A method, system, device and medium for evaluating pressure changes in cryogenic storage tanks

Abstract

The embodiment of the application provides a low-temperature tank pressure change evaluation method, system, device and medium, the method comprises the steps: establishing a propellant utilization system simulation model, obtaining the action state of the engine mixture ratio regulating valve of the rocket in the flight process according to the propellant utilization system simulation model; based on the rocket flight iterative guidance scheme, the flight attitude angle of the rocket at different times is obtained according to the action state of the engine mixture ratio regulating valve and the engine mixture ratio working condition; an attitude simulation model is established, and the control swing angle state of the engine is obtained according to the attitude simulation model and the flight attitude angle; a three-dimensional fluid motion analysis model is established according to the control swing angle state of the engine, and the parameter information of the rocket internal pressure increasing system and the outflow device; the change process of the low-temperature tank pressure is evaluated according to the three-dimensional fluid motion analysis model to obtain an evaluation result. The application improves the accuracy of the evaluation of the low-temperature tank pressure change in the low-temperature rocket flight process.

Description

Technical Field

[0001] This application relates to the aerospace field, and in particular to a method, system, device, and medium for assessing pressure changes in cryogenic tanks. Background Technology

[0002] Currently, the assessment of liquid rocket propellant tank pressurization capacity is achieved through traditional pressurization calculations. This approach uses the rocket's theoretical flight trajectory as input and only considers the impact of the axial overload coefficient on gas heat transfer within the tank during flight. To improve rocket flight performance, cryogenic rockets have begun to employ system-based adjustments to the mixture ratio of remaining propellant within the tank, while simultaneously using iterative guidance technology to enhance orbital accuracy and adaptability. While these two technologies improve rocket flight performance, they also create an additional coupling effect: adjusting the mixture ratio affects changes in engine thrust, which in turn affects the iterative guidance program angle. This process, due to repeated adjustments of the mixture ratio, causes periodic fluctuations in the actual flight program angle. These periodic fluctuations in the rocket body intensify heat transfer between the gas cushion and propellant within the tank, thereby weakening the actual pressurization capacity—an effect that traditional pressurization calculation methods cannot account for. Summary of the Invention

[0003] To address one of the aforementioned technical deficiencies, this application provides a method, system, device, and medium for assessing pressure changes in cryogenic storage tanks.

[0004] According to a first aspect of the embodiments of this application, a method for assessing pressure changes in a cryogenic storage tank is provided, the method comprising:

[0005] A simulation model of the propellant utilization system is established, and the action state of the engine mixture ratio regulating valve during rocket flight is obtained based on the simulation model of the propellant utilization system.

[0006] Based on the rocket flight iterative guidance scheme, the rocket's flight attitude angles at different times are obtained according to the operating state of the engine mixture ratio regulating valve and the engine mixture ratio conditions.

[0007] Establish an attitude simulation model, and obtain the engine control yaw angle state based on the attitude simulation model and the flight attitude angle;

[0008] A three-dimensional fluid motion analysis model is established based on the control swing angle state of the engine and the parameter information of the rocket's internal pressurization system and outflow device;

[0009] The evaluation results were obtained by assessing the pressure change process in the cryogenic tank based on the three-dimensional fluid motion analysis model.

[0010] According to a second aspect of the embodiments of this application, a system for assessing pressure changes in a cryogenic storage tank is provided, the system comprising:

[0011] The propellant utilization system simulation module is used to establish a propellant utilization system simulation model and obtain the action state of the engine mixture ratio regulating valve during rocket flight based on the propellant utilization system simulation model.

[0012] The flight attitude angle acquisition module is used to obtain the rocket's flight attitude angle at different times based on the rocket's flight iterative guidance scheme, according to the action state of the engine mixture ratio regulating valve and the engine mixture ratio conditions.

[0013] The attitude simulation module is used to establish an attitude simulation model and obtain the engine control yaw angle state based on the attitude simulation model and the flight attitude angle.

