CN110131073B - Space propulsion system suitable for filling of large-capacity storage tank - Google Patents
Space propulsion system suitable for filling of large-capacity storage tank Download PDFInfo
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- CN110131073B CN110131073B CN201910371033.XA CN201910371033A CN110131073B CN 110131073 B CN110131073 B CN 110131073B CN 201910371033 A CN201910371033 A CN 201910371033A CN 110131073 B CN110131073 B CN 110131073B
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- filling
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- storage tank
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- pipeline
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- 239000007800 oxidant agent Substances 0.000 claims abstract description 40
- 230000001590 oxidative effect Effects 0.000 claims abstract description 35
- 239000000446 fuel Substances 0.000 claims abstract description 33
- 239000007788 liquid Substances 0.000 claims abstract description 29
- 239000003380 propellant Substances 0.000 claims abstract description 26
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 17
- 238000004880 explosion Methods 0.000 claims abstract description 16
- 238000007599 discharging Methods 0.000 claims description 13
- 238000004891 communication Methods 0.000 claims description 9
- 239000002828 fuel tank Substances 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 238000012544 monitoring process Methods 0.000 claims description 4
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 239000002360 explosive Substances 0.000 description 3
- 238000005429 filling process Methods 0.000 description 3
- 238000007789 sealing Methods 0.000 description 2
- 230000001154 acute effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 229920006395 saturated elastomer Polymers 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; 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
-
- 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
-
- 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)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The invention provides a space propulsion system suitable for filling a large-capacity storage tank. The filling gas path system consists of an oxidant filling gas path subsystem and a fuel filling gas path subsystem, the oxidant filling gas path subsystem and the fuel filling gas path subsystem are communicated with each other at the upstream and then connected with a pressurization gas path, and the downstream are independent and are respectively connected with the filling liquid path system; the filling liquid path system consists of an oxidant storage tank pipeline subsystem and a fuel storage tank pipeline subsystem, wherein the oxidant storage tank pipeline subsystem and the fuel storage tank pipeline subsystem are independent and physically isolated from each other and are respectively connected with a filling gas path system. The invention can improve the safety of the space propulsion system and effectively prevent the explosion caused by chemical reaction of the reverse flow of the oxidant and the fuel; the propellant filling efficiency is improved, the propellant filling time is reduced, and the propellant filling in place of the conventional surface tension storage tank is ensured.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a space propulsion system suitable for filling a high-capacity storage tank.
Background
In the aerospace field, propellant tanks, namely oxidizer tanks and fuel tanks, are currently important components of space propulsion systems, wherein surface tension tanks are widely used with their excellent reliability. However, at the same time, space propulsion systems using surface tension tanks also suffer from the following problems:
firstly, due to the residual gas existing in the filling pipeline, the propellant gas is entrapped in the filling process, the hidden danger of incomplete filling is generated, and the filling process has low efficiency and long time consumption;
secondly, because the air cavity and the liquid cavity of the surface tension storage tank are the same, the internal oxidant or fuel vapor has the risk of explosion due to upstream contact, and in addition, the liquid surface of the surface tension storage tank is easy to shake, so that the service performance of the storage tank is influenced.
The above problem is particularly acute for space propulsion systems with large capacity surface tension tanks. Therefore, the design of the space propulsion system with high safety, quick filling in place and high reliability has high importance and application value.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide a space propulsion system suitable for filling a large-capacity storage tank, which solves the problems of insufficient filling, low efficiency and long time consumption in the filling process and effectively prevents the risks of easy liquid level shaking and explosion of the surface tension storage tank.
In order to solve the problems, the space propulsion system suitable for filling the large-capacity storage tank comprises a filling gas path system and a filling liquid path system; the filling gas path system comprises an oxidant filling gas path subsystem and a fuel filling gas path subsystem; the oxidant filling gas circuit subsystem and the fuel filling gas circuit subsystem are communicated with each other at the upstream and then connected with a pressurization gas circuit, and the downstream are independent and respectively connected with the filling liquid circuit system; the filling liquid path system comprises an oxidant storage tank pipeline subsystem and a fuel storage tank pipeline subsystem, wherein the oxidant storage tank pipeline subsystem and the fuel storage tank pipeline subsystem are independent and physically isolated from each other, the upstream is respectively connected with a filling gas path system, and the downstream is respectively connected with an engine liquid path; wherein, the upstream is a material inflow side, and the downstream is a material outflow side.
