CN110566369A - Pressure supplementing type space propulsion system suitable for high-capacity surface tension storage tank - Google Patents
Pressure supplementing type space propulsion system suitable for high-capacity surface tension storage tank Download PDFInfo
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- CN110566369A CN110566369A CN201910796331.3A CN201910796331A CN110566369A CN 110566369 A CN110566369 A CN 110566369A CN 201910796331 A CN201910796331 A CN 201910796331A CN 110566369 A CN110566369 A CN 110566369A
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- storage tank
- gas
- pressure
- propellant
- valve
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Classifications
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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
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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
- F02K9/56—Control
- F02K9/566—Control elements and safety devices, e.g. pressure relief valves
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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
- F02K9/56—Control
- F02K9/58—Propellant feed valves
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention discloses a pressure supplementing type space propulsion system suitable for a high-capacity surface tension storage tank, which consists of a gas path pressurization system and a liquid path supply system; the gas path pressurization system is connected to an inlet of a storage tank in the liquid path supply system; the liquid path supply system is connected to the engine; the gas circuit pressurization system consists of a main gas cylinder and a downstream pipeline thereof, a pressure supplementing gas cylinder and a downstream pipeline thereof, and can realize the pipeline pressurization and propellant residual quantity measurement of the propulsion system scheme; the liquid path supply system consists of an oxidant storage tank and a downstream pipeline thereof, and a fuel storage tank and a downstream pipeline thereof, and can realize the filling and discharging of the propellant in the system storage tank and the supply of the propellant required by the work of the engine. The invention improves the safety of the system, can realize high-precision and reliable measurement of the residual quantity of the on-orbit propellant, reduces the propellant filling time, improves the propellant filling efficiency and solves the hidden trouble that the propellant in the conventional surface tension storage tank is not filled in place.
Description
Technical Field
The invention relates to the field of spaceflight, in particular to a pressure supplementing type space propulsion system suitable for a high-capacity surface tension storage box.
Background
In the field of aerospace at present, a propulsion system adopting a surface tension storage tank generally cannot realize high-precision propellant residual quantity measurement, and the filling of the surface tension storage tank always has the hidden trouble of incomplete filling due to the fact that a filling pipeline clamps air, so that the whole filling process is long, the filling efficiency is low, and the propulsion system with the large-capacity surface tension storage tank is particularly prominent. Therefore, a propulsion system which can realize high-precision propellant residual quantity measurement, has high filling efficiency, does not have hidden danger of failure in filling and has high system safety is required to be designed.
Disclosure of Invention
Aiming at the defects of a propulsion system of a traditional aerospace surface tension storage box, the invention provides a pressure supplementing type space propulsion system suitable for a high-capacity surface tension storage box.
The purpose of the invention is realized by the following technical scheme:
A pressure-compensating space propulsion system suitable for a high-capacity surface tension storage tank is composed of a gas path pressurization system and a liquid path supply system, wherein the gas path pressurization system is connected to an inlet of the storage tank in the liquid path supply system; the liquid path supply system is connected to an engine; the gas circuit pressurization system consists of a main gas cylinder and a downstream pipeline thereof, and a pressure supplementing gas cylinder and a downstream pipeline thereof; the liquid path supply system consists of an oxidant storage tank and a downstream pipeline thereof, and a fuel storage tank and a downstream pipeline thereof.
furthermore, the gas circuit pressurization system comprises a main gas cylinder with a larger volume and a pressure supplementing gas cylinder with a smaller volume; the main gas bottle is used for storing high-pressure gas required by the pressurization of the whole propulsion system and is used as a primary pressurization gas source for the pressurization of the storage tank; the pressure supplementing gas cylinder is used for assisting the measurement of the propellant surplus of the whole propulsion system, and is communicated with a primary pressurized gas source through an L3 valve to serve as a secondary pressurized gas source for pressurizing the storage tank.
Furthermore, the volume of the main gas cylinder needs to meet the requirement of the pressurized gas in the whole propelling task, and the number of the main gas cylinders can be set into a plurality according to the total assembly layout; the volume of the pressure-supplementing gas cylinder requires that the liquid level of a propellant in the storage tank changes slightly in the process of directly pressurizing the storage tank, so that the pressure of the pressure-supplementing gas cylinder can change obviously; therefore, the pressure change value of the pressure compensation gas cylinder can be measured according to the high-precision pressure sensor, and the residual quantity of the storage tank propellant can be measured by a PVT method.
Furthermore, the gas path pressurization system is provided with a pressure sensor P2, a pressure sensor P3 and a pressure sensor P4 which have high measurement accuracy.
