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Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106567791A (en) * | 2016-11-08 | 2017-04-19 | 上海宇航系统工程研究所 | Forced circulation precooling system |
| CN108019296A (en) * | 2017-12-07 | 2018-05-11 | 上海新力动力设备研究所 | A kind of nitrous oxide is from pressure charging system |
| CN108590887A (en) * | 2018-03-27 | 2018-09-28 | 北京零壹空间科技有限公司 | Cryogenic propulsion system based on steam cooling screen |
| CN108590888A (en) * | 2018-03-27 | 2018-09-28 | 北京零壹空间科技有限公司 | Cryogenic propulsion system |
| CN108826018A (en) * | 2018-07-19 | 2018-11-16 | 北京航天动力研究所 | A kind of microminiature pressure charging system and boosting method based on liquefied gas |
| CN109737829A (en) * | 2019-01-31 | 2019-05-10 | 北京蓝箭空间科技有限公司 | Rocket liquid tank propellant transfer system and carrier rocket |
| CN109779787A (en) * | 2018-12-28 | 2019-05-21 | 中国运载火箭技术研究院 | Reuse aircraft liquid methane circulating precooling system |
| CN109826725A (en) * | 2019-02-19 | 2019-05-31 | 北京星际荣耀空间科技有限公司 | Power mechanism, propulsion system and the liquid rocket system of propulsion system |
| CN110030115A (en) * | 2019-03-27 | 2019-07-19 | 上海宇航系统工程研究所 | A kind of propellant tank combination pressure charging system |
| CN110131073A (en) * | 2019-05-06 | 2019-08-16 | 上海空间推进研究所 | A kind of space propulsion system suitable for the filling of large capacity tank |
| CN110700966A (en) * | 2019-09-18 | 2020-01-17 | 北京星际荣耀空间科技有限公司 | Rocket engine heat exchanger and aerospace vehicle |
| CN110979738A (en) * | 2019-12-23 | 2020-04-10 | 北京宇航推进科技有限公司 | Pressure-drop type integrated power system and power propulsion method |
| CN111042950A (en) * | 2019-12-31 | 2020-04-21 | 西北工业大学 | Motor pump auxiliary speed regulation type turbine pump supply system |
| CN112145316A (en) * | 2018-01-23 | 2020-12-29 | 陕西蓝箭航天技术有限公司 | Liquid engine |
| CN112160848A (en) * | 2020-09-29 | 2021-01-01 | 西北工业大学 | Self-supercharging solid-liquid mixed engine |
| CN112196695A (en) * | 2020-10-19 | 2021-01-08 | 北京天兵科技有限公司 | Self-generated pressurization system and pressurization method for liquid rocket engine |
| CN113386981A (en) * | 2021-06-07 | 2021-09-14 | 上海空间推进研究所 | Corrugated conical column diaphragm storage tank |
| CN113565652A (en) * | 2021-07-27 | 2021-10-29 | 中国人民解放军国防科技大学 | Multilayer fixed high-temperature fluid channel |
| CN114275194A (en) * | 2021-12-14 | 2022-04-05 | 中国运载火箭技术研究院 | Autogenous pressurization system suitable for pressurization of multi-working-condition storage tank of nuclear carrier |
| CN114320667A (en) * | 2021-09-16 | 2022-04-12 | 西北工业大学 | Extrusion type oxidant supply solid-liquid mixing engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4508680A (en) * | 1982-06-08 | 1985-04-02 | National Aerospace Laboratory Of Science And Technology Agency | Method of manufacturing a rocket combustion chamber |
| FR2877403A1 (en) * | 2004-11-02 | 2006-05-05 | Eads Space Transp Sa Sa | DEVICE FOR SUPPLYING A FUEL ENGINE WITH FUEL AND FUEL |
| US20100326044A1 (en) * | 2006-08-25 | 2010-12-30 | Xcor Aerospace | Method for cooling rocket engines |
| CN102308077A (en) * | 2008-12-08 | 2012-01-04 | 火星工程有限公司 | Regeneratively cooled porous media jacket |
| US20130048097A1 (en) * | 2011-08-30 | 2013-02-28 | Firestar Engineering, Llc | Thermal phase separation |
-
2016
- 2016-06-10 CN CN201610402329.XA patent/CN105971768B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4508680A (en) * | 1982-06-08 | 1985-04-02 | National Aerospace Laboratory Of Science And Technology Agency | Method of manufacturing a rocket combustion chamber |
| FR2877403A1 (en) * | 2004-11-02 | 2006-05-05 | Eads Space Transp Sa Sa | DEVICE FOR SUPPLYING A FUEL ENGINE WITH FUEL AND FUEL |
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