CN110332060B - Liquid oxymethane rocket and liquid oxymethane rocket storage tank pressure-drop type pressurization design method - Google Patents
Liquid oxymethane rocket and liquid oxymethane rocket storage tank pressure-drop type pressurization design method Download PDFInfo
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- CN110332060B CN110332060B CN201910222723.9A CN201910222723A CN110332060B CN 110332060 B CN110332060 B CN 110332060B CN 201910222723 A CN201910222723 A CN 201910222723A CN 110332060 B CN110332060 B CN 110332060B
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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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- 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
- F02K9/605—Reservoirs
Abstract
The invention provides a liquid oxymethane rocket and a liquid oxymethane rocket storage tank pressure-drop type pressurization design method, which comprises the following steps: in a first time period when the engine main machine works, the storage tank is pressurized by utilizing a self-generated pressurization mode; and after the engine main machine stops working, at least one of the evaporation of the low-temperature propellant and the expansion of the gas in the storage tank is used for pressurizing the storage tank at least in part of the second time period of the working of the engine main machine. According to the liquid oxymethane rocket storage tank pressure drop type pressurization design method, the difference of the pressurization pressure needed by the engine main engine and the inlet of the engine traveling machine is fully utilized, a self-generated pressurization system of the traveling machine is omitted, the rocket structural design is simplified, and the carrying capacity of the rocket is improved.
Description
Technical Field
The invention belongs to the field of tank pressurization conveying, relates to a novel rocket propellant liquid oxygen methane self-generation pressurization system, and particularly relates to a flight state self-generation pressurization scheme under the combination of an engine host and a swimming unit.
Background
The pressurizing system is used for providing air pillow pressure of the liquid rocket propellant storage tank, and pressurized gas enters the propellant storage tank, occupies the space after the propellant is discharged after being expanded and generates working pressure on the liquid propellant. Thereby meeting the normal working pressure of the propellant inlet required in the starting and flying processes of the engine; the internal pressure requirement required by the load bearing of the rocket propellant storage tank thin-wall structure is met, and the storage tank structure is ensured to have enough strength and rigidity.
The pressurization modes generally comprise gas pressurization, gas cylinder pressurization and autogenous pressurization.
Gas supercharging is a supercharging mode that uses engine combustion products as a supercharging medium. Usually, a branch is led out from the outlet of a gas generator of an engine, and is cooled by a cooler arranged on a flow passage of a propellant, so that the gas is cooled to a proper temperature and then is led into a storage tank for pressurization. The gas increase has the advantages of simple system and lower cost. However, the gas components are different from the propellant components in the storage tank, the use of the gas is limited, only the propellant storage tank with good compatibility can be pressurized, and the adaptability is poor.
Cylinder pressurization is performed using pressurized gas stored in a high pressure cylinder. Because helium has small density and strong supercharging capacity, the helium is used in a supercharging medium more frequently. The gas cylinder pressurization is a pressurization system which is independently configured, and has the advantages of wide applicability and flexible system design. However, the pressurization of the gas cylinder requires the provision of a separate pressurized gas source storage device, and the system is relatively complex and costly.
The autogenous pressurization mode is to utilize the propellant component of the rocket to pressurize the storage tank after the engine is evaporated and gasified. Usually, a branch is led out from the high-pressure area behind the engine pump, the propellant is gasified through an evaporator, the temperature is adjusted to a required value, and then the propellant is led into a storage tank for pressurization. The autogenous pressurization is similar to the gas cooling pressurization mode, and the system has the advantages of simplicity and lower cost. However, since the self-generated pressurization adopts a propellant as a pressurization medium, the rocket loses certain carrying capacity, and the adaptability has certain limitation. For practical applications, autogenous pressurization is generally preferred for less dense propellants (e.g., liquid hydrogen).
Therefore, how to provide a pressurizing manner that simplifies a pressurizing system, can improve the carrying capacity of the rocket, and achieves the maximum benefit is a technical problem to be solved urgently by those skilled in the art.
Disclosure of Invention
In order to solve at least part of the technical problems, the invention provides a hydraulic type pressurization design method for a liquid oxygen methane rocket storage tank, which is characterized in that the storage tank is pressurized by utilizing a self-generated pressurization mode in a first working period of an engine host; and after the engine host stops working, at least one of the evaporation of the low-temperature propellant and the expansion of the gas in the storage tank is used for pressurizing the storage tank at least in part of the second time period of the working of the engine host.
