CN114370355B - Differential variable thrust method and device, electronic equipment and storage medium - Google Patents
Differential variable thrust method and device, electronic equipment and storage medium Download PDFInfo
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- CN114370355B CN114370355B CN202210016685.3A CN202210016685A CN114370355B CN 114370355 B CN114370355 B CN 114370355B CN 202210016685 A CN202210016685 A CN 202210016685A CN 114370355 B CN114370355 B CN 114370355B
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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
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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
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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Abstract
The disclosure relates to a differential variable thrust method, and belongs to the technical field of engine thrust adjusting methods. When the coolant at the outlet of the cooling channel is in a subcritical state and is adjusted in a negative direction, the flow of the oxidant is reduced firstly, and then the flow of the fuel is reduced. When the cooling passage outlet of the engine is in a supercritical condition, both positively and negatively regulated, the oxidant and fuel flows are simultaneously increased or decreased. The method disclosed by the invention fully considers the influence of two-phase flow of the cooling channel on the response characteristic of the system, and when the forward adjustment is carried out, the flow of the oxidant and the flow of the fuel are simultaneously and actively increased, so that the smooth adjustment of the thrust of the engine can be realized; when the engine is adjusted in the negative direction (namely the thrust is adjusted from large to small), the flow of the oxidant and the flow of the fuel are simultaneously and actively reduced, when the outlet of the cooling channel is in the subcritical state, the flow of the oxidant is actively reduced, and then the flow of the fuel is actively reduced, so that the thrust of the engine can be smoothly adjusted, the parameter oscillation is avoided, the service life of the engine is prolonged, and the design requirement of the engine is reduced.
Description
The technical field is as follows:
the disclosure relates to the technical field of liquid rocket engine thrust adjusting methods, and in particular relates to a differential thrust changing method, electronic equipment and a machine readable storage medium for an electric pump liquid oxygen kerosene variable thrust rocket engine.
Background
Compared with the mature toxic propellant extrusion type engine and the like, the liquid oxygen kerosene motor pump variable-thrust liquid rocket engine has the advantages of environmental friendliness, adjustable thrust depth, convenience in adjustment and the like, and is widely concerned and continuously researched in recent years. Among these, the system response characteristics of the variable thrust rocket engine are of great importance. However, the current research on the electric pump liquid oxygen kerosene variable thrust engine mainly stays in the aspect of system scheme design, and the research on the system response characteristics directly determining the maneuverability of the spacecraft is relatively lacked.
In the aspect of dynamics of liquid oxygen kerosene variable thrust rocket engine systems, scholars at home and abroad have already carried out some work. Li Jinjiang establishes a general simulation platform for a low-temperature liquid rocket engine based on Amesim, which can improve the modeling efficiency of engine system simulation, but the simulation platform cannot consider the influence of two-phase flow of a cooling channel. 5363 and the like establish simulation models of liquid oxygen kerosene different circulation engine systems, namely Chen Hongyu, li Ying, tan Yonghua, jihyoung Cha and the like, but the influence of a cooling channel is not considered.
The method is relatively preliminary in the aspect of the dynamics of the electric pump variable-thrust liquid rocket engine system. Liu Yangji carries out dynamics modeling and simulation research on a motor pump supercharging variable thrust engine on an Amesim platform, and compared with throttle valve adjustment, the pump rotating speed adjustment consumes less energy. But it does not consider the power supply, motor, cooling channel model, and the two-phase flow effect due to low temperature.
Disclosure of Invention
The present disclosure is directed to overcome or partially overcome the above technical problems, and provides a differential variable thrust method, an electronic device and a machine readable storage medium for an electric pump liquid oxygen kerosene variable thrust rocket engine, so as to fully consider the influence of two-phase flow of a cooling channel on the response characteristics of a system and achieve smooth adjustment of thrust.
In a first aspect, an embodiment of the present disclosure provides a differential variable thrust method for an electric pumping type liquid oxygen kerosene variable thrust rocket engine, including: the coolant at the outlet of the cooling channel is in a subcritical state, and when the coolant is adjusted in a negative direction, the flow of the oxidant is reduced firstly, and then the flow of the fuel is reduced.
