CN114060171B - Rocket and rocket propellant sloshing inhibition method and device - Google Patents
Rocket and rocket propellant sloshing inhibition method and device Download PDFInfo
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- CN114060171B CN114060171B CN202111076246.3A CN202111076246A CN114060171B CN 114060171 B CN114060171 B CN 114060171B CN 202111076246 A CN202111076246 A CN 202111076246A CN 114060171 B CN114060171 B CN 114060171B
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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
Abstract
The invention discloses a rocket and a method and a device for inhibiting the shaking of a propellant, comprising the following steps: detecting whether a preliminary shutdown signal of a main engine of the rocket is received; when a preparation shutdown signal of the main engine is received and the time interval between the current moment and the moment of receiving the preparation shutdown signal is a first set time interval, controlling the thrust of the main engine to be reduced to a first target thrust, and controlling an auxiliary engine of the rocket to provide the thrust in the flight direction for the rocket by using a second target thrust. The overload reducing method and the overload reducing device have the advantages that the overload is provided by the auxiliary engine in the process of reducing the overload of the main engine, the overload reducing degree of the rocket is further reduced, the shaking amplitude of the propellant is greatly reduced, the mixing degree of the residual propellant and the supercharged gas in the storage box can be reduced, the gas inclusion risk of the propellant in the power conveying pipeline is avoided to a certain extent, the reliability of secondary starting of the main engine is improved, and the flight safety of the rocket is improved.
Description
Technical Field
The invention relates to the technical field of rockets, in particular to a rocket and a rocket propellant sloshing suppression method and device.
Background
In order to break through rocket recovery technology with high efficiency, a vertical take-off and landing demonstration and verification rocket flight test is usually developed. And verifying all key technologies of recovering the rocket through vertical take-off and landing demonstration and verification of take-off, hovering, maneuvering, landing and rapid multiplexing of the rocket.
The existing vertical take-off and landing demonstration rocket is generally divided into low-altitude verification flight and high-altitude verification flight according to the flight altitude. The low-altitude verification flight can be realized by starting the rocket main engine once, and the rocket body is overloaded in the whole flight process without propellant management problems. The high-altitude verification flight test needs to be realized by starting the rocket main engine for multiple times, and when the main engine is shut down for the first time, because the rocket body flight overload is greatly reduced, the shaking amplitude of the residual propellant in the storage tank is larger, so that the propellant management problem exists, and the restarting of the rocket main engine for demonstration and verification can be influenced.
Disclosure of Invention
The embodiment of the application provides a rocket and a rocket propellant shaking suppression method and device, solves the technical problem that in the prior art, the shaking amplitude of residual propellant in a storage tank is large due to the fact that the rocket body is greatly reduced in flying overload, achieves the technical effects of reducing the shaking amplitude of the residual propellant in the storage tank and reducing the influence on the demonstration and verification of the restarting of a rocket main engine.
In a first aspect, the present application provides a rocket propellant sloshing suppression method, the method comprising:
detecting whether a preliminary shutdown signal of a main engine of the rocket is received;
when a preparation shutdown signal of the main engine is received and the time interval between the current time and the time of receiving the preparation shutdown signal is a first set time interval, controlling the thrust of the main engine to be reduced to a first target thrust, and controlling an auxiliary engine of the rocket to provide the thrust in the flight direction for the rocket by using a second target thrust.
Further, the first set time interval is 1s to 2s.
Further, when the time interval between the present time and the time at which the thrust force of the main engine is controlled to decrease to the first target thrust force is a second set time interval, the method further includes:
and controlling the main engine to shut down, and controlling the auxiliary engine to continuously provide the rocket with the thrust in the flight direction at the second target thrust.
Further, the second set time interval is 3s to 3.5s.
Further, after controlling the main engine to shut down, the method further comprises:
detecting whether an ignition signal of a main engine is received;
and when the ignition signal of the main engine is received and the time interval between the current moment and the moment of receiving the ignition signal of the main engine is a third set time interval, controlling the auxiliary engine to be shut down.