In the above aspect, in the drop-pressure pressurization design method for a liquid oxymethane rocket tank, after the engine main unit stops operating, at least part of the time in a second period of time during which the engine main unit operates, the pressurizing the tank by using at least one of evaporation of a low-temperature propellant and expansion of gas in the tank includes: determining the closing time of the self-generation pressurization mode according to the pressurization requirement in the storage tank, and pressurizing the storage tank by utilizing at least one of the evaporation of the low-temperature propellant and the expansion of gas in the storage tank after the self-generation pressurization mode is closed.
In the above scheme, in the drop-pressure pressurization design method for the liquid oxymethane rocket tank, the closing time of the autogenous pressurization mode is determined according to the pressurization requirement in the tank, and after the autogenous pressurization mode is closed, the tank is pressurized by using the evaporation of the low-temperature propellant and the gas expansion in the tank comprises: when the engine main unit stops operating, the self-generated supercharging mode is stopped, and the tank is supercharged by at least one of evaporation of the low-temperature propellant and expansion of gas in the tank.
In some embodiments, in the design method of the drop-pressure pressurization of the liquid oxymethane rocket tank, the first time period is 0s to 150 s; the second time interval is 150-550 s.
In some embodiments, in the design method of the drop-pressure pressurization of the liquid oxymethane rocket tank, the second time period is 150s to 400 s.
In some embodiments, the design method of the drop-pressure type pressurization of the liquid oxymethane rocket tank further comprises the step of pressurizing the tank by utilizing a self-generated pressurization mode in a third period of time when the engine runs; wherein the third time period is 400 s-550 s.
In some embodiments, in the design method for the pressure drop pressurization of the liquid oxymethane rocket tank, when the thrust of the engine is 100t, the required pressurization pressure of the oxygen tank of the tank is reduced from 0.37MPa to 0.14MPa in a first period of the operation of the engine; the pressurization pressure required by the combustion box of the storage box is reduced from 0.33MPa to 0.09 MPa;
when the thrust of the engine is 25t, in the second working period of the engine, the pressurization pressure required by the oxygen tank of the storage tank is reduced to 0.10MPa from 0.14MPa, and the pressurization pressure required by the fuel tank of the storage tank is reduced to 0.05MPa from 0.09 MPa.
In some embodiments, in the design method for the drop-pressure pressurization of the liquid oxymethane rocket tank, when the thrust of the engine is 100t, the tank is pressurized by a self-generated pressurization mode in a first period of time when the engine host works, the actual pressurization of the oxygen tank is reduced from 0.39MPa to 0.36MPa, and the actual pressurization of the fuel tank is reduced from 0.35MPa to 0.32 MPa.
The invention also provides a liquid oxymethane rocket which uses the liquid oxymethane rocket storage tank pressure-drop type pressurization design method.
In certain embodiments, the liquid oxygen methane rocket comprises: an oxygen self-generating pressure-increasing pipe for communicating the combustion box with the engine host; the combustion self-generating pressure increasing pipe is communicated with the oxygen box and the engine main machine; an engine bracket and an engine combustion engine.
The drop-pressure type pressurization design method for the liquid oxymethane rocket storage tank provided by the embodiment of the invention has at least one of the following beneficial effects:
the design method combines a pressurization scheme with the actual working process of the rocket, utilizes the advantages of different pressurization schemes according to the difference of the inlet pressure requirements of the engine main machine and the engine swimming machine and the difference of the working time of the engine main machine and the engine swimming machine, realizes the heat exchange effect between the residual low-temperature liquid in the storage tank and the high-temperature self-generated pressurization gas, realizes the pressurization of the propellant, maximizes the advantages of the method, reduces the additional consumption of the propellant and increases the carrying capacity of the rocket.
According to the liquid oxymethane rocket storage tank pressure drop type pressurization design method, the difference of the pressurization pressure needed by the engine main engine and the inlet of the engine traveling machine is fully utilized, a self-generated pressurization system of the traveling machine is omitted, the rocket structural design is simplified, and the carrying capacity of the rocket is improved.
Drawings
FIG. 1 is a first flow diagram of a design method for the pressure drop pressurization of a liquid oxymethane rocket tank according to one embodiment of the present invention;
FIG. 2 is a diagram illustrating a required boost pressure and an actual boost pressure of an oxygen tank in a drop-pressure boost design method of a liquid oxymethane rocket tank according to an embodiment of the present invention;
FIG. 3 illustrates a tank required boost pressure and an actual boost pressure in a drop-pressure boost design method for a liquid oxymethane rocket tank according to an embodiment of the present invention;
FIG. 4 is a second flow chart of a design method for the pressure drop pressurization of a liquid oxymethane rocket tank according to one embodiment of the present invention;
FIG. 5 is a third flow chart of a design method for the pressure drop pressurization of a liquid oxymethane rocket tank according to an embodiment of the present invention;
FIG. 6 is a schematic diagram of a partial structure of a liquid methanone rocket according to an embodiment of the present invention using a tank pressure drop design method.