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, reduces the propellant filling time, improves the propellant filling efficiency, reduces the liquid level shaking degree of the storage tank, 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 block diagram of a space propulsion system suitable for high volume tank filling in accordance with an embodiment of the present invention.
Detailed Description
A space propulsion system suitable for filling a large-capacity tank according to an embodiment of the present invention will be described in detail with reference to the accompanying drawings.
As shown in fig. 1, a space propulsion system suitable for filling a large-capacity storage tank according to an embodiment of the present invention includes a filling gas path system and a filling liquid path system; the filling gas path system comprises an oxidant filling gas path subsystem and a fuel filling gas path subsystem; the oxidant filling gas circuit subsystem and the fuel filling gas circuit subsystem are communicated with each other at the upstream and then connected with a pressurization gas circuit, and the downstream are independent and respectively connected with the filling liquid circuit system; the filling liquid path system comprises an oxidant storage tank pipeline subsystem and a fuel storage tank pipeline subsystem, wherein the oxidant storage tank pipeline subsystem and the fuel storage tank pipeline subsystem are independent and physically isolated from each other, the upstream is respectively connected with a filling gas path system, and the downstream is respectively connected with an engine liquid path; wherein, the upstream is a material inflow side, and the downstream is a material outflow side.
Further, the oxidant filling gas circuit subsystem comprises: a check valve C1, a filling valve L1, a pressure sensor P1 and a communication pipeline; the refueling gas circuit subsystem comprises: a check valve C2, a filling valve L2, a pressure sensor P2 and a communication pipeline; the oxidant tank piping subsystem includes: the system comprises an oxidant storage tank, a pneumatic stop valve K1, a filling valve L3, a pressure sensor P3, an electric explosion valve B1 and a communication pipeline; the fuel tank piping subsystem comprises: the fuel tank, the pneumatic stop valve K2, the filling valve L4, the pressure sensor P4, the electric explosion valve B2 and the communicating pipeline;
in the filling gas path system, a check valve C1 is arranged in an upstream pipeline of the oxidant filling gas path subsystem, and a check valve C2 is arranged in an upstream pipeline of the fuel filling gas path subsystem; the check valve allows the pipeline working medium to flow in the forward direction and blocks the pipeline working medium from flowing in the reverse direction; 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 oxidant and the saturated steam of the fuel in the storage tank from meeting in a gas path pipeline communicated at the upstream of the stop valve and generating explosion due to chemical reaction. Therefore, the safety of the system can be effectively improved by adding the C1 and C2 one-way valves; and the positive flowing direction of the working medium is the flowing direction of the one-way valve to the storage tank.
In the filling gas path system, a charging and discharging valve L1 is arranged in a downstream pipeline of the oxidant filling gas path subsystem, and a charging and discharging valve L2 is arranged in a downstream pipeline of the fuel filling gas path subsystem; the charging and discharging valve can be used for charging and discharging gas or propellant; reason 1 for setting the charge and discharge valves L1 and L2 is: when the storage tank is filled with the propellant, the volume of a liquid cavity in the storage tank is gradually increased, and the volume of an air cavity of the storage tank is gradually reduced, so that the gas pressure in the air cavity of the storage tank is gradually increased, the storage tank is difficult to fill due to the overhigh gas pressure of the storage tank, and even the storage tank cannot be filled in the last filling stage, therefore, the filling and discharging valves L1 and L2 arranged in a filling gas circuit can be used for relieving pressure when the pressure of the air cavity of the storage tank is overhigh, the storage tank can be smoothly filled with the propellant, the filling efficiency is improved, and the propellant is ensured to be filled in place; reason 2 for setting the charge and discharge valves L1 and L2 is: after the propellant is filled in the storage tank, the residual air cavities in the storage tank can be pre-pressurized through the charging and discharging valves L1 and L2, the pressure of the air cavities of the storage tank is improved, and the reason for pressurizing the pressure of the air cavities of the storage tank is as follows: on one hand, the rigidity of a structural system can be effectively improved; on the other hand, the shaking degree of the liquid level of the propellant in the liquid cavity of the storage tank can be reduced, and the use performance of the surface tension storage tank can be reduced due to the larger shaking degree of the liquid level; wherein the propellant is an oxidizer or fuel filled in the storage tank.