Further, the third set time interval is 2s to 3s.
Further, controlling an auxiliary engine of the rocket to provide the rocket with a thrust in the flight direction at a second target thrust, comprising:
determining a second target thrust according to the propellant density, the flight direction overload, the propellant storage tank radius and the propellant surface tension coefficient of the rocket;
and controlling the auxiliary engine to provide the rocket with the thrust in the flight direction at the second target thrust.
Further, controlling the thrust of the main engine to decrease to the first target thrust includes:
determining a first target thrust according to the current total thrust of the rocket, the mass of the rocket body, the flying height and the overload;
the thrust of the main engine is controlled to be reduced to the first target thrust.
In a second aspect, the present application provides a rocket propellant sloshing suppression device, the device comprising:
the detection module is used for detecting whether a prepared shutdown signal of a main engine of the rocket is received or not;
and the control module is used for controlling the thrust of the main engine to be reduced to a first target thrust and controlling the auxiliary engine of the rocket to provide the thrust in the flight direction for the rocket by using a second target thrust when the preparation shutdown signal of the main engine is received and the time interval between the current time and the time when the preparation shutdown signal is received is a first set time interval.
In a third aspect, the present application provides a rocket comprising a primary engine and an auxiliary engine; when the main engine is ready to be shut down and/or shut down, the auxiliary engine is controlled to provide thrust in the flight direction to the rocket.
One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:
when a standby shutdown signal of the main engine is received, the thrust of the main engine is controlled to be reduced to a first target thrust, the auxiliary engine of the rocket is controlled to provide the thrust in the flight direction for the rocket by using a second target thrust, namely, the overload is reduced in the process of reducing the overload of the main engine, the overload is provided by the auxiliary engine, the overload reduction degree of the rocket is further reduced, the shaking amplitude of the propellant is greatly reduced, the mixing degree of the residual propellant and the supercharged gas in the storage tank can be reduced, the gas inclusion risk of the propellant in a power conveying pipeline is avoided to a certain extent, the reliability of secondary startup of the main engine is improved, and the flight safety of the rocket is improved.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on the drawings without creative efforts.
FIG. 1 is a schematic flow diagram illustrating a first method for suppressing rocket propellant sloshing according to the present disclosure;
FIG. 2 is a schematic flow diagram of a second method for rocket propellant sloshing suppression provided herein;
FIG. 3 is a schematic diagram of the relationship between a plurality of set time intervals provided herein;
fig. 4 is a schematic structural diagram of a rocket propellant sloshing suppression device provided by the present application.
Detailed Description
The embodiment of the application provides a rocket propellant shaking inhibiting method, and solves the technical problem that the shaking amplitude of residual propellant in a storage tank is large in the prior art.
In order to solve the technical problems, the general idea of the embodiment of the application is as follows:
a rocket propellant sloshing suppression method, the method comprising: detecting whether a preliminary shutdown signal of a main engine of the rocket is received; when a preparation shutdown signal of the main engine is received and the time interval between the current time and the time of receiving the preparation shutdown signal is a first set time interval, controlling the thrust of the main engine to be reduced to a first target thrust, and controlling an auxiliary engine of the rocket to provide the thrust in the flight direction for the rocket by using a second target thrust.
The embodiment reduces the in-process of transshipping at main engine to the auxiliary engine provides and transships, and then has reduced the degree that the rocket transships and has reduced, makes the range that the propellant rocked reduce by a wide margin, can also reduce surplus propellant and pressurized gas will be at the storage tank degree of mixing, has avoided the gas inclusion risk of the propellant in the power transmission pipeline to a certain extent, improves the reliability of main engine secondary start-up, improves the flight safety of rocket.
In order to better understand the technical scheme, the technical scheme is described in detail in the following with reference to the attached drawings of the specification and specific embodiments.
First, it is stated that the term "and/or" appearing herein is merely one type of associative relationship that describes an associated object, meaning that three types of relationships may exist, e.g., a and/or B may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter associated objects are in an "or" relationship.