Description of the drawings:
1 represents a fuel tank, 2 represents an oxygen tank, 3 represents an engine support, 4 represents an engine, 5 represents an engine main machine, 6 represents an oxygen autogenous pressure boost pipe, and 7 represents an autogenous pressure boost pipe.
Detailed Description
Reference will now be made in detail to various exemplary embodiments of the invention, the detailed description should not be construed as limiting the invention but as a more detailed description of certain aspects, features and embodiments of the invention.
It is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. Further, for numerical ranges in this disclosure, it is understood that the upper and lower limits of the range, and each intervening value therebetween, is specifically disclosed. Every smaller range between any stated value or intervening value in a stated range and any other stated or intervening value in a stated range is encompassed within the invention. The upper and lower limits of these smaller ranges may independently be included or excluded in the range.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Although only preferred methods and materials are described herein, any methods and materials similar or equivalent to those described herein can be used in the practice or testing of the present invention. All documents mentioned in this specification are incorporated by reference herein for the purpose of disclosing and describing the methods and/or materials associated with the documents. In case of conflict with any incorporated document, the present specification will control.
It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the present disclosure without departing from the scope or spirit of the disclosure. The specification and examples are exemplary only.
As used herein, the terms "comprising," "including," "having," "containing," and the like are open-ended terms that mean including, but not limited to.
As used herein, "and/or" includes any and all combinations of the stated items.
The present invention will be further described with reference to the following detailed description and accompanying drawings.
As shown in fig. 1 to 3, in one embodiment of the present invention, the method for designing a pressure drop type pressurization of a liquid oxymethane rocket tank comprises:
in a first time period when the engine main machine works, the storage tank is pressurized by utilizing a self-generated pressurization mode; and after the engine main machine stops working, at least one of the evaporation of the low-temperature propellant and the expansion of the gas in the storage tank is used for pressurizing the storage tank at least in part of the second time period of the working of the engine main machine.
The invention provides a pressure drop type pressurization scheme for a liquid oxymethane rocket tank, which aims to overcome the defects and shortcomings of the prior art. The scheme combines a pressurization scheme with an actual rocket working process, considers the difference of the pressure requirements of the inlet of the engine main engine and the difference of the working time, and the heat exchange effect between the residual low-temperature liquid and the high-temperature self-generated pressurization gas in the storage tank, pressurizes the storage tank by utilizing a self-generated pressurization mode in a first time period when the engine main engine works, and pressurizes the storage tank by utilizing the evaporation of a low-temperature propellant or the expansion of the gas in the storage tank in a second time period when the engine main engine works. The invention makes full use of the difference of the needed pressurization pressure of the engine host and the inlet of the traveling machine, cancels the self-generation pressurization system of the traveling machine, simplifies the structural design of the rocket, respectively utilizes the advantages of different pressurization schemes, realizes the pressurization of the propellant, maximizes the overall advantages of the schemes, simultaneously reduces the additional consumption of the propellant and increases the carrying capacity of the rocket. The working time of the engine host and the engine trip machine is determined according to the real design, and the end time of the autogenous pressurization is determined according to the real working time.
In some embodiments, pressurizing the tank with at least one of evaporation of the cryogenic propellant and expansion of gas in the tank for at least a portion of the second period of engine operation after the engine host ceases operation comprises: determining the closing time of the self-generation pressurization mode according to the pressurization requirement in the storage tank, and pressurizing the storage tank by utilizing at least one of the evaporation of the low-temperature propellant and the expansion of gas in the storage tank after the self-generation pressurization mode is closed.