In the filling gas path system, a pressure sensor P1 is arranged in a downstream pipeline of the oxidant filling gas path subsystem, and a pressure sensor P2 is arranged in a downstream pipeline of the fuel filling gas path subsystem; the pressure sensor is used for monitoring the pressure of the air cavity of the storage tank, and the pressure parameter displayed by the pressure sensor can be used as a criterion for pressure relief of the air cavity of the storage tank on one hand and can also be used as an indication parameter of pre-pressurization pressure of the air cavity of the storage tank after filling is finished on the other hand. The communication position of the pressure sensor is as close to the inlet of the air chamber of the storage tank as possible, because the closer the pressure sensor is to the air chamber of the storage tank, the closer the available pressure parameter is to the pressure value of the actual air chamber of the storage tank.
In the filling liquid path 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; the pneumatic stop valves 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 table; the reason for pneumatically controlling the shut-off valve switch is two-fold: 1) the sealing specific pressure of the shut-off valve after being closed can be changed by adjusting the driving pressure, while the sealing specific pressure of the traditional manual or electric valve can not be changed; 2) the use of pneumatically controlled valves allows smaller volumes and weights to be obtained, since the number of manual operating handles or electromagnetic devices is reduced compared to manual or electric valves, while also improving the reliability of the valve itself; the pneumatic stop valves are used for auxiliary tank downstream vacuumizing and pipeline propellant filling between K1 and B1 and K2 and B2 respectively before the tank is filled. The operation steps of the auxiliary vacuumizing of the stop valve and the pipeline propellant filling are as follows: 1) the driving gas is provided through the gas distribution table, and the pneumatic stop valve K1 (or K2) is controlled to be closed; 2) vacuumizing a pipeline between K1 and B1 (or a pipeline between K2 and B2) by using ground vacuumizing equipment through a filling valve L3 (or L4); 3) filling the oxidant (or fuel) into the pipeline between K1 and B1 (or the pipeline between K2 and B2) by a ground filling device through a filling valve L3 (or L4); 4) the opening of K1 (or K2) is controlled by the gas station, and the oxidizer (or fuel) is continuously filled into the oxidizer tank (fuel tank) through L3 (or L4) by the surface filling equipment until the required filling amount is reached. Wherein, the content in brackets in the above steps corresponds to the fuel storage tank operation step; the reasons for the auxiliary vacuum pumping and the pipeline propellant filling by adopting the pneumatic stop valve are as follows: when a large-capacity surface tension storage tank is filled, if the downstream filling pipelines (the filling pipelines refer to pipelines between K1 and B1 and between K2 and B2) are not vacuumized, gas entrapment can be generated in the propellant in the filling pipelines (namely the propellant can be mixed with the air in the original filling pipelines), and the propellant with the gas entrapment is difficult to fill into the surface tension storage tank, so that the risk of insufficient filling of the propellant is generated. Therefore, before filling, the filling pipeline at the downstream of the storage tank needs to be vacuumized and prefilled, so as to prevent gas in the filling pipeline from influencing the filling of the propellant. The pneumatic stop valve is mounted in such a way that it is directly connected to the outlet of the tank, without the need for a conduit or other connection between the tank and the stop valve. The reason is that: after the pneumatic stop valves K1 and K2 are closed, the storage tank can be completely isolated from the vacuumizing pipeline at the downstream of the storage tank, so that the pipeline vacuumizing operation before the storage tank is filled can cover all the vacuumizing pipelines at the downstream of the storage tank.
In the filling liquid path system, a filling valve L3 and a pressure sensor P3 are respectively arranged between K1 and B1, and a filling valve L4 and a pressure sensor P4 are respectively arranged between K2 and B2; the filling valves L3 and L4 are used for vacuumizing the pipeline and propelling filling and discharging, and the pressure sensors P3 and P4 are used for monitoring the pressure of the liquid cavity of the storage tank. An electro-explosive valve B1 and an electro-explosive valve B2 are respectively arranged at the downstream of the oxidant storage tank and the fuel storage tank. The electro-explosive valves B1 and B2 should be provided at the ends of the filling line. The electric explosion valves B1 and B2 are normally closed electric explosion valves, namely, are in a closed state under a normal state. The electric explosion valves B1 and B2 are used for blocking communication between a storage tank downstream filling pipeline and an engine liquid pipeline downstream of the electric explosion valves, so that on one hand, the pipeline to the engine can be prevented from being vacuumized when the storage tank downstream filling pipeline is vacuumized, on the other hand, propellant can be prevented from entering the engine too early, and the safety of the system is improved.