Further, in the gas path pressurization system, a check valve C1 is arranged at the upstream of the inlet of the oxidant storage tank, a check valve C2 is arranged at the upstream of the inlet of the fuel storage tank, and the check valve C1 and the check valve C2 allow the forward flow of the pipeline working medium and block the reverse flow of the pipeline working medium.
Furthermore, in the gas circuit pressurization system, a gas circuit charging and discharging valve D3 and a gas circuit charging and discharging valve D4 are respectively arranged at the upstream of the oxidant storage tank and the fuel storage tank, and the gas charging and discharging valve D3 and the gas circuit charging and discharging valve D4 are used for discharging gas in a storage tank gas cavity during propellant charging so as to facilitate propellant charging in place; and on the other hand, the device is used for pre-pressurizing the air cavity of the storage tank after the propellant is filled.
Further, in the liquid path supply system, a pneumatic stop valve K1 is arranged at the outlet of the oxidant storage tank, a pneumatic stop valve K2 is arranged at the outlet of the fuel storage tank, and the pneumatic stop valves are used for vacuumizing a filling pipeline between K1 and D5 and between K2 and D6 at the downstream of the auxiliary storage tank; the pneumatic stop valves K1 and K2 are normally open under normal working conditions, and the pneumatic stop valves K1 and K2 are closed only when driving pressure is provided for K1 and K2 through a ground gas distribution platform; before filling, after K1 and K2 are driven to be closed by a ground gas distribution table, the filling and discharging valves D5 and D6 can realize the vacuum pumping of the filling pipeline at the downstream of the storage tank.
Further, in the liquid path supply system, one electric explosion valve B1 and one electric explosion valve B2 are respectively provided downstream of the oxidant storage tank and the fuel storage tank; the electric explosion valve B1 and the electric explosion valve B2 are normally closed electric explosion valves, namely normally in a closed state. The valve is used for blocking communication between a filling pipeline at the downstream of the storage tank and a pipeline from the downstream of the electric explosion valve to the engine.
Compared with the prior art, the invention has the following beneficial effects:
For a propulsion system with a large-capacity surface tension storage tank, the scheme improves the safety of the system, can realize high-precision and reliable measurement of the residual quantity of the on-orbit propellant, reduces the propellant filling time, improves the propellant filling efficiency, and solves the hidden trouble that the propellant in the conventional surface tension storage tank is not filled in place.
Drawings
FIG. 1 is a system block diagram of a pressurized space propulsion system suitable for use with a high capacity surface tension reservoir, according to an embodiment of the present invention.
Detailed Description
The invention is further explained in detail with the abstract attached drawing.
As shown in fig. 1, an embodiment of the present invention provides a pressure-compensated space propulsion system suitable for a high-capacity surface tension tank, which is composed of a gas path pressurization system and a liquid path supply system, wherein the gas path pressurization system is connected to an inlet of the tank in the liquid path supply system; the liquid path supply system is connected to the engine.
The gas circuit pressurization system comprises two subsystems, namely a main gas bottle and a downstream pipeline subsystem thereof (consisting of P1, D1, L1, R1 components and connecting pipelines), and a pressure supplementing gas bottle and a downstream pipeline subsystem thereof (consisting of P2, D2, L2, R2, C1-C2, D3-D4, P3-P4 components and connecting pipelines); the main gas cylinder is communicated with the pressure supplementing gas cylinder through a stop valve L3.
The liquid path supply system comprises an oxidant storage tank and a downstream pipeline subsystem thereof (consisting of K1, D5, P5, B1 and a connecting pipeline), and a fuel storage tank and a downstream pipeline subsystem thereof (consisting of K2, D6, P6, B2 and a connecting pipeline). The oxidant storage tank and the downstream pipeline subsystem thereof are physically isolated from the fuel storage tank and the downstream pipeline subsystem thereof.