The time for closing the autogenous pressurization is calculated according to the actual required pressurization pressure, and the autogenous pressurization can be carried out for a period of time firstly in the working time period of the swimming machine and then converted into the autogenous expansion pressurization. The adjustment of the pressurization scheme is determined according to the actual pressurization pressure, the consumption of the propellant is reduced, the carrying capacity is increased under the condition of unchanged cost, and the benefit maximization is realized. In some embodiments, determining the closing time of the autogenous pressurization mode based on the pressurization demand in the tank, and pressurizing the tank using the evaporation of the cryogenic propellant and the expansion of the gas in the tank after the autogenous pressurization mode is closed comprises: when the engine main unit stops operating, the self-generated supercharging mode is stopped, and the tank is supercharged by at least one of evaporation of the low-temperature propellant and expansion of gas in the tank. The inlet pressure of the engine pump and the required supercharging pressure can be calculated according to the real situation, and when the requirement of the required supercharging pressure can be met by means of self evaporation of the low-temperature propellant and expansion of gas in the storage box, the self-generated supercharging process can be finished.
The thrust of the engine main unit and the engine travel unit is selected according to actual conditions.
In the scheme, when the thrust of the engine is 100t, in the first working period of the engine, the required pressurization pressure of the oxygen tank of the storage tank is reduced from 0.37MPa to 0.14 MPa; the pressurization pressure required by the combustion box of the storage box is reduced from 0.33MPa to 0.09 MPa;
when the thrust of the engine is 25t, in the second working period of the engine, the pressurization pressure required by the oxygen tank of the storage tank is reduced to 0.10MPa from 0.14MPa, and the pressurization pressure required by the fuel tank of the storage tank is reduced to 0.05MPa from 0.09 MPa.
When the thrust of the engine is 100t, the storage tank is pressurized in a self-generated pressurization mode in a first working period of the engine host, the actual pressurization of the oxygen tank is reduced from 0.39MPa to 0.36MPa, and the actual pressurization of the fuel tank is reduced from 0.35MPa to 0.32 MPa. As shown in FIG. 2, it can be seen from the graph of the required boost pressure of the oxygen tank and the actual boost pressure that the required boost pressure of the oxygen tank is reduced from 0.37MPa to 0.14MPa when the thrust of the engine main engine is 100t in the first period of the operation of the engine main engine, and the actual boost pressure is reduced from 0.39MPa to 0.36MPa because the self-generated boost scheme is adopted to meet the condition of the pump inlet pressure of the engine main engine at the moment. Therefore, when the engine main machine is shut down, the boost pressure is greater than the boost pressure actually required, after the engine main machine is shut down, the engine trip machine is started, the thrust of the engine trip machine is 25t, the required boost pressure is reduced to 0.10MPa from 0.14MPa, and is far lower than the autogenous boost pressure in the previous period, so that the autogenous boost flow can be ended while the engine main machine is shut down, and the boost pressure of the storage tank can be realized only by utilizing the expansion of the gas in the storage tank, so that the required boost pressure of the engine trip machine can be met. The invention makes full use of the difference of the needed supercharging pressure at the inlet of the engine host and the swimming machine, cancels the autogenous supercharging system of the swimming machine, simplifies the structural design of the rocket, and improves the carrying capacity of the rocket.
As shown in fig. 3, as can be seen from the graph of the required boost pressure and the actual boost pressure of the fuel tank, from the fuel tank curve, during the working period of the engine host from 0 to 150s, the required boost pressure of the fuel tank is reduced from 0.33MPa to 0.09MPa due to the thrust of the engine host being 100t, and the actual boost pressure is reduced from 0.35MPa to 0.32MPa due to the self-generated boost scheme adopted to meet the condition of the pump inlet pressure of the engine host at the time. Therefore, when the engine main machine is shut down, the boost pressure is greater than the boost pressure actually required, after the engine main machine is shut down, the engine trip machine is started, the thrust of the engine trip machine is 25t, the required boost pressure is reduced to 0.05MPa from 0.09MPa, and is far lower than the autogenous boost pressure in the previous period, so that the autogenous boost flow can be ended while the engine main machine is shut down, and the boost pressure of the storage tank can be realized only by utilizing the expansion of the gas in the storage tank, so that the required boost pressure of the engine trip machine can be met. The invention makes full use of the difference of the needed supercharging pressure at the inlet of the engine host and the swimming machine, cancels the autogenous supercharging system of the swimming machine, simplifies the structural design of the rocket, and improves the carrying capacity of the rocket.
In certain embodiments, the first period of time is between 0s and 150 s. The second time interval is 150-550 s.
In some embodiments, the actual boost pressure of the reservoir is reduced from 0.39MPa to 0.36MPa when the engine host is operating.
