CN115659508A - Simulation test method and system for thrust adjustment and electronic equipment - Google Patents
Simulation test method and system for thrust adjustment and electronic equipment Download PDFInfo
- Publication number
- CN115659508A CN115659508A CN202211323852.5A CN202211323852A CN115659508A CN 115659508 A CN115659508 A CN 115659508A CN 202211323852 A CN202211323852 A CN 202211323852A CN 115659508 A CN115659508 A CN 115659508A
- Authority
- CN
- China
- Prior art keywords
- simulation
- dynamics
- valve control
- parameters
- control instruction
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention discloses a simulation test method and system for thrust adjustment and electronic equipment. Obtaining a trial binding parameter sent by a simulation measurement and control system and a physical parameter sent by a dynamics simulation system; generating a valve control instruction according to the acquired trial binding parameters and physical parameters, and sending the valve control instruction to a dynamics simulation system; the dynamics simulation system carries out dynamics and thermodynamics simulation on the liquid rocket engine according to the valve control instruction to obtain updated physical parameters; and obtaining an updated valve control instruction according to the trial-run binding parameters and the updated physical parameters, and sending the updated valve control instruction to a dynamics simulation system for performing dynamics and thermodynamics simulation on the liquid rocket engine. Therefore, the test run process of the simulation engine can be quickly and reliably simulated, reference is provided for hot test run, the risk in the process of hot test run and liquid rocket engine development is greatly reduced, the number of hot test run is reduced, and the development cost is reduced.
Description
Technical Field
The invention relates to the technical field of liquid rocket engines, in particular to a simulation test method and system for thrust adjustment and electronic equipment.
Background
The reusable rocket technology is a new direction for the development of the current aerospace industry, only SpaceX companies successfully realize rocket recovery and develop repeated use commercial launching at present, the launching cost is greatly reduced, the liquid rocket engine technology with adjustable thrust is one of key technologies for realizing the attack and the customs of the reusable rocket, and is a gap which is low in cost and cannot be spanned by the reusable rocket for the development of each rocket company.
At present, the development of a liquid rocket engine with adjustable thrust is in a starting and rising stage in China. The development of the liquid rocket engine is closely related to the hot test, and the performance of the engine is improved usually by multiple hot test and continuous correction of engine parameters. The liquid rocket engine is a thermal device with extremely high power density and extremely high energy release speed, and has certain risk in the process of trial run if insufficient development experience exists, and in addition, the liquid rocket engine has higher development cost and long development period due to multiple trial runs.
Therefore, how to reduce the risks in the hot trial and the liquid rocket engine development process is a problem to be solved at present.
Disclosure of Invention
In view of the above problems, the present invention is proposed to provide a simulation test method, system and electronic device for thrust adjustment, which overcome or at least partially solve the above problems, and simulate the engine test run by a fast and reliable simulation means, i.e. simulate the working condition, thrust adjustment and parameter change of the predicted engine in advance before the real ignition hot test, verify the correctness of the engine control system and thrust adjustment algorithm, provide reference for the hot test, and greatly reduce the risk of the hot test and the liquid rocket engine in the development process.
According to a first aspect of the present invention, there is provided a simulation test method for thrust adjustment, which is applied to a simulation test system for thrust adjustment, the simulation test method including:
acquiring a trial binding parameter sent by a simulation measurement and control system and a physical parameter sent by a dynamics simulation system;
generating a valve control instruction according to the acquired trial binding parameters and physical parameters, and sending the valve control instruction to a dynamics simulation system;
the dynamics simulation system carries out dynamics and thermodynamics simulation on the liquid rocket engine according to the valve control instruction to obtain updated physical parameters;
and obtaining an updated valve control instruction according to the trial-run binding parameters and the updated physical parameters, and sending the updated valve control instruction to a dynamics simulation system for performing dynamics and thermodynamics simulation on the liquid rocket engine.
Optionally, before generating a valve control instruction according to the obtained trial run binding parameter and physical parameter, the method further includes:
receiving a starting operation command and an ignition permission command which are sent by the simulation measurement and control system and used for starting the navigation panel;
and receiving a time system signal sent by the simulation measurement and control system, and controlling the actions of the simulation test electromagnetic valve and the initiating explosive device.
Optionally, the simulation test method further includes:
judging whether the numerical value of the physical parameter exceeds a corresponding preset range or not for each updated physical parameter, and if so, calculating the duration time for the numerical value of the physical parameter to exceed the preset range;
and comparing the duration with a corresponding preset threshold, if the duration is greater than the preset threshold, determining that the physical parameter is abnormal, and sending an abnormal signal and an emergency shutdown signal of the physical parameter to the simulation measurement and control system to control the dynamic simulation system to shut down.