In a second aspect, the disclosed embodiments provide a differential variable thrust device for an electric pump type liquid oxygen kerosene variable thrust rocket engine, including: the detection device is arranged at the outlet of the engine cooling channel and is used for detecting whether the outlet coolant is in a subcritical state or not; the adjusting device is used for reducing the flow of the oxidant firstly and then reducing the flow of the fuel when the detecting device detects that the outlet coolant is in a subcritical state.
In a third aspect, an embodiment of the present disclosure provides an electronic device, including:
a memory;
a processor; and
a computer program;
wherein the computer program is stored in the memory and configured to be executed by the processor to implement the method of the first aspect.
In a fourth aspect, an embodiment of the present invention provides a computer-readable storage medium, on which a computer program is stored, where the computer program is implemented, when executed by a processor, as the method in the first aspect.
Has the advantages that:
the method, the device, the electronic equipment and the computer readable storage medium provided by the disclosure fully consider the influence of two-phase flow of the cooling channel on the response characteristic of the system, and when the forward regulation is carried out (namely the thrust is regulated from small to large), the flow of the oxidant and the fuel are simultaneously and actively increased, so that the thrust of the engine can be smoothly regulated; when the engine is adjusted in a negative direction (namely the thrust is adjusted from large to small), the flow of the oxidant and the flow of the fuel are actively reduced at the same time, when the outlet of the cooling channel is in a subcritical state, the flow of the oxidant is actively reduced, and then the flow of the fuel is actively reduced, so that the thrust of the engine can be smoothly adjusted, the parameter oscillation is avoided, the service life of the engine is prolonged, and the design requirement of the engine is reduced.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and together with the description, serve to explain the principles of the invention.
In order to more clearly illustrate the embodiments or technical solutions in the prior art of the present disclosure, the drawings used in the description of the embodiments or prior art will be briefly described below, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive exercise.
FIG. 1 is a schematic structural diagram of an electric pump liquid oxygen kerosene variable thrust rocket engine provided in an embodiment of the disclosure;
FIG. 2 is a simulation model of an electric pump liquid oxygen kerosene variable thrust liquid rocket engine provided in an embodiment of the present disclosure;
FIG. 3 shows the simultaneous adjustment of the lower chamber pressure p by the control signal of the oxygen-fuel motor c A schematic diagram of a thrust F vs. time variation curve;
FIG. 4 is a diagram of the room pressure p after the fuel corner cross arm weighting factor is adjusted downward after the oxygen corner cross arm weighting factor is adjusted downward c And a schematic diagram of the thrust F versus time curve;
fig. 5 is a schematic structural diagram of an electronic device according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of another electronic device according to an embodiment of the present invention.
Detailed Description
In order that the above objects, features and advantages of the present invention may be more clearly understood, a solution of the present invention will be further described below. It should be noted that the embodiments of the present invention and features of the embodiments may be combined with each other without conflict.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be practiced in other ways than those described herein; it is to be understood that the embodiments described in this specification are only some embodiments of the invention, and not all embodiments.
In a fuel-powered engine, generally, to increase the thrust force, the oxygen and fuel flow rates should be increased at the same time, and to decrease the thrust force, the oxygen and fuel flow rates should be decreased at the same time. However, the inference is not completely applicable to a rocket engine which is sent from the earth to the space, and due to the particularity of the use scene of the rocket engine, the thrust in the running track of the rocket engine is changed constantly according to the states of the running altitude, the speed and the like of the rocket engine, so that high requirements are put forward on the design of the rocket engine. In the prior art, the influence of two-phase flow of a cooling channel on the response characteristic of a system cannot be fully considered when a variable thrust rocket engine system is subjected to simulation research. Therefore, the engine can shake during negative regulation, and higher design implementation requirements are provided for the engine.
The differential variable thrust method provided by the embodiment of the disclosure realizes smooth adjustment of the engine through adjustment of power raw materials.
The embodiment of the disclosure provides a differential variable thrust method, which is used for a variable thrust rocket engine. When the cooling passage outlet of the engine is in a supercritical condition, both positively and negatively regulated, the oxidant and fuel flows are simultaneously increased or decreased.