In one embodiment of the invention, as shown in fig. 4, in the design method of the drop-pressure type pressurization of the liquid oxymethane rocket tank, the tank is pressurized by a self-generated pressurization mode in a first period of time when the engine main machine works; after the engine host stops working, in a second time interval of the engine host working, at least one of the evaporation of the low-temperature propellant and the expansion of the gas in the storage tank is used for pressurizing the storage tank; and in a third period of time when the engine is in operation, the storage tank is pressurized by utilizing a self-generated pressurization mode.
Wherein the first time interval is 0 s-150 s, the second time interval is 150 s-400 s, and the third time interval is 400 s-550 s.
In one embodiment of the invention, as shown in fig. 5, in the design method of the drop-pressure type pressurization of the liquid oxymethane rocket tank, the tank is pressurized by a self-generated pressurization mode in a first period of time when the engine main machine works; after the engine host stops working, continuously pressurizing the storage tank by utilizing a self-generated pressurizing mode in a second time period when the engine trip works; during a third period of operation of the engine, the tank is pressurized with at least one of evaporation of cryogenic propellant and expansion of gas in the tank.
Wherein the first time interval is 0 s-150 s, the second time interval is 150 s-400 s, and the third time interval is 400 s-550 s.
The working time of the engine host and the engine trip machine is determined according to the real design. In some embodiments, the end time of the self-generated boost mode may be determined according to an inlet pressure value of the engine pump, and when the engine starts to work, the inlet pressure of the engine pump is monitored in real time to obtain the inlet pressure value of the engine pump, and the end time of the self-generated boost mode is determined according to the inlet pressure value of the engine pump. For example, when the engine main unit is finished, an inlet pressure value of a pump of the engine main unit is obtained, a current required pressure value is determined as a first pressure value according to the inlet pressure value of the pump of the engine main unit, the storage tank is continuously pressurized in a self-generated pressurization mode, the engine trip unit starts to work, meanwhile, the inlet pressure value of the pump of the engine trip unit is obtained in real time, the current required pressure value is determined as a second pressure value according to the inlet pressure value of the pump of the engine trip unit, when the second pressure value is 1/8-1/9 of the first pressure value, the self-generated pressurization system is closed, and at least one of evaporation of low-temperature propellant and gas expansion in the storage tank is utilized to pressurize the.
As shown in fig. 6, the present invention also provides a liquid oxymethane rocket using a tank pressure drop type pressurization design method, including: the device comprises a combustion box 1, an oxygen box 2, an engine support 3, an engine trip machine 4, an engine host machine 5, an oxygen self-generating pressure pipe 6 for communicating the combustion box 1 with the engine host machine 5, and a combustion self-generating pressure pipe 7 for communicating the oxygen box 2 with the engine host machine 5.
In the above scheme, the liquid oxymethane rocket further comprises a detector for detecting the pressure of the storage tank in real time; the database is prestored with expected pressure values of all working stages of the storage box; and the comparator is used for acquiring the pressure value detected by the detector in real time, comparing the pressure value with an expected pressure value in the database according to a working stage, and when the pressure value is smaller than the corresponding expected pressure value, executing the operation of closing the self-generating pressurization system, and simultaneously, carrying out pressurization on the storage tank by the evaporation of the low-temperature propellant or the expansion of gas in the storage tank. For example, in some embodiments, when the indicated pressure value is 1/9-1/3 corresponding to the expected pressure value, preferably when the indicated pressure value is 1/9-1/5 corresponding to the expected pressure value, more preferably when the indicated pressure value is 1/9-1/8 corresponding to the expected pressure value, for example, when the indicated pressure value is 1/9 or 1/8 corresponding to the expected pressure value, then the operation of closing the autogenous pressurization system is performed while the tank is pressurized by the evaporation of the cryogenic propellant or the expansion of the gas in the tank.
It will be apparent to those skilled in the art that various modifications and variations can be made in the specific embodiments of the present disclosure without departing from the scope or spirit of the disclosure. Other embodiments will be apparent to those skilled in the art from consideration of the specification. The specification and examples are exemplary only.
Claims (9)
1. A pressure drop type pressurization design method of a liquid oxygen methane rocket tank, wherein,
in a first time period when the engine main machine works, the storage tank is pressurized by utilizing a self-generated pressurization mode; and
after the engine host stops working, at least one of evaporation of the low-temperature propellant and expansion of gas in the storage tank is utilized to pressurize the storage tank in at least part of the second time period of the working of the engine host; it includes: determining the closing time of the self-generation pressurization mode according to the pressurization requirement in the storage tank, and pressurizing the storage tank by utilizing at least one of the evaporation of the low-temperature propellant and the expansion of gas in the storage tank after the self-generation pressurization mode is closed.