Optionally, the dynamics simulation system performs dynamics and thermodynamics simulation on the liquid rocket engine according to the valve control instruction to obtain updated physical parameters, including:
the dynamic simulation system receives and analyzes the valve control instruction from the CAN bus, and performs dynamic and thermodynamic simulation calculation on the liquid rocket engine to obtain updated physical parameters, wherein the physical parameters comprise the pressure of an engine thrust chamber, the flow of the engine and the pressure behind an engine pump.
Optionally, the trial run binding parameters include an initial opening of the regulating valve and an initial value of the engine flow.
Optionally, the valve control instruction includes a methane auxiliary valve opening instruction, an oxygen auxiliary valve opening instruction, and an oxygen main valve opening instruction.
According to a second aspect of the present invention, there is provided a thrust modulation simulation test system comprising: the system comprises an analog measurement and control system, a dynamics simulation system and a central computer which is respectively connected with the analog measurement and control system and the dynamics simulation system;
the dynamic simulation system is used for simulating the dynamic and thermodynamic running processes of the liquid rocket engine, and sends physical parameters required by closed-loop control of thrust adjustment of the liquid rocket engine to the central computer; the simulation measurement and control system is used for generating test run binding parameters and sending the test run binding parameters to the central computer; the central computer is used for generating a valve control instruction according to the trial binding parameters and the physical parameters and sending the valve control instruction to the dynamics simulation system; and the dynamics simulation system performs dynamics and thermodynamics simulation on the liquid rocket engine according to the valve control instruction to obtain updated physical parameters and sends the updated physical parameters to the central computer for generating a new valve control instruction.
Optionally, the simulation test system further comprises a simulation upper computer, and the simulation upper computer is respectively connected with the simulation measurement and control system and the dynamics simulation system and is used for model configuration, test run binding parameter configuration, parameter detection and data recording.
According to a third aspect of the present invention, there is provided an electronic apparatus comprising: the device comprises a memory, a processor and a computer program which is stored on the memory and can run on the processor, wherein the processor realizes the simulation test method for thrust adjustment when executing the computer program.
According to a fourth aspect of the present invention, there is provided a computer-readable storage medium having stored thereon a computer program which, when executed by a processor, implements the aforementioned thrust force adjustment simulation test method.
One or more technical solutions in the embodiments of the present specification have at least the following technical effects:
the simulation test method, the simulation test system and the electronic equipment for thrust adjustment provided by the embodiment of the specification simulate the engine test run process through a quick and reliable simulation means, namely simulate and predict the working condition, the thrust adjustment and the parameter change condition of an engine before the real ignition hot test run, verify the correctness of an engine control system and a thrust adjustment algorithm and provide reference for the hot test run, thereby greatly reducing the risk in the hot test run and the liquid rocket engine development process, effectively reducing the times of the hot test run, reducing the development cost of the liquid rocket engine, and reducing the waste of manpower, material resources, financial resources and the like.
The foregoing description is only an overview of the technical solutions of the present invention, and the embodiments of the present invention are described below in order to make the technical means of the present invention more clearly understood and to make the above and other objects, features, and advantages of the present invention more clearly understandable.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
fig. 1 shows a schematic diagram of an electronic device in an embodiment of the invention.
Fig. 2 shows a flow chart of a simulation test method of thrust adjustment in an embodiment of the invention.
FIG. 3 shows a block schematic diagram of a thrust modulated pilot simulation system in an embodiment of the present invention.
Icon:
100-an electronic device; 10-a simulation test device for thrust adjustment; 20-a memory; 30-a processor; 40-a communication unit.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The reusable rocket technology is a new direction for the development of the current aerospace industry, only SpaceX companies successfully realize rocket recovery and develop repeated use commercial launching at present, the launching cost is greatly reduced, the liquid rocket engine technology with adjustable thrust is one of key technologies for realizing the attack and the customs of the reusable rocket, and is a gap which is low in cost and cannot be spanned by the reusable rocket for the development of each rocket company.
At present, the development of a liquid rocket engine with adjustable thrust is in a starting and rising stage in China. The development of the liquid rocket engine is closely related to the hot test, and the performance of the engine is improved usually by multiple hot test and continuous correction of engine parameters. The liquid rocket engine is a thermal device with extremely high power density and extremely high energy release speed, and has certain risk in the process of trial run if sufficient development experience is not available, and in addition, the liquid rocket engine has higher development cost and long development period due to multiple trial runs.
Based on the research content, the embodiment provides a simulation test method for thrust adjustment, which simulates the test run process of a simulation engine through a quick and reliable simulation means, namely, before the real ignition hot test run, the simulation indicates the working condition, the thrust adjustment and the parameter change condition of the engine, verifies the correctness of an engine control system and a thrust adjustment algorithm, and provides reference for the hot test run, so that the risk in the development process of the hot test run and a liquid rocket engine is greatly reduced, the times of the hot test run are effectively reduced, the development cost of the liquid rocket engine is reduced, and the waste of manpower, material resources, financial resources and the like is reduced.