As shown in fig. 1, the electric pump liquid oxygen kerosene variable thrust rocket engine applied to the method of the embodiment of the present disclosure includes an oxygen battery 14 for providing energy to an oxygen motor 12; the oxygen corner cross arm 13 is connected with the oxygen battery 14 through an oxygen circuit 16, and regulates the input voltage and current of the oxygen motor 12 by regulating the weight factor (namely the control signal of the transistor, representing the opening of the transistor, and the opening is the largest when the value is 1 and the opening is the smallest when the value is 0), so as to regulate the power of the oxygen pump 11 and finally regulate the flow of the oxidant; an oxygen motor 12 connected to the oxygen corner cross arm 13 through an oxygen circuit 16 for driving the oxygen pump 11; the oxygen pump 11 is mechanically connected with the oxygen motor 12 through an oxygen shaft 19 and is used for pressurizing liquid oxygen; an oxygen main valve 10 connected to the oxygen pump 11 through an oxygen line 15, located downstream of the oxygen pump 11, and functioning as a switch; a fuel cell 1 for supplying power to a fuel motor 3; the fuel corner cross arm 2 is connected with the fuel cell 1 through a fuel circuit 18, and adjusts the input voltage and the current of the fuel motor 3 by adjusting the weighting factor of the fuel corner cross arm, so as to adjust the power of the fuel pump 4 and finally adjust the fuel flow; a fuel motor 3 connected to the fuel angle cross arm 2 via a fuel circuit 18 for driving the fuel pump 4; a fuel pump 4 mechanically connected to the fuel motor 3 through a fuel shaft 20 for pressurizing fuel; a fuel main valve 5 connected to the fuel pump 4 through a fuel line 17, located downstream of the fuel pump 4, and functioning as a switch; a cooling channel 7 connected to the main fuel valve 5 via a fuel line 17, downstream of the main fuel valve 5, for cooling the combustion chamber 8 and the nozzle 6; an injector 9 connected to the oxygen main valve 10 through an oxidizer line 15 and to the cooling channel 7 through a fuel line 17 for injecting and atomizing the oxidizer and the fuel into the combustion chamber 8; the combustion chamber 8 is positioned at the downstream of the injector 9 and is used for organizing the combustion of an oxidant and a fuel to generate high-temperature and high-pressure fuel gas; and the spray pipe 6 is positioned at the downstream of the combustion chamber and accelerates the high-temperature and high-pressure fuel gas generated by the combustion chamber 8 to generate thrust.
Alternatively, in the rocket engine application scenario shown in fig. 1, the adjustment of the oxidant flow is achieved by adjusting the weighting factor of the oxygen turn angle cross arm 13 of the engine, and the adjustment of the fuel flow is achieved by adjusting the weighting factor of the fuel turn angle cross arm 2 of the engine.
When the thrust is adjusted in the forward direction (from small to large), the weighting factors of the oxygen rudder angle crossarm 13 and the fuel rudder angle crossarm 2 are changed at the same time.
When the thrust is adjusted in a negative direction (from large to small), the weight factors of the oxygen corner cross arm 13 and the fuel corner cross arm 2 are changed simultaneously when the outlet parameter of the cooling channel 7 is in a supercritical state; when the outlet parameter of the cooling channel 7 is in subcritical state, firstly adjusting the weight factor of the oxygen corner cross arm 13 to reduce the wall surface temperature of the cooling channel 7, and then adjusting the weight factor of the fuel corner cross arm 2 to realize smooth adjustment of the engine thrust. Those skilled in the art know that a substance is in a supercritical state when it exceeds its critical pressure and critical temperature. In the supercritical case, the fluid is no longer divided into gas and liquid phases. When the temperature of the material is higher than the boiling point but lower than the critical temperature and the pressure is lower than the critical pressure, the material is in a subcritical state.
Optionally, the cooling mode adopted by the electric pump liquid oxygen kerosene variable thrust rocket engine provided by the embodiment of the disclosure is regenerative cooling, as shown in fig. 1, fuel such as kerosene is used as fuel and coolant, the fuel moves upwards along the outer walls of the nozzle 6 and the combustion chamber 8 through the cooling channel 7, the wall surface of the fuel is cooled to remove heat, the temperature of the fuel is raised, and the fuel is injected into the combustion chamber 8 through the injector 9 to be mixed with oxygen for combustion.