The existing vertical take-off and landing demonstration rocket is generally divided into low-altitude verification flight and high-altitude verification flight according to the flight altitude. The low-altitude verification flight can be realized by starting the rocket main engine once, and the rocket body is overloaded in the whole flight process without propellant management problems. The high-altitude verification flight test needs to be realized by starting the rocket main engine for multiple times, and when the main engine is shut down for the first time, because the rocket body flight overload is greatly reduced, the shaking amplitude of the residual propellant in the storage tank is larger, so that the propellant management problem exists, and the restarting of the rocket main engine for demonstration and verification can be influenced.
More specifically, the primary engine may involve multiple shutdowns and multiple firings during high altitude validation flight of the rocket. After the main engine is shut down, overload can be greatly reduced, propellant in the storage tank can greatly shake due to the inertia effect, the risk that liquid impacts the front bottom of the storage tank exists, residual propellant and pressurized gas are fully mixed in the storage tank due to the fact that no overload flight working condition exists in the following aircraft in the sliding process, the propellant in the power transmission pipeline has the risk of air entrainment, the reliability of the engine during secondary starting is reduced, and the flight safety of the aircraft is affected.
Compared with low-altitude verification flight, the flight working condition of high-altitude verification flight is closer to the real flight working condition during rocket recovery, and the demonstration verification of the key technology of the recovered rocket can be better carried out. Therefore, the problem of propellant shaking after rocket shutdown is demonstrated and verified needs to be solved.
In order to solve the above technical problem, the embodiment provides a rocket propellant sloshing suppression method as shown in fig. 1, which is applied to a controller of a rocket, and the solution provided by the embodiment is described with reference to fig. 2 and fig. 3.
Step S11, detecting whether a preliminary shutdown signal of a main engine of the rocket is received;
and S12, when a preparation shutdown signal of the main engine is received and the time interval between the current time and the time of receiving the preparation shutdown signal is a first set time interval, controlling the thrust of the main engine to be reduced to a first target thrust and controlling an auxiliary engine of the rocket to provide the thrust in the flight direction for the rocket by using a second target thrust. The first set time interval is 1s to 2s. The first set time interval is related to the time delay characteristic of the thrust regulation of the main engine and the time delay characteristic of the control signal transmission loop, and 1 s-2 s can cover the thrust regulation time delay characteristic of the pumping type liquid engine, so that the engine can normally execute the thrust regulation.
When the time interval between the present time and the time at which the thrust of the main engine is controlled to decrease to the first target thrust is a second set time interval, the method further includes:
and S13, controlling the main engine to shut down, and controlling the auxiliary engine to continuously provide the thrust in the flight direction for the rocket by using the second target thrust. The second set time interval is 3s to 3.5s. The second set time interval is related to the time delay characteristic of the thrust regulation of the main engine and the time delay characteristic of the control signal transmission loop, and 3 s-3.5 s can cover the thrust regulation time delay characteristic of the pumping type liquid engine, so that the engine is normally shut down.
After controlling the main engine to shut down, the method further comprises:
step S14, detecting whether an ignition signal of a main engine is received;
and step S15, when the ignition signal of the main engine is received and the time interval between the current time and the time when the ignition signal of the main engine is received is a third set time interval, controlling the auxiliary engine to shut down. The third set time interval is 2s to 3s. The third set time interval is related to the time delay characteristic of the thrust regulation of the main engine and the time delay characteristic of the control signal transmission loop, and 2s to 3s can cover the thrust regulation time delay characteristic of the pumping type liquid engine, so that the engine can be started normally.
Whether a preparation shutdown signal of the main engine is received or not is detected, and when the preparation shutdown signal is received, the main engine enters the overload reduction process, and at the moment, measures for restraining the propellant from shaking are needed. After the preliminary shutdown signal of the main engine is received and the first set time interval t1 is passed, the thrust of the main engine is controlled to be reduced to the first target thrust, and the auxiliary engine is controlled to provide the rocket with the thrust in the flight direction. Within a first set time interval t1, the thrust of the main engine gradually decreases, and at the same time, the auxiliary engine provides a second target thrust, reducing the extent of the decrease in rocket overload, i.e. providing a portion of overload for the rocket.