[0014] The three-dimensional fluid motion analysis model building module is used to build a three-dimensional fluid motion analysis model based on the control swing angle state of the engine and the parameter information of the rocket's internal pressurization system and outflow device.

[0015] The pressure change assessment module is used to assess the pressure change process of the cryogenic tank based on the three-dimensional fluid motion analysis model and obtain the assessment results.

[0016] According to a third aspect of the embodiments of this application, an electronic device is provided, comprising:

[0017] Memory, used to store computer programs;

[0018] A processor is used to execute the computer program to implement the method for evaluating pressure changes in cryogenic tanks as described above.

[0019] According to a fourth aspect of the embodiments of this application, a computer-readable storage medium is provided, wherein computer-executable instructions are stored in the computer-readable storage medium, and when the computer-executable instructions are loaded and executed by a processor, the method for evaluating pressure changes in a cryogenic tank as described above is implemented.

[0020] The cryogenic tank pressure change assessment method provided in this application first obtains the operating state of the engine mixture control valve through a propellant system simulation model. Then, based on the engine mixture conditions, the rocket's flight attitude angles at different times are obtained. Next, the engine's control angle state is obtained using an attitude simulation model based on the flight attitude angles. Finally, a three-dimensional fluid motion analysis model is established, and this model is used to assess the cryogenic tank pressure change process. This process fully considers the periodic fluctuations in the rocket's flight attitude angles during actual flight under different mixture conditions, thereby improving the accuracy of the cryogenic tank pressure change assessment during cryogenic rocket flight. Attached Figure Description

[0021] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0022] Figure 1 This is a flowchart of the method for assessing pressure changes in a cryogenic storage tank as described in Embodiment 1 of this application;

[0023] Figure 2 This is a schematic diagram of the pressurized state of the cryogenic storage tank as described in Embodiment 1 of this application;

[0024] Figure 3 This is a schematic diagram of the pressure change curve of the cryogenic storage tank described in Embodiment 1 of this application;

[0025] Figure 4 This is a schematic diagram of the pressure change assessment system for cryogenic storage tanks described in Embodiment 2 of this application. Detailed Implementation

[0026] To make the technical solutions and advantages of the embodiments of this application clearer, the exemplary embodiments of this application will be described in further detail below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not an exhaustive list of all embodiments. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this application can be combined with each other.

[0027] Example 1

[0028] like Figure 1 As shown in the figure, this embodiment proposes a method for assessing pressure changes in cryogenic storage tanks. The method includes:

[0029] S101. Establish a simulation model of the propellant utilization system, and obtain the action state of the engine mixture ratio regulating valve during rocket flight based on the simulation model of the propellant utilization system.

[0030] Specifically, this embodiment first establishes a propellant utilization system simulation model, which can simulate the propellant utilization state during rocket flight, and then obtain the action state of the engine mixture control valve during rocket flight:

[0031]

[0032] S102. Based on the rocket flight iterative guidance scheme, the rocket's flight attitude angles at different times are obtained according to the operating state of the engine mixture ratio regulating valve and the engine mixture ratio conditions.

[0033] Specifically, in this embodiment, the guidance specialist, based on the iterative guidance scheme, considers the varying thrust of the engine under different mixture ratios when calculating the iterative flight attitude angles (guidance program angles), and calculates the remaining flight time and corresponding flight attitude angles of the rocket at different times. The engine thrust for different mixture ratios is as follows:

[0034]

[0035] Selecting 3 velocity components and , When the two positional components of the direction are used as terminal constraints, the flight attitude angles of the launch vehicle can be simplified to the following form:

[0036]

[0037] in , To ensure that the rocket reaches the predetermined flight attitude angle formed by the velocity vector at the target point, , To satisfy the flight attitude angles with position constraints, the optimal control problem described above can be solved to obtain the desired values. , , , , , The specific value.

[0038] ( )

[0039] )

[0040] in, , , Apparent velocity increment The three components in the guidance coordinate system. When calculating the apparent velocity increment, the influence of the engine's actual thrust on the mixture ratio adjustment of the system needs to be considered.