Alternatively, as shown in figure 1, the cooling channels 7 are counterflow and cover part or all of the nozzle 6 and combustion chamber 8 of the rocket motor, in order to better cool the nozzle throat. Specifically, the throat part of the nozzle is the narrowest part where the combustion chamber 8 is connected with the nozzle 6, and the combustion chamber 8 is a cylindrical section and a contraction section below the cylindrical section. Liquid oxygen directly enters the injector 9; the kerosene is changed into high-temperature kerosene through the cooling channel 7 and enters the injector 9; finally, after the oxygen and the kerosene are sprayed out through the injector 9, the oxygen and the kerosene are atomized and mixed, the oxygen and the kerosene are combusted in the combustion chamber 8 and sprayed out at high speed in the spray pipe 6, and the conversion from heat energy to mechanical energy is completed.
Further, in order to make the power adjustment of the engine smoother, the embodiment of the present disclosure sets the weight factor adjustment time interval of the oxygen turning angle cross arm 13 and the fuel turning angle cross arm 2 to 5s.
Further, in order to make the power of the engine sufficient and as light as possible, the disclosed implementation selects the fuel to be methane.
The embodiment of the disclosure further provides a differential variable thrust device, which comprises a detection device and an adjusting device, wherein the detection device is arranged at the outlet of the engine cooling channel and is used for detecting whether the outlet coolant is in a subcritical state; the adjusting device is used for reducing the flow of the oxidant firstly and then reducing the flow of the fuel when the detecting device detects that the outlet coolant is in a subcritical state. In the rocket engine shown in fig. 1, the detection means 21 comprise pressure and temperature sensors and the regulating means comprise a fuel transfer cross-arm 2 and an oxygen transfer cross-arm 13.
Alternatively, in the rocket engine application scenario shown in fig. 1, the adjustment of the oxidant flow is performed by adjusting the weighting factor of the oxygen turn angle cross arm 13 of the engine, and the adjustment of the fuel flow is performed by adjusting the weighting factor of the fuel turn angle cross arm 2 of the engine.
Alternatively, as shown in fig. 1, the cooling channels 7 are counterflow and cover part or all of the nozzle 6 and combustion chamber 8 of the rocket motor for better cooling of the nozzle throat.
Further, in order to make the power adjustment of the engine smoother, the embodiment of the present disclosure sets the weight factor adjustment time interval of the oxygen turning angle cross arm 13 and the fuel turning angle cross arm 2 to 5s.
Further, in order to make the engine power efficient, cost effective, and as light as possible, the disclosed implementation selects the fuel to be methane.
Fig. 5 is a schematic structural diagram of an embodiment of an electronic device provided in the embodiment of the present disclosure, where the electronic device may execute a processing flow provided in the foregoing method embodiment. As shown in fig. 5, the electronic device includes a memory 151 and a processor 152.
And a memory 151 for storing a program. In addition to the above-described programs, the memory 151 may also be configured to store other various data to support operations on the electronic device. Examples of such data include instructions for any application or method operating on the electronic device, contact data, phonebook data, messages, pictures, videos, and the like.
The memory 151 may be implemented by any type or combination of volatile or non-volatile memory devices such as Static Random Access Memory (SRAM), electrically erasable programmable read-only memory (EEPROM), erasable programmable read-only memory (EPROM), programmable read-only memory (PROM), read-only memory (ROM), magnetic memory, flash memory, magnetic or optical disks.
A processor 152, coupled to the memory 151, executes the program stored in the memory 71 for use in the methods described above.
Further, as shown in fig. 5, the electronic device may further include: communication components 153, power components 154, audio components 155, a display 156, and other components. Only some of the components are schematically shown in fig. 5, and it is not meant that the electronic device comprises only the components shown in fig. 5.
The communication component 153 is configured to facilitate wired or wireless communication between the electronic device and other devices. The electronic device may access a wireless network based on a communication standard, such as WiFi,2G or 3G, or a combination thereof. In an exemplary embodiment, the communication component 153 receives a broadcast signal or broadcast related information from an external broadcast management system via a broadcast channel. In an exemplary embodiment, the communication component 153 further includes a Near Field Communication (NFC) module to facilitate short-range communication. For example, the NFC module may be implemented based on Radio Frequency Identification (RFID) technology, infrared data association (IrDA) technology, ultra Wideband (UWB) technology, bluetooth (BT) technology, and other technologies.
A power supply component 154 provides power to the various components of the electronic device. The power components 154 may include a power management system, one or more power sources, and other components associated with generating, managing, and distributing power for an electronic device.