Referring to fig. 1, fig. 1 is a block diagram of an electronic device 100 according to the present embodiment. As shown in fig. 1, the electronic device may include a simulation test apparatus 10 for thrust adjustment, a memory 20, a processor 30 and a communication unit 40, where the memory 20 stores machine-readable instructions executable by the processor 30, and when the electronic device 100 runs, the processor 30 and the memory 20 communicate with each other through a bus, and the processor 30 executes the machine-readable instructions and executes a simulation test method for thrust adjustment.
The elements of the memory 20, the processor 30 and the communication unit 40 are electrically connected to each other, directly or indirectly, to enable transmission or interaction of signals. For example, the components may be electrically connected to each other via one or more communication buses or signal lines. The thrust force modulated pilot simulator 10 includes at least one software functional module that may be stored in memory 20 in the form of software or firmware (firmware). The processor 30 is configured to execute executable modules (e.g., software functional modules or computer programs included in the thrust modifying simulator trial 10) stored in the memory 20.
The Memory 20 may be, but is not limited to, a Random Access Memory (RAM), a Read Only Memory (ROM), a Programmable Read-Only Memory (PROM), an Erasable Read-Only Memory (EPROM), an electrically Erasable Read-Only Memory (EEPROM), and the like.
In some embodiments, processor 30 is configured to perform one or more of the functions described in this embodiment. In some embodiments, the processor 30 may include one or more processing cores (e.g., a single-core processor (S) or a multi-core processor (S)). Merely by way of example, the Processor 30 may include a Central Processing Unit (CPU), an Application Specific Integrated Circuit (ASIC), an Application Specific Instruction Set Processor (ASIP), a Graphics Processing Unit (GPU), a Physical Processing Unit (PPU), a Digital Signal Processor (DSP), a Field Programmable Gate Array (FPGA), a Programmable Logic Device (PLD), a controller, a microcontroller Unit, a reduced Instruction Set computer (reduced Instruction Set Computing, RISC), a microprocessor, or the like, or any combination thereof.
For ease of illustration, only one processor is depicted in electronic device 100. However, it should be noted that the electronic device 100 in this embodiment may also include multiple processors, and thus steps performed by one processor described in this embodiment may also be performed by multiple processors in combination or individually. For example, if the processor of the server executes steps a and B, it should be understood that steps a and B may also be executed by two different processors together or separately in one processor. For example, the processor performs step a and the second processor performs step B, or the processor and the second processor perform steps a and B together.
In this embodiment, the memory 20 is used for storing programs, and the processor 30 is used for executing the programs after receiving execution instructions. The method defined by the process disclosed in any of the embodiments of the present invention can be applied to the processor 30, or can be implemented by the processor 30.
The communication unit 40 is used to establish a communication connection between the electronic apparatus 100 and another apparatus via a network, and to transmit and receive data via the network.
In some embodiments, the network may be any type of wired or wireless network, or combination thereof. Merely by way of example, the Network may include a wired Network, a Wireless Network, a fiber optic Network, a telecommunications Network, an intranet, the internet, a Local Area Network (LAN), a Wide Area Network (WAN), a Wireless Local Area Network (WLAN), a Metropolitan Area Network (MAN), a Wide Area Network (WAN), a Public Switched Telephone Network (PSTN), a bluetooth Network, a ZigBee Network, a Near Field Communication (NFC) Network, or the like, or any combination thereof.
In the embodiment, the electronic device 100 may be, but is not limited to, a notebook computer, an ultra-mobile Personal computer (UMPC), a netbook, a Personal Digital Assistant (PDA), and other electronic devices, and the embodiment does not limit the specific type of the electronic device.
It will be appreciated that the configuration shown in figure 1 is merely schematic. Electronic device 100 may also have more or fewer components than shown in FIG. 1, or a different configuration than shown in FIG. 1. The components shown in fig. 1 may be implemented in hardware, software, or a combination thereof.
Based on the implementation architecture of fig. 1, the present embodiment provides a simulation test method for thrust adjustment, which is executed by the electronic device 100 shown in fig. 1, and the following describes in detail steps of the simulation test method for thrust adjustment provided in the present embodiment based on a structure diagram of the electronic device 100 shown in fig. 1, and with reference to fig. 2, the simulation test method for thrust adjustment includes steps 101 to 104:
step 101: acquiring a trial run binding parameter sent by a simulation measurement and control system and a physical parameter sent by a dynamics simulation system;
step 102: generating a valve control instruction according to the acquired trial binding parameters and physical parameters, and sending the valve control instruction to a dynamics simulation system;
step 103: the dynamics simulation system carries out dynamics and thermodynamics simulation on the liquid rocket engine according to the valve control instruction to obtain updated physical parameters;
step 104: and obtaining an updated valve control instruction according to the trial-run binding parameters and the updated physical parameters, and sending the updated valve control instruction to a dynamics simulation system for performing dynamics and thermodynamics simulation on the liquid rocket engine.