[0041] S103. Establish an attitude simulation model, and obtain the engine control yaw angle state based on the attitude simulation model and the flight attitude angle.

[0042] Specifically, this embodiment obtains the engine's control angle state through an attitude simulation model and flight attitude angles. In obtaining the engine's control angle state, it is necessary to consider various deviation factors of the rocket during flight, including but not limited to center of mass deviation, engine thrust deviation, thrust line deviation, and separation interference. After obtaining the engine's control angle state, the rocket's center of mass acceleration and attitude angular acceleration at different times can be calculated based on this.

[0043] S104. Establish a three-dimensional fluid motion analysis model based on the control swing angle state of the engine and the parameter information of the rocket's internal pressurization system and outflow device;

[0044] S105. The pressure change process of the cryogenic tank is evaluated based on the three-dimensional fluid motion analysis model to obtain the evaluation results.

[0045] Specifically, in this embodiment, after obtaining the engine's control angle state, a three-dimensional fluid motion analysis model is established based on this control angle state and the parameter information of the rocket's internal pressurization system and outflow device. This three-dimensional fluid motion analysis model integrates multiple aspects such as cryogenic tank motion, propellant sloshing, and gas-liquid heat exchange. Considering the energy changes in the cryogenic tank's air cushions, the model further considers the lateral overload caused by the periodic changes in the rocket's flight attitude angle, and conducts an assessment process for the cryogenic tank pressure changes.

[0046] like Figure 2 As shown, during the assessment of cryogenic tank pressure changes, the main factors affecting the pressurization capacity of the cryogenic tank include: the energy of the gas entering the cryogenic tank through the pressurization system (pressurization gas flow rate and temperature), heat exchange between the gas and the structure, the sloshing of the propellant at the gas-liquid interface caused by external load excitation (center of mass acceleration and attitude angular acceleration), which intensifies the heat exchange between the gas and liquid, and the expansion work done for propellant outflow (propellant outflow flow rate). Therefore, in this embodiment, during the assessment of the cryogenic tank pressure change process using a three-dimensional fluid motion analysis model, the motion state of the propellant at the gas-liquid interface within the cryogenic tank can be obtained first based on the aforementioned center of mass acceleration and attitude angular acceleration. Then, the heat exchange state within the cryogenic tank can be obtained based on the motion state of the propellant at the gas-liquid interface. Finally, the assessment result is obtained by evaluating the cryogenic tank pressure change using a three-dimensional fluid motion analysis model based on the energy of the gas entering the cryogenic tank through the pressurization system, the heat exchange state within the cryogenic tank, and the outflow flow rate of the outflow device. Figure 3The figure shows the pressure change curve of the cryogenic tank during the actual flight of the rocket and the pressure change curve of the cryogenic tank obtained by the method proposed in this embodiment. It can be seen that the pressure change curve obtained by the method proposed in this embodiment is relatively consistent with the pressure change curve during the actual flight.

[0047] The cryogenic tank pressure change assessment method provided in this embodiment first obtains the operating state of the engine mixture control valve through a propellant system simulation model. Then, based on the engine mixture conditions, it obtains the rocket's flight attitude angles at different times. Next, it uses an attitude simulation model to obtain the engine's control angle state based on the flight attitude angles. Finally, it establishes a three-dimensional fluid motion analysis model and uses this model to assess the cryogenic tank pressure change process. This process fully considers the periodic fluctuations in the rocket's flight attitude angles under different mixture conditions during actual flight, thereby improving the accuracy of assessing cryogenic tank pressure changes during cryogenic rocket flight.

[0048] Example 2

[0049] Corresponding to Example 1, this example proposes a system for assessing pressure changes in cryogenic storage tanks, such as... Figure 4 As shown, the system includes:

[0050] The propellant utilization system simulation module is used to establish a propellant utilization system simulation model and obtain the action state of the engine mixture ratio regulating valve during rocket flight based on the propellant utilization system simulation model.