The display 156 includes a screen, which may include a Liquid Crystal Display (LCD) and a Touch Panel (TP). If the screen includes a touch panel, the screen may be implemented as a touch screen to receive an input signal from a user. The touch panel includes one or more touch sensors to sense touch, slide, and gestures on the touch panel. The touch sensor may not only sense the boundary of a touch or slide action, but also detect the duration and pressure associated with the touch or slide operation.
Fig. 6 is a schematic structural diagram of another electronic device according to an embodiment of the present disclosure, where the device may execute the processing flow provided by the foregoing method embodiment, and as shown in fig. 6, the electronic device 110 includes: memory 111, processor 112, computer programs, and communications interface 113; wherein the computer program is stored in the memory 111 and is configured to be executed by the processor 112 for performing the method as described above.
In addition, the embodiment of the present disclosure also provides a computer readable storage medium, on which a computer program is stored, the computer program being executed by a processor to implement the method of the above embodiment. Those of ordinary skill in the art will understand that: all or a portion of the steps of implementing the above-described method embodiments may be performed by hardware associated with program instructions. The program may be stored in a computer-readable storage medium. When executed, the program performs steps comprising the method embodiments described above; and the aforementioned storage medium includes: various media that can store program codes, such as ROM, RAM, magnetic or optical disks.
The realization and effect of the differential variable thrust method, the differential variable thrust device, the electronic equipment and the computer readable storage medium provided by the embodiment of the disclosure can be verified by carrying out system simulation through Amesim software. The system simulation model of the electric pump liquid oxygen kerosene variable thrust liquid rocket engine shown in fig. 1 is shown in fig. 2, wherein 9 (1) represents an oxygen injector, 9 (2) represents a fuel injector, a represents a fuel storage tank, b represents a fuel electric explosion valve, c represents a fuel pump rotor, d represents a fuel hose, e represents an environmental parameter, f represents a gas fraction query module, g represents an oxygen pre-cooling valve, h represents an oxygen hose, i represents an oxygen pump rotor, j represents an oxygen electric explosion valve, and k represents an oxygen storage tank. The simulation model was solved to obtain the following results.
FIG. 3 shows that the weight factors of the oxygen and combustion corner cross arms are simultaneously adjusted to lower chamber pressure p c Thrust F varying with timeCurve, each stage of thrust level conversion process is 54.4-RPL → 73.3-RPL → 100-RPL → 73.3-RPL → 54.4-RPL, wherein RPL represents the rated thrust level, rated power level. It can be seen that chamber pressure and thrust oscillations occur when rpl (the condition cooling channel outlet is supercritical) was negatively adjusted 77.3% to 54.4% rpl (the condition cooling channel outlet is subcritical).
FIG. 4 shows the time-dependent change curves of the chamber pressure and the thrust at the time of the downward-adjustment of the fuel corner cross-arm weight factor after the downward-adjustment of the fuel corner cross-arm weight factor, wherein the horizontal lines from the high to the low thrust are 100% RPL, 73.3% RPL, 54.4% RPL, 29.2% RPL, 14.8% RPL, 10.1% RPL, respectively. It can be seen that when the RPL is adjusted to 54.4% RPL in the negative direction of 77.3%, the chamber pressure and the thrust are stable and there is no oscillation, because the oxygen turning angle cross arm weight factor is adjusted first, which means that the oxygen motor power is reduced, the oxygen motor speed is reduced, the oxidant flow is reduced, and the fuel motor is not reduced, so the combustion chamber mixing ratio (the mixing ratio is the ratio of the oxidant flow to the fuel flow) is reduced, which results in the instant reduction of the gas temperature, further reducing the wall temperature of the cooling channel, and moderating the environment where the coolant is located, thereby achieving smooth adjustment. As can be seen from a comparison between fig. 3 and fig. 4, by using the method of the present disclosure, when the thrust is adjusted in the negative direction (from large to small), and the outlet parameter of the cooling passage 7 is in the subcritical state, the weighting factor of the oxygen turning angle cross arm 13 is adjusted first, and then the weighting factor of the fuel turning angle cross arm 2 is adjusted, so that the smooth adjustment of the engine thrust can be realized, the oscillation can be prevented, the design and implementation requirements on the engine can be reduced, and the service life of the engine can also be prolonged.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. A differential variable thrust method is characterized in that the method is used for an electric pump liquid variable thrust rocket engine, a cooling channel is connected with a fuel main valve through a fuel pipeline, and the cooling channel is positioned at the downstream of the fuel main valve and used for cooling a combustion chamber and a spray pipe; when the outlet coolant of the cooling channel is in a subcritical state and the negative regulation is carried out, namely the thrust is regulated from large to small, the flow of the oxidant is firstly reduced, and then the flow of the fuel is reduced.