Claims (4)
1. A space propulsion system adapted for high volume tank filling, comprising: a gas filling pipeline system and a liquid filling pipeline system are added;
the filling gas path system comprises an oxidant filling gas path subsystem and a fuel filling gas path subsystem; the oxidant filling gas circuit subsystem and the fuel filling gas circuit subsystem are communicated with each other at the upstream and then connected with a pressurization gas circuit, and the downstream are independent and respectively connected with the filling liquid circuit system;
the filling liquid path system comprises an oxidant storage tank pipeline subsystem and a fuel storage tank pipeline subsystem, wherein the oxidant storage tank pipeline subsystem and the fuel storage tank pipeline subsystem are independent and physically isolated from each other, the upstream is respectively connected with a filling gas path system, and the downstream is respectively connected with an engine liquid path;
wherein, the upstream is a material inflow side, and the downstream is a material outflow side; the oxidant filling gas circuit subsystem comprises: a check valve C1, a charging and discharging valve L1, a pressure sensor P1 and a communication pipeline; the refueling gas circuit subsystem comprises: a check valve C2, a charging and discharging valve L2, a pressure sensor P2 and a communication pipeline;
the upstream pipeline of the oxidant filling gas circuit subsystem is provided with a one-way valve C1, and the upstream pipeline of the fuel filling gas circuit subsystem is provided with a one-way valve C2; the check valve C1 and the check valve C2 allow the forward circulation of the pipeline working medium and block the reverse circulation of the pipeline working medium; wherein the positive flow direction of the working medium is the flow direction from the one-way valve to the storage tank;
a charge and discharge valve L1 is arranged in the downstream pipeline of the oxidant charging gas circuit subsystem, and a charge and discharge valve L2 is arranged in the downstream pipeline of the fuel charging gas circuit subsystem; the charging and discharging valve L1 and the charging and discharging valve L2 are used for charging and discharging gas; wherein the propellant is an oxidizer or fuel that is filled into the tank;
a pressure sensor P1 is arranged in a downstream pipeline of the oxidant filling gas path subsystem, and a pressure sensor P2 is arranged in a downstream pipeline of the fuel filling gas path subsystem; the pressure sensor P1 and the pressure sensor P2 are used for monitoring the pressure of the air cavity of the storage tank, and the displayed pressure parameters are used as a criterion for the pressure relief of the air cavity of the storage tank on one hand and are used as indication parameters of the pre-pressurization pressure of the air cavity of the storage tank after the filling is finished on the other hand;
the oxidant tank piping subsystem includes: the system comprises an oxidant storage tank, a pneumatic stop valve K1, a filling valve L3, a pressure sensor P3, an electric explosion valve B1 and a communication pipeline; the fuel tank piping subsystem comprises: the fuel tank, the pneumatic stop valve K2, the filling valve L4, the pressure sensor P4, the electric explosion valve B2 and the communicating pipeline;
the outlet of the oxidant storage tank is provided with a pneumatic stop valve K1, and the outlet of the fuel storage tank is provided with a pneumatic stop valve K2; the pneumatic stop valve K1 and the pneumatic stop valve K2 are in a normally open state under a normal working condition, and the pneumatic stop valve K1 and the pneumatic stop valve K2 are in a closed state only when driving pressure is provided for the pneumatic stop valve K1 and the pneumatic stop valve K2 through a ground gas distribution table; and the pneumatic stop valve K1 and the pneumatic stop valve K2 are used for assisting the vacuumizing and the propellant filling of a filling pipeline between the pneumatic stop valve K1 and the electric explosion valve B1 at the downstream of the storage tank and between the pneumatic stop valve K2 and the electric explosion valve B2 respectively before the storage tank is filled.