2. The pressure drop type pressurization design method for liquid oxymethane rocket tank according to claim 1,
determining the closing time of the self-generated pressurization mode according to the pressurization requirement in the storage tank, and pressurizing the storage tank by utilizing the evaporation of the low-temperature propellant and the expansion of gas in the storage tank after the self-generated pressurization mode is closed, wherein the step of pressurizing the storage tank comprises the following steps:
when the engine main unit stops operating, the self-generated supercharging mode is stopped, and the tank is supercharged by at least one of evaporation of the low-temperature propellant and expansion of gas in the tank.
3. The liquid oxymethane rocket tank pressure drop type pressurization design method according to claim 1, wherein the first time period is 0s to 150 s; the second time interval is 150-550 s.
4. The liquid oxymethane rocket tank pressure drop type pressurization design method according to claim 1, wherein the second period of time is 150s to 400 s.
5. The design method of the drop-pressure type pressurization of the liquid oxymethane rocket tank according to claim 4, wherein the method further comprises the step of pressurizing the tank by utilizing a self-generated pressurization mode in a third period of the operation of the engine;
wherein the third time period is 400-550 s.
6. The pressure drop type pressurization design method for liquid oxymethane rocket tank according to claim 1,
when the thrust of the engine is 100t, in a first period of time when the engine works, the required pressurization pressure of an oxygen tank of the storage tank is reduced from 0.37MPa to 0.14 MPa; the pressurization pressure required by the combustion box of the storage box is reduced from 0.33MPa to 0.09 MPa;
when the thrust of the engine is 25t, in the second working period of the engine, the pressurization pressure required by the oxygen tank of the storage tank is reduced to 0.10MPa from 0.14MPa, and the pressurization pressure required by the fuel tank of the storage tank is reduced to 0.05MPa from 0.09 MPa.
7. The pressure drop type pressurization design method for liquid oxymethane rocket tank according to claim 6,
when the thrust of the engine is 100t, the storage tank is pressurized in a self-generated pressurization mode in a first working period of the engine host, the actual pressurization of the oxygen tank is reduced from 0.39MPa to 0.36MPa, and the actual pressurization of the fuel tank is reduced from 0.35MPa to 0.32 MPa.
8. Liquid oxymethane rockets using a liquid oxymethane rocket tank pressure drop design method as claimed in any one of claims 1 to 7.
9. The liquid oxymethane rocket according to claim 8, wherein the liquid oxygen rocket includes:
an oxygen self-generating pressure increasing pipe (6) for communicating the combustion box (1) and the engine main machine (5);
a combustion self-generating pressure increasing pipe (7) which is communicated with the oxygen box (2) and the engine host (5);
an engine mount (3); and the combination of (a) and (b),
an engine combustion engine (4).
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| CN110716590B (en) * | 2019-10-18 | 2022-12-13 | 中国运载火箭技术研究院 | Liquid hydrogen storage tank pressure control system based on cryopump signal feedback |
| 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 |
| CN114320664A (en) * | 2022-02-08 | 2022-04-12 | 北京星际荣耀科技有限责任公司 | Anti-freezing supercooling device and rocket |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1346915A3 (en) * | 2002-03-19 | 2005-11-23 | Moog Inc. | Propellant supply device |
| CN101907041A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
| US9909574B1 (en) * | 2015-05-04 | 2018-03-06 | Cu Aerospace, Llc | Electrothermal space thruster heater for decomposable propellants |
| 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 |
| CN109018444A (en) * | 2018-08-02 | 2018-12-18 | 中国人民解放军国防科技大学 | Rocket-powered mars transporter power system |
Family Cites Families (1)
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| FR2976626B1 (en) * | 2011-06-17 | 2013-07-05 | Snecma | CRYOGENIC PROPULSIVE ASSEMBLY |
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2019
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Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1346915A3 (en) * | 2002-03-19 | 2005-11-23 | Moog Inc. | Propellant supply device |
| CN101907041A (en) * | 2010-07-23 | 2010-12-08 | 北京航空航天大学 | Propane liquid gas micro propulsion device suitable for micro-nano satellite |
| US9909574B1 (en) * | 2015-05-04 | 2018-03-06 | Cu Aerospace, Llc | Electrothermal space thruster heater for decomposable propellants |
| 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 |
| CN109018444A (en) * | 2018-08-02 | 2018-12-18 | 中国人民解放军国防科技大学 | Rocket-powered mars transporter power system |
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