[0051] The flight attitude angle acquisition module is used to obtain the rocket's flight attitude angle at different times based on the rocket's flight iterative guidance scheme, according to the action state of the engine mixture ratio regulating valve and the engine mixture ratio conditions.

[0052] The attitude simulation module is used to establish an attitude simulation model and obtain the engine control yaw angle state based on the attitude simulation model and the flight attitude angle.

[0053] The three-dimensional fluid motion analysis model building module is used to build a three-dimensional fluid motion analysis model based on the control swing angle state of the engine and the parameter information of the rocket's internal pressurization system and outflow device.

[0054] The pressure change assessment module is used to assess the pressure change process of the cryogenic tank based on the three-dimensional fluid motion analysis model and obtain the assessment results.

[0055] The attitude simulation module can be implemented in the attitude control system, while the three-dimensional fluid motion analysis model establishment module and the pressure change evaluation module can be implemented in the power system. The specific working principle and process of this system can be found in Example 1, and will not be repeated here.

[0056] Example 3

[0057] This embodiment proposes an electronic device, including:

[0058] Memory, used to store computer programs;

[0059] A processor is used to execute computer programs to implement the steps of the method for assessing pressure changes in cryogenic tanks as described above.

[0060] Since the embodiments of the electronic equipment section correspond to the embodiments of the cryogenic tank pressure change assessment method section in Embodiment 1, please refer to the description of the embodiments of the electronic equipment section in the cryogenic tank pressure change assessment method section for the embodiments of the electronic equipment section, and will not be repeated in this embodiment.

[0061] Example 4

[0062] This embodiment proposes a computer-readable storage medium storing a computer program. When the computer program is executed by a processor, it implements the steps of the cryogenic tank pressure change assessment method of any of the above embodiments.

[0063] Since the embodiments of the computer-readable storage medium portion correspond to the embodiments of the cryogenic tank pressure change assessment method portion of Embodiment 1, the embodiments of the storage medium portion are described in the description of the embodiments of the cryogenic tank pressure change assessment method portion, and will not be repeated here.

[0064] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of this application can be implemented in various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.

[0065] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can 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, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.

[0066] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.

[0067] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.

[0068] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0069] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.

[0070] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.

Claims

1. A method for assessing pressure changes in a cryogenic storage tank, characterized in that, The method includes: A simulation model of the propellant utilization system is established, and the action state of the engine mixture ratio regulating valve during rocket flight is obtained based on the simulation model of the propellant utilization system. Based on the rocket flight iterative guidance scheme, the rocket's flight attitude angles at different times are obtained according to the operating state of the engine mixture ratio regulating valve and the engine mixture ratio conditions. Based on the iterative guidance scheme, the guidance specialists considered the varying thrust of the engine under different mixture ratios when calculating the iterative flight attitude angles, thus obtaining the rocket's remaining flight time and corresponding flight attitude angles at different times. The engine thrust for different mixture ratios is as follows: Selecting 3 velocity components and , When the two positional components of the direction are used as terminal constraints, the flight attitude angles of the launch vehicle can be simplified to the following form: in , To ensure that the rocket reaches the predetermined flight attitude angle formed by the velocity vector at the target point, , To satisfy the flight attitude angles with position constraints, the optimal control problem described above can be solved to obtain the desired values. , , , , , The specific value; （ ） ） in, , , Apparent velocity increment The three components in the guidance coordinate system; when calculating the apparent velocity increment, the influence of the engine's actual thrust on the system's mixture ratio adjustment needs to be considered; Establish an attitude simulation model, and obtain the engine control yaw angle state based on the attitude simulation model and the flight attitude angle; A three-dimensional fluid motion analysis model is established based on the control swing angle state of the engine and the parameter information of the rocket's internal pressurization system and outflow device; The evaluation results were obtained by assessing the pressure change process in the cryogenic tank based on the three-dimensional fluid motion analysis model.

2. The method according to claim 1, characterized in that, The method further includes: To obtain the deviation factors of the rocket during flight; The engine's control yaw state is obtained based on the attitude simulation model, flight attitude angle, and deviation factors.