The gas circuit pressurization system comprises a main gas cylinder with a large volume and a pressure supplementing gas cylinder with a small volume. The main gas bottle is used for storing high-pressure gas required by the pressurization of the whole propulsion system and is used as a primary pressurized gas source for the pressurization of the four storage tanks; the pressure supplementing gas cylinder is used for assisting the measurement of the propellant surplus of the whole propulsion system, and is communicated with a primary pressurized gas source (a main gas cylinder) through an L3 valve to serve as a secondary pressurized gas source for pressurizing four storage tanks. The main gas cylinder is used as a primary gas source, the storage tank is not directly pressurized by a downstream pipeline, but the storage tank is indirectly pressurized by a pressure supplementing gas cylinder used as a secondary gas source. The main gas cylinders are characterized by having larger volume and meeting the requirement of the pressurized gas in the whole propulsion task, in addition, the number of the main gas cylinders is not limited to one, and the main gas cylinders can be optimized according to the general assembly layout, and the number of the main gas cylinders can be set to be a plurality; the pressure-supplementing gas cylinder is characterized by having smaller volume, and obvious pressure change can be formed for the pressure-supplementing gas cylinder by small change of liquid level of a propellant in the storage tank in the process of directly pressurizing the storage tank. Therefore, the residual quantity of the storage tank propellant can be measured by a PVT method according to the pressure change value of the pressure compensation gas cylinder measured by the high-precision pressure sensor. When the pressure of the pressurized gas cylinder is insufficient, the L3 valve can be opened, the pressure supplementing gas cylinder (secondary gas source) is supplemented with gas through the main gas cylinder (primary gas source), the L3 valve is closed after the pressure supplementing gas cylinder completes gas supplementing, and continuous measurement of the residual propellant in the storage tank can be continuously realized through the pressure change of the pressure supplementing gas cylinder.
The pressure sensor P2, the pressure sensor P3 and the pressure sensor P4 in the gas circuit pressurization system have high measurement accuracy, and high-accuracy and reliable measurement can be realized when the propellant residual quantity measurement is carried out through the pressure change of the pressure compensation cylinder.
In the gas path pressurization system, a check valve C1 is arranged at the upstream of the inlet of the oxidant storage tank, and a check valve C2 is arranged at the upstream of the inlet of the fuel storage tank. The check valve C1 and the check valve C2 allow the forward flow of the working fluid in the corresponding pipeline (the arrow of the check valve indicates the direction in the figure) and block the reverse flow of the working fluid in the corresponding pipeline. The reason for providing the check valve is: because the gas and liquid cavities of the surface tension storage tank are communicated, the one-way valve arranged at the upstream of the storage tank can prevent the saturated steam of the oxidant and the fuel from meeting in a gas circuit pipeline and generating explosion through chemical reaction. Therefore, the safety of the system can be effectively improved by adding the C1 and C2 one-way valves.
In the gas path pressurization system, a gas path charging and discharging valve D3 and a gas path charging and discharging valve D4 are respectively arranged at the upstream of the oxidant storage tank and the fuel storage tank. The air path charging and discharging valve can be communicated and closed with the outside through manually controlling the inner cavity of the storage tank. The reason for arranging the gas circuit charging and discharging valves D3 and D4 is that: on one hand, the device is used for discharging gas in a gas cavity of the storage tank during propellant filling, so that the propellant can be conveniently filled in place; and on the other hand, the method is used for pre-pressurizing the air cavity of the storage tank after the propellant is filled, so that the rigidity of a structural system can be effectively improved, and the liquid level swing of the storage tank is reduced.
In the liquid path supply system, a pneumatic stop valve K1 is arranged at the outlet of the oxidant storage tank, and a pneumatic stop valve K2 is arranged at the outlet of the fuel storage tank and is used for vacuumizing a filling pipeline between K1 and D5 and between K2 and D6 at the downstream of the auxiliary storage tank. The pneumatic stop valves K1, K2 are in a normally open state under normal working conditions, and the pneumatic stop valves K1, K2 are in a closed state only when driving pressure is provided for K1, K2 through a ground gas distribution table. Before the propellant is filled, after K1 and K2 are driven to be closed by a ground gas distribution table, the filling and discharging valves D5 and D6 can realize the vacuum pumping of the filling pipeline at the downstream of the storage tank. The reason for setting the K1 and K2 stop valves and the evacuation thereof is as follows: when a large-capacity surface tension tank is filled, if the downstream filling lines (lines between D5 and K1 and between D6 and K2) become air-filled, it is difficult to add propellant to the surface tension tank, thereby risking insufficient filling of the propellant. Therefore, the filling pipeline at the downstream of the storage tank needs to be vacuumized before filling, so that the filling pipeline is prevented from air inclusion in the filling process, and the hidden danger that the propellant is not filled in place is avoided. In addition, gas in the surface tension storage tank has no influence on propellant filling, and in order to improve the vacuumizing efficiency, save the vacuumizing time and avoid vacuumizing the inner cavity of the high-capacity surface tension storage tank, the communication between the downstream pipeline of the storage tank and the inside of the storage tank needs to be blocked by closing K1 and K2 before vacuumizing.