For example, when the preliminary shutdown signal is received, the overload of the rocket is 2g, and in the process that the thrust of the main engine is gradually reduced to the first target thrust, the overload of the rocket is reduced to 1.2g under the condition that the auxiliary engine does not provide the second target thrust, so that the overload is reduced too much, and the oscillation amplitude of the propellant is large. The auxiliary engine is additionally arranged in the embodiment, the second target thrust is provided for the rocket, the overload of the rocket is 1.6g, the degree of reduction of the overload of the rocket is further reduced, the amplitude of the shaking of the propellant is greatly reduced, the mixing degree of the residual propellant and the pressurized gas in the storage tank can be reduced, the gas inclusion risk of the propellant in the power conveying pipeline is avoided to a certain extent, the reliability of the secondary starting of the main engine is improved, and the flight safety of the rocket is improved.
Wherein, the auxiliary engine of control rocket uses the second target thrust to provide the thrust of flight direction for the rocket, includes:
and S21, determining a second target thrust according to the propellant density, the flight direction overload, the propellant storage tank radius and the propellant surface tension coefficient of the rocket.
And S22, controlling the auxiliary engine to provide the rocket with the thrust in the flight direction by using the second target thrust.
Thrust magnitude reference bond number B for assisting second target thrust of engine 0 And (5) designing. Wherein, the bond number
Rho is the density of the propellant, n is the rocket body flying direction overload, r is the radius of the propellant storage tank, and sigma is the surface tension coefficient of the propellant. In this embodiment, the bond number B 0 The value is not less than 500.
Controlling the thrust of the main engine to decrease to a first target thrust, comprising:
step S31, determining a first target thrust according to the current total thrust of the rocket, the mass of the rocket body, the flying height and the overload;
in step S32, the thrust of the main engine is controlled to be reduced to the first target thrust.
Propellant in the rocket is consumed in the flying process, the mass change of the propellant can cause the mass change of the rocket, so that the adjustment of the thrust of the engine in each stage is determined according to the iterative calculation of thrust to mass to altitude to overload, and the staggered change of axial flying overload of the rocket body is realized. Therefore, the first target thrust needs to be calculated and adjusted in real time according to the real-time parameters of the rocket.
In step S12, a preliminary shutdown signal of the main engine is received, and after a first set time interval t1, the thrust of the main engine is reduced to a first target thrust, and the auxiliary engine provides thrust to the rocket at a second target thrust. After that, step S13 is executed to wait for a second set time interval t2, control the main engine to shut down, control the auxiliary engine to continue to provide the rocket with the thrust in the flight direction at the second target thrust, at this time, the main engine does not provide overload, and only the auxiliary engine provides overload.
The embodiment reduces the in-process of transshipping at main engine to the auxiliary engine provides and transships, and then has reduced the degree that the rocket transships and has reduced, makes the range that the propellant rocked reduce by a wide margin, can also reduce surplus propellant and pressurized gas will be at the storage tank degree of mixing, has avoided the gas inclusion risk of the propellant in the power transmission pipeline to a certain extent, improves the reliability of main engine secondary start-up, improves the flight safety of rocket.
After step S13, or during the high altitude verification flight, as long as the main engine is off, step S14 is executed to detect whether the ignition signal of the main engine is received, and when the ignition signal of the main engine is received, it means that the main engine can start the rocket to provide overload. And the starting process of the main engine needs time, so that the auxiliary engine is controlled to be shut down after the main engine is started up after the third set time interval t3 is waited, or the main engine starts to provide overload to a certain extent for the rocket, the overload is completely provided by the main engine until a prepared shutdown signal of the main engine is detected next time, and the method provided by the embodiment is reused.