2. The method of claim 1, wherein the adjusting of the oxidant flow is accomplished by adjusting a weighting factor of an oxygen turn angle cross-arm of the engine and the adjusting of the fuel flow is accomplished by adjusting a weighting factor of a fuel turn angle cross-arm of the engine.
3. The method of claim 2, wherein the cooling passage is counter-flow and covers part or all of a nozzle and a combustion chamber of the rocket engine.
4. The method of claim 3, wherein the weighting factor adjustment time interval for the oxygen turn angle cross arm and the fuel turn angle cross arm is 5s.
5. The method of claim 4, wherein the fuel is methane.
6. A differential variable thrust device is characterized by being used for an electric pumping type liquid oxygen kerosene variable thrust rocket engine and comprising a detection device and an adjusting device, wherein a cooling channel is connected with a fuel main valve through a fuel pipeline, and the cooling channel is positioned at the downstream of the fuel main valve and used for cooling a combustion chamber and a spray pipe; the detection device is arranged at the outlet of the cooling channel and used for detecting whether the outlet coolant is in a subcritical state or not; the adjusting device is used for reducing the flow of the oxidant firstly and then reducing the flow of the fuel when the detecting device detects that the outlet coolant is in the subcritical state and when the outlet coolant is adjusted in the negative direction, namely when the thrust is adjusted from large to small.
7. The apparatus of claim 6, wherein the adjustment of the oxidant flow is achieved by adjusting a weighting factor of an oxygen turn angle cross-arm of the engine and the adjustment of the fuel flow is achieved by adjusting a weighting factor of a fuel turn angle cross-arm of the engine.
8. The apparatus of claim 7, wherein the weighting factor adjustment time interval for the oxygen corner crossarm and the fuel corner crossarm is 5s.
9. An electronic device, comprising:
a memory;
a processor; and
a computer program;
wherein the computer program is stored in the memory and configured to be executed by the processor to implement the method of any one of claims 1-5.
10. A computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the method according to any one of claims 1-5.
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| RU2006115260A (en) * | 2006-05-05 | 2007-11-20 | Открытое акционерное общество "НПО Энергомаш имени академика В.П. Глушко" (RU) | METHOD FOR PRODUCING A CRITICAL CROSS-SECTION OF A NOZZLE OF A LIQUID ROCKET ENGINE CAMERA NOZZLE |
| CN104358625A (en) * | 2014-07-11 | 2015-02-18 | 中国航天科技集团公司第六研究院第十一研究所 | Method for closed-loop control of thrust of thrust-variable engine |
| CN108953003A (en) * | 2018-06-28 | 2018-12-07 | 西安航天动力研究所 | A kind of promoted using oxygen rich fuel gas realizes afterburning cycle engine system and thrust depth adjustment method |
| CN112065605A (en) * | 2020-09-29 | 2020-12-11 | 航天科工火箭技术有限公司 | Variable thrust pump pressure type liquid rocket engine system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8776494B2 (en) * | 2010-06-22 | 2014-07-15 | Cal Poly Corporation | System, method and apparatus for cooling rocket motor components using a saturated liquid vapor coolant mixture |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2006115260A (en) * | 2006-05-05 | 2007-11-20 | Открытое акционерное общество "НПО Энергомаш имени академика В.П. Глушко" (RU) | METHOD FOR PRODUCING A CRITICAL CROSS-SECTION OF A NOZZLE OF A LIQUID ROCKET ENGINE CAMERA NOZZLE |
| CN104358625A (en) * | 2014-07-11 | 2015-02-18 | 中国航天科技集团公司第六研究院第十一研究所 | Method for closed-loop control of thrust of thrust-variable engine |
| CN108953003A (en) * | 2018-06-28 | 2018-12-07 | 西安航天动力研究所 | A kind of promoted using oxygen rich fuel gas realizes afterburning cycle engine system and thrust depth adjustment method |
| CN112065605A (en) * | 2020-09-29 | 2020-12-11 | 航天科工火箭技术有限公司 | Variable thrust pump pressure type liquid rocket engine system |
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