In the liquid path supply system, one electroexplosion valve B1 and one electroexplosion valve B2 are provided downstream of the oxidizer tank and the fuel tank, respectively. The electric explosion valves B1 and B2 are normally closed electric explosion valves, namely normally in a closed state. The electric explosion valves B1 and B2 are used for blocking communication between a charging pipeline at the downstream of the storage tank and a pipeline from the downstream of the electric explosion valve to the engine, so that on one hand, the pipeline from the downstream of the storage tank to the engine is prevented from being vacuumized, on the other hand, propellant can be prevented from entering the engine too early, and the safety of the system is improved.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.
Claims (8)
1. The pressure-supplementing space propulsion system is characterized by consisting of a gas path pressurization system and a liquid path supply system, wherein the gas path pressurization system is connected to an inlet of a storage tank in the liquid path supply system; the liquid path supply system is connected to an engine; the gas circuit pressurization system consists of a main gas cylinder and a downstream pipeline thereof, and a pressure supplementing gas cylinder and a downstream pipeline thereof; the liquid path supply system consists of an oxidant storage tank and a downstream pipeline thereof, and a fuel storage tank and a downstream pipeline thereof.
2. The system according to claim 1, wherein said gas circuit pressurization system comprises a main gas cylinder of larger volume and a supplementary gas cylinder of smaller volume; the main gas bottle is used for storing high-pressure gas required by the pressurization of the whole propulsion system and is used as a primary pressurization gas source for the pressurization of the storage tank; the pressure supplementing gas cylinder is used for assisting the measurement of the propellant surplus of the whole propulsion system, and is communicated with a primary pressurized gas source through an L3 valve to serve as a secondary pressurized gas source for pressurizing the storage tank.
3. The pressure supplementing type space propelling system suitable for the high-capacity surface tension storage tank is characterized in that the volume of the main gas cylinder is required to meet the requirement of pressurizing gas in the whole propelling task, and the number of the main gas cylinder can be set to be a plurality according to the total assembly layout; the volume of the pressure-supplementing gas cylinder requires that the liquid level of a propellant in the storage tank changes slightly in the process of directly pressurizing the storage tank, so that the pressure of the pressure-supplementing gas cylinder can change obviously; therefore, the pressure change value of the pressure compensation gas cylinder can be measured according to the high-precision pressure sensor, and the residual quantity of the storage tank propellant can be measured by a PVT method.
4. The pressure compensating space propulsion system for the large-capacity surface tension storage tank as claimed in claim 1, wherein the gas path pressurization system is provided with a pressure sensor P2, a pressure sensor P3 and a pressure sensor P4 with high measurement accuracy.
5. The pressure compensating space propulsion system for high capacity surface tension tanks of claim 1 wherein the gas circuit pressurization system includes a check valve C1 upstream of the oxidant tank inlet and a check valve C2 upstream of the fuel tank inlet, the check valve C1 and check valve C2 allowing the forward flow of line fluid and blocking the reverse flow of line fluid.
6. The pressure compensating space propulsion system for high capacity surface tension tanks as claimed in claim 1, wherein the gas circuit pressurization system is provided with a gas circuit charging and discharging valve D3 and a gas circuit charging and discharging valve D4 respectively at the upstream of the oxidant tank and the fuel tank, and the gas charging and discharging valve D3 and the gas circuit charging and discharging valve D4 are used for discharging gas in the tank gas cavity during propellant charging so as to facilitate propellant charging; and on the other hand, the device is used for pre-pressurizing the air cavity of the storage tank after the propellant is filled.
7. The pressure compensating space propulsion system for high capacity surface tension tanks as claimed in claim 1, wherein in the liquid path supply system, a pneumatic cut-off valve K1 is provided at the outlet of the oxidant tank, a pneumatic cut-off valve K2 is provided at the outlet of the fuel tank, and the auxiliary tank is used for evacuating the charging line downstream from K1 to D5 and from K2 to D6; the pneumatic stop valves K1 and K2 are normally open under normal working conditions, and the pneumatic stop valves K1 and K2 are closed only when driving pressure is provided for K1 and K2 through a ground gas distribution platform; before filling, after K1 and K2 are driven to be closed by a ground gas distribution table, the filling and discharging valves D5 and D6 can realize the vacuum pumping of the filling pipeline at the downstream of the storage tank.
8. The system of claim 1, wherein an electro-explosive valve B1 and an electro-explosive valve B2 are provided in the fluid path supply system downstream of the oxidizer tank and the fuel tank, respectively; the electric explosion valve B1 and the electric explosion valve B2 are normally closed electric explosion valves, namely normally in a closed state. The valve is used for blocking communication between a filling pipeline at the downstream of the storage tank and a pipeline from the downstream of the electric explosion valve to the engine.