2. The space propulsion system for high-capacity tank filling according to claim 1, wherein the pressure sensor is in communication with the inlet of the tank air chamber, so that the pressure parameter can be obtained more closely to the actual pressure value of the tank air chamber.
3. A space propulsion system for the filling of large volumes of tanks according to claim 1, characterised in that the pneumatic stop valve is mounted in direct connection with the tank outlet.
4. A space propulsion system suitable for high-capacity tank filling according to claim 1, characterized in that in the filling liquid path system, a filling valve L3 and a pressure sensor P3 are respectively provided between a pneumatic cut-off valve K1 and an electric explosion valve B1, and a filling valve L4 and a pressure sensor P4 are respectively provided between a pneumatic cut-off valve K2 and an electric explosion valve B2; the filling valve L3 and the filling valve L4 are used for pushing filling and discharging, and the pressure sensor P3 and the pressure sensor P4 are used for monitoring the pressure of the liquid cavity of the storage tank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910371033.XA CN110131073B (en) | 2019-05-06 | 2019-05-06 | Space propulsion system suitable for filling of large-capacity storage tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910371033.XA CN110131073B (en) | 2019-05-06 | 2019-05-06 | Space propulsion system suitable for filling of large-capacity storage tank |
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| Publication Number | Publication Date |
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| CN110131073A CN110131073A (en) | 2019-08-16 |
| CN110131073B true CN110131073B (en) | 2022-02-18 |
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| CN201910371033.XA Expired - Fee Related CN110131073B (en) | 2019-05-06 | 2019-05-06 | Space propulsion system suitable for filling of large-capacity storage tank |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110566369A (en) * | 2019-08-27 | 2019-12-13 | 上海空间推进研究所 | Pressure supplementing type space propulsion system suitable for high-capacity surface tension storage tank |
| CN111071490B (en) * | 2019-12-11 | 2021-08-06 | 上海空间推进研究所 | Method for improving shock resistance of orbit control engine of propulsion system of planet lander |
| CN117345469B (en) * | 2023-12-04 | 2024-02-09 | 北京航天试验技术研究所 | Liquid oxygen evacuating and supercooling device, liquid oxygen supercooling system and use method |
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| FR2697587A1 (en) * | 1992-11-04 | 1994-05-06 | Europ Propulsion | Optimized rocket motor power supply system. |
| 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 |
| CN104648696A (en) * | 2014-12-11 | 2015-05-27 | 上海空间推进研究所 | Metal propellant storage tank for spaceflight and manufacturing method thereof |
| CN106762224A (en) * | 2016-11-21 | 2017-05-31 | 北京控制工程研究所 | A kind of Large Copacity half manages formula surface tension propellant tank balance charging method in parallel |
| CN108730071A (en) * | 2018-04-11 | 2018-11-02 | 上海空间推进研究所 | The multidirectional propulsion system added |
| CN109281774A (en) * | 2018-12-03 | 2019-01-29 | 上海空间推进研究所 | Electronic pump pressure type liquid oxygen methane space propulsion system |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105971768B (en) * | 2016-06-10 | 2017-09-15 | 中国人民解放军国防科学技术大学 | A kind of supercharging supply system certainly based on re-generatively cooled |
| US10605204B2 (en) * | 2017-03-09 | 2020-03-31 | The Government Of The United States Of America, As Represented By The Secretary Of The Navy | Methane/oxygen rocket engine with specific impulse enhancement by hot helium infusion |
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2019
- 2019-05-06 CN CN201910371033.XA patent/CN110131073B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2697587A1 (en) * | 1992-11-04 | 1994-05-06 | Europ Propulsion | Optimized rocket motor power supply system. |
| 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 |
| CN104648696A (en) * | 2014-12-11 | 2015-05-27 | 上海空间推进研究所 | Metal propellant storage tank for spaceflight and manufacturing method thereof |
| CN106762224A (en) * | 2016-11-21 | 2017-05-31 | 北京控制工程研究所 | A kind of Large Copacity half manages formula surface tension propellant tank balance charging method in parallel |
| CN108730071A (en) * | 2018-04-11 | 2018-11-02 | 上海空间推进研究所 | The multidirectional propulsion system added |
| CN109281774A (en) * | 2018-12-03 | 2019-01-29 | 上海空间推进研究所 | Electronic pump pressure type liquid oxygen methane space propulsion system |
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