Referring to fig. 3, after the main engine of the rocket sends a main engine preliminary shutdown signal at time T0, the main engine sends thrust adjustment and the auxiliary engine is started at preset time T1, the main engine executes a shutdown program at time T2, and the auxiliary engine keeps working normally. In the rocket sliding process, the auxiliary engine keeps normal work and provides overload required by the bottom sinking of the storage tank propellant, the main engine executes a secondary starting program at the moment T3, after the preset time T3, the auxiliary power system bottom sinking engine finishes the rocket body propellant management, and the rocket body main engine thrust is subsequently used for providing the propellant bottom sinking overload until the rocket landing is verified through demonstration.
In conclusion, the present embodiment can reduce the degree of rocket overload reduction, so that the amplitude of propellant shaking is greatly reduced, the degree of mixing of the residual propellant and the pressurized gas in the storage tank can be reduced, the risk of gas entrapment of the propellant in the power transmission pipeline is avoided to a certain extent, the reliability of the secondary start-up of the main engine is improved, and the flight safety of the rocket is improved.
More specifically, in the embodiment, after the main engine sends the preliminary shutdown signal, the main engine executes the thrust adjusting program at a preset time interval, and adjusts the thrust of the main engine to the engine thrust adjusting lower limit (i.e., the first target thrust), so that the aftereffect is significantly reduced when the main engine is normally shutdown, the overload variation amplitude of the rocket body is reduced when the main engine is shutdown, and the oscillation amplitude of the liquid level of the propellant is effectively reduced.
In the embodiment, after the main engine sends the preparatory shutdown signal, the auxiliary power system bottom sinking engine starts to work at preset time intervals, so that the aircraft is ensured to have proper axial overload in the whole flight process, the propellant mixing and air-entrapping time in the shutdown and gliding periods of the main engine of the aircraft is obviously reduced, the safety of the secondary startup of the main engine is effectively improved, and the risk of landing of a vertical take-off and landing demonstration verification rocket is reduced.
The embodiment is suitable for the working condition of multiple times of ignition of the main engine, ensures that the rocket is demonstrated and verified to have larger flight overload in the whole process, solves the problem of propellant management in the rocket flight process, and provides a more suitable flight environment for recoverable key technology verification.
Based on the same inventive concept, the present embodiment provides a rocket propellant sloshing suppressing device as shown in fig. 4, the device comprising:
a detection module 41, configured to detect whether a preliminary shutdown signal of a main engine of the rocket is received;
and the control module 42 is configured to, when the standby shutdown signal of the main engine is received and a time interval between the current time and the time when the standby shutdown signal is received is a first set time interval, control the thrust of the main engine to be reduced to a first target thrust, and control the auxiliary engine of the rocket to provide the rocket with thrust in the flight direction by using a second target thrust. The first set time interval is 1s to 2s.
And the control module 42 is further configured to control the main engine to shut down and the auxiliary engine to continue to provide the rocket with the thrust in the flight direction at the second target thrust when the time interval between the current time and the time when the thrust of the main engine is controlled to be reduced to the first target thrust is a second set time interval. The second set time interval is 3s to 3.5s.
After controlling the main engine to shut down, the detection module 41 is further configured to: detecting whether an ignition signal of a main engine is received;
the control module 42 is further configured to control the auxiliary engine to shut down when the ignition signal of the main engine is received and a time interval between the current time and the time when the ignition signal of the main engine is received is a third set time interval. The third set time interval is 2s to 3s.
A control module 42, comprising:
the control submodule is used for determining a second target thrust according to the propellant density, the flight direction overload, the propellant storage tank radius and the propellant surface tension coefficient of the rocket; and controlling the auxiliary engine to provide the rocket with the thrust in the flight direction at the second target thrust.
The system is also used for determining a first target thrust according to the current total thrust of the rocket, the mass of the rocket body, the flying height and the overload; the thrust of the main engine is controlled to be reduced to the first target thrust.