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| CN201910796331.3A CN110566369A (en) | 2019-08-27 | 2019-08-27 | Pressure supplementing type space propulsion system suitable for high-capacity surface tension storage tank |
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| CN201910796331.3A CN110566369A (en) | 2019-08-27 | 2019-08-27 | Pressure supplementing type space propulsion system suitable for high-capacity surface tension storage tank |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110979747A (en) * | 2019-12-20 | 2020-04-10 | 北京中科宇航探索技术有限公司 | Attitude and orbit coupling control method and system |
| CN111152944A (en) * | 2019-12-31 | 2020-05-15 | 上海空间推进研究所 | Surface tension storage tank bubble breaking point testing method and system |
| CN111928104A (en) * | 2020-10-09 | 2020-11-13 | 北京星际荣耀空间科技有限公司 | Liquid oxymethane rocket supercharging device and liquid oxymethane rocket |
| CN112983678A (en) * | 2021-05-07 | 2021-06-18 | 星河动力(北京)空间科技有限公司 | Propellant delivery device and propellant filling method |
| CN114087090A (en) * | 2021-11-10 | 2022-02-25 | 中国运载火箭技术研究院 | System and method for pressurizing small air pillow of storage tank of reusable low-temperature power system |
| CN114251193A (en) * | 2021-12-10 | 2022-03-29 | 北京航天动力研究所 | Integrated propellant tank pressurization system and method for double-component liquid rocket engine |
| CN114291297A (en) * | 2021-12-20 | 2022-04-08 | 上海空间推进研究所 | Lunar surface launch vehicle propulsion system |
| CN114291300A (en) * | 2021-12-21 | 2022-04-08 | 上海空间推进研究所 | Earth-moon shuttle aircraft propulsion system |
| WO2022077079A1 (en) * | 2020-10-16 | 2022-04-21 | Comando De Operações Aeroespaciais - Comae | Method for controlling mixing ratio by thermal action in the propellant tanks of space systems |
| CN115258200A (en) * | 2022-07-01 | 2022-11-01 | 宁波天擎航天科技有限公司 | Dual-mode variable-thrust propulsion system and propulsion method |
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Cited By (13)
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| CN110979747B (en) * | 2019-12-20 | 2021-06-22 | 北京中科宇航探索技术有限公司 | Attitude and orbit coupling control method and system |
| CN110979747A (en) * | 2019-12-20 | 2020-04-10 | 北京中科宇航探索技术有限公司 | Attitude and orbit coupling control method and system |
| CN111152944A (en) * | 2019-12-31 | 2020-05-15 | 上海空间推进研究所 | Surface tension storage tank bubble breaking point testing method and system |
| CN111928104A (en) * | 2020-10-09 | 2020-11-13 | 北京星际荣耀空间科技有限公司 | Liquid oxymethane rocket supercharging device and liquid oxymethane rocket |
| CN111928104B (en) * | 2020-10-09 | 2020-12-22 | 北京星际荣耀空间科技有限公司 | Liquid oxymethane rocket supercharging device and liquid oxymethane rocket |
| WO2022077079A1 (en) * | 2020-10-16 | 2022-04-21 | Comando De Operações Aeroespaciais - Comae | Method for controlling mixing ratio by thermal action in the propellant tanks of space systems |
| CN112983678A (en) * | 2021-05-07 | 2021-06-18 | 星河动力(北京)空间科技有限公司 | Propellant delivery device and propellant filling method |
| CN114087090A (en) * | 2021-11-10 | 2022-02-25 | 中国运载火箭技术研究院 | System and method for pressurizing small air pillow of storage tank of reusable low-temperature power system |
| CN114251193A (en) * | 2021-12-10 | 2022-03-29 | 北京航天动力研究所 | Integrated propellant tank pressurization system and method for double-component liquid rocket engine |
| CN114291297A (en) * | 2021-12-20 | 2022-04-08 | 上海空间推进研究所 | Lunar surface launch vehicle propulsion system |
| CN114291300A (en) * | 2021-12-21 | 2022-04-08 | 上海空间推进研究所 | Earth-moon shuttle aircraft propulsion system |
| CN114291300B (en) * | 2021-12-21 | 2024-03-29 | 上海空间推进研究所 | Ground-moon shuttle aircraft propulsion system |
| CN115258200A (en) * | 2022-07-01 | 2022-11-01 | 宁波天擎航天科技有限公司 | Dual-mode variable-thrust propulsion system and propulsion method |
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Application publication date: 20191213 |
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