3. The method according to claim 1, characterized in that, The deviation factors of the rocket during flight include at least one of the following: center of mass deviation, engine thrust deviation, thrust line deviation, and separation interference.

4. The method according to claim 1, characterized in that, The process of evaluating the pressure change process in the cryogenic tank based on the three-dimensional fluid motion analysis model to obtain the evaluation result includes: The three-dimensional fluid motion analysis model evaluates the changes in the pressure of the cryogenic tank based on the energy of the gas entering the cryogenic tank from the pressurization system, the heat exchange state inside the cryogenic tank, and the outflow rate of the outflow device.

5. The method according to claim 1, characterized in that, The method further includes: The rocket's center of mass acceleration and attitude angular acceleration at different times are obtained based on the engine's control swing angle state. The centroid acceleration and attitude angular acceleration are input into the three-dimensional fluid motion analysis model, and the pressure change process of the cryogenic tank is evaluated based on the three-dimensional fluid motion analysis model to obtain the evaluation results.

6. The method according to claim 5, characterized in that, The process of inputting the centroid acceleration and attitude angular acceleration into the three-dimensional fluid motion analysis model, and evaluating the pressure change process of the cryogenic tank based on the three-dimensional fluid motion analysis model to obtain the evaluation result includes: The three-dimensional fluid motion analysis model obtains the motion state of the propellant near the gas-liquid interface in the cryogenic tank based on the centroid acceleration and attitude angular acceleration. The heat exchange of the gas in the cryogenic tank is obtained based on the motion state of the propellant near the gas-liquid interface in the cryogenic tank. The three-dimensional fluid motion analysis model evaluates the pressure change of the cryogenic tank based on the energy of the gas entering the cryogenic tank from the pressurization system, the heat exchange of the gas in the cryogenic tank, and the outflow rate of the outflow device.

7. A system for assessing pressure changes in a cryogenic storage tank, characterized in that, The system includes: The propellant utilization system simulation module is used to establish a propellant utilization system simulation model and obtain the action state of the engine mixture ratio regulating valve during rocket flight based on the propellant utilization system simulation model. The flight attitude angle acquisition module is used to obtain the rocket's flight attitude angle at different times based on the rocket's flight iterative guidance scheme, according to the action state of the engine mixture ratio regulating valve and the engine mixture ratio conditions. Based on the iterative guidance scheme, the guidance specialists considered the varying thrust of the engine under different mixture ratios when calculating the iterative flight attitude angles, thus obtaining the rocket's remaining flight time and corresponding flight attitude angles at different times. The engine thrust for different mixture ratios is as follows: Selecting 3 velocity components and , When the two positional components of the direction are used as terminal constraints, the flight attitude angles of the launch vehicle can be simplified to the following form: in , To ensure that the rocket reaches the predetermined flight attitude angle formed by the velocity vector at the target point, , To satisfy the flight attitude angles with position constraints, the optimal control problem described above can be solved to obtain the desired values. , , , , , The specific value; （ ） ） in, , , Apparent velocity increment The three components in the guidance coordinate system; when calculating the apparent velocity increment, the influence of the engine's actual thrust on the system's mixture ratio adjustment needs to be considered; The attitude simulation module is used to establish an attitude simulation model and obtain the engine control yaw angle state based on the attitude simulation model and the flight attitude angle. The three-dimensional fluid motion analysis model building module is used to build a three-dimensional fluid motion analysis model based on the control swing angle state of the engine and the parameter information of the rocket's internal pressurization system and outflow device. The pressure change assessment module is used to assess the pressure change process of the cryogenic tank based on the three-dimensional fluid motion analysis model and obtain the assessment results.

8. An electronic device, characterized in that, include: Memory, used to store computer programs; A processor for executing the computer program to implement the method for assessing pressure changes in cryogenic tanks as described in any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer-executable instructions, which, when loaded and executed by a processor, implement the method for assessing pressure changes in cryogenic tanks as described in any one of claims 1 to 6.

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