Based on the same inventive concept, the embodiment provides a rocket, which comprises a main engine and an auxiliary engine; when the main engine is ready to be shut down and/or shut down, the auxiliary engine is controlled to provide thrust in the flight direction to the rocket. The controller of the rocket provided in this embodiment may execute step S11 to step S15.
Since the electronic device described in this embodiment is an electronic device used for implementing the method for processing information in this embodiment, a person skilled in the art can understand the specific implementation manner of the electronic device of this embodiment and various variations thereof based on the method for processing information described in this embodiment, and therefore, how to implement the method in this embodiment by the electronic device is not described in detail here. Electronic devices used by those skilled in the art to implement the method for processing information in the embodiments of the present application are all within the scope of the present application.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present invention is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (7)
1. A rocket propellant sloshing suppression method, said method comprising:
detecting whether a preliminary shutdown signal of a main engine of the rocket is received;
when the preparation shutdown signal of the main engine is received and the time interval between the current time and the time when the preparation shutdown signal is received is a first set time interval, controlling the thrust of the main engine to be reduced to a first target thrust, and controlling an auxiliary engine of the rocket to provide the rocket with a thrust in the flight direction by using a second target thrust; the first set time interval is 1 s-2 s, and is related to the time delay characteristic of the thrust adjustment of the main engine and the time delay characteristic of the control signal transmission loop;
when the time interval between the current time and the time of controlling the thrust of the main engine to be reduced to the first target thrust is a second set time interval, controlling the main engine to be shut down, and controlling the auxiliary engine to continue to provide the rocket with the thrust in the flight direction by using the second target thrust; the second set time interval is 3s to 3.5s, and the second set time interval is related to the time delay characteristic of the thrust adjustment of the main engine and the time delay characteristic of the control signal transmission loop.
2. The method of claim 1, after controlling the main engine to shut down, further comprising:
detecting whether an ignition signal of the main engine is received;
and when the ignition signal of the main engine is received and the time interval between the current moment and the moment of receiving the ignition signal of the main engine is a third set time interval, controlling the auxiliary engine to be shut down.
3. The method of claim 2, wherein the third set time interval is 2s to 3s.
4. The method of claim 1, wherein the controlling the auxiliary engine of the rocket to provide a direction of flight thrust for the rocket at a second target thrust comprises:
determining the second target thrust according to the propellant density, the flight direction overload, the radius of a propellant storage tank and the surface tension coefficient of the propellant of the rocket;
and controlling the auxiliary engine to provide the rocket with the thrust in the flight direction at the second target thrust.
5. The method of claim 1, wherein the controlling the thrust of the main engine to decrease to a first target thrust comprises:
determining the first target thrust according to the current total thrust, rocket body mass, flying height and overload of the rocket;
controlling the thrust of the main engine to be reduced to the first target thrust.
6. A rocket propellant slosh suppression device, said device comprising:
the detection module is used for detecting whether a prepared shutdown signal of a main engine of the rocket is received;
the control module is used for controlling the thrust of the main engine to be reduced to a first target thrust and controlling the auxiliary engine of the rocket to provide the rocket with thrust in the flight direction by using a second target thrust when the preparation shutdown signal of the main engine is received and the time interval between the current time and the time when the preparation shutdown signal is received is a first set time interval; the first set time interval is 1s to 2s; the first set time interval is related to the time delay characteristic of the thrust adjustment of the main engine and the time delay characteristic of the control signal transmission loop;
the control module is also used for controlling the main engine to shut down and controlling the auxiliary engine to continue to provide the rocket with the thrust in the flight direction by using the second target thrust when the time interval between the current moment and the moment of controlling the thrust of the main engine to be reduced to the first target thrust is a second set time interval; the second set time interval is 3s to 3.5s; the second set time interval is associated with a time delay characteristic of the thrust modulation of the main engine and a time delay characteristic of the control signal transmission circuit.
7. A rocket, wherein the rocket comprises a primary engine and a secondary engine; and when the main engine is ready to be shut down and/or shut down, controlling the auxiliary engine to provide thrust in the flight direction for the rocket.
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