The simulation test method is applied to a simulation test system for thrust adjustment, and the simulation test system for thrust adjustment comprises a simulation measurement and control system, a dynamic simulation system, a central computer and a simulation upper computer. The central computer is respectively connected with the simulation measurement and control system and the dynamics simulation system. The dynamic simulation system is used for simulating the dynamic and thermodynamic running processes of the liquid rocket engine and sending physical parameters required by the thrust adjustment of the engine to the central computer; the simulation measurement and control system is used for generating initial trial binding parameters, sending the trial binding parameters to the central computer and finishing sending related trial commands and time sequence commands; the central computer is used for performing thrust adjustment control calculation according to the bound trial run binding parameters and physical parameters required by thrust adjustment and sending a valve control instruction to the dynamic simulation system; and the dynamics simulation system performs dynamics and thermodynamics simulation on the liquid rocket engine based on the valve control instruction to obtain new engine physical parameters. The simulation upper computer is used for controlling the starting and the stopping of the simulation test system and monitoring and managing the running state of the simulation test system.
The binding parameters of the test run CAN be directly input into the simulation measurement and control system by a user or written into a file of a specific computer, the file is read by the simulation measurement and control system, and the binding parameters of the test run are sent to the central computer through the CAN bus after the binding parameters of the test run are obtained so as to complete binding of the binding parameters of the test run. The trial run binding parameters to be bound are parameters necessary for the central computer to be used for thrust regulation closed-loop control calculation, and the trial run binding parameters can include: the initial opening of the regulating valve, the initial value of the engine flow and the like.
It should be noted that the simulation measurement and control system may also read the fitting binding parameters from the central computer, compare the read fitting binding parameters with the fitting binding parameters to be bound, and determine whether the parameter binding is successfully performed and whether the binding parameters are correct. If not, the simulation measurement and control system performs parameter binding again.
Optionally, before step 102, the simulation testing method further includes:
receiving a starting operation command and an ignition permission command which are sent by the simulation measurement and control system and used for starting the navigation panel;
and receiving a time system signal sent by the simulation measurement and control system, and controlling the actions of the simulation test electromagnetic valve and the initiating explosive device.
That is to say, the simulation measurement and control system is also used for sending a starting operation command and an ignition allowing command for starting a central computer navigation board to the central computer according to the test run flow and the time sequence after the binding of the test parameters is finished, the central computer is started after receiving the starting operation command, and the central computer is ready for ignition when receiving the ignition allowing command.
And the simulation measurement and control system sends a timing signal for agreeing to start a test run process to the central computer and the dynamics simulation system. And the central computer completes parameter binding, starts the main control software of the navigation board of the central computer after receiving the starting operation command, and starts a waiting system signal after receiving the ignition permission command. And when the central computer receives the timing signal, the central computer starts to sequentially control the actions of the simulation test electromagnetic valve and the initiating explosive device according to the trial run time sequence so as to complete the starting time sequence. The dynamics simulation system starts to respond to a valve control command of the central computer after receiving the timing signal, simulates the dynamics and thermodynamics processes of the engine and simulates the starting operation process of the engine.
In addition, the simulation measurement and control system is also used for displaying the progress of the parameter binding process, whether the binding parameters are correct or not and whether the binding is successful or not, and can display information which can represent the progress of the test run process, such as a starting operation command, an ignition allowing command, whether a time system signal is sent or not, and the time system signal, and the like, and a user can more accurately master and control the test run process based on the information.
In an optional embodiment, the dynamic simulation system performs dynamic and thermodynamic simulation on the liquid rocket engine according to the valve control command to obtain updated physical parameters, specifically including:
the dynamic simulation system receives and analyzes the valve control instruction from the CAN bus, and performs dynamic and thermodynamic simulation calculation on the liquid rocket engine to obtain updated physical parameters. The dynamic simulation system feeds back the updated physical parameters to the central computer through the CAN bus, the central computer calculates new valve control instructions based on the fed-back physical parameters, namely parameters such as thrust chamber pressure, engine flow, engine pump back pressure and the like, so as to adjust the working state of the engine and complete the thrust adjusting process, and the process forms closed-loop semi-physical simulation. In the present embodiment, the valve control command includes a methane auxiliary valve opening command, an oxygen auxiliary valve opening command, and an oxygen main valve opening command.
The central computer also needs to monitor physical parameters of the engine in real time in the test run process, specifically, for each updated physical parameter, whether the value of the physical parameter exceeds a corresponding preset range is judged, and if the value exceeds the corresponding preset range, the duration time that the value of the physical parameter exceeds the preset range is calculated;
and comparing the duration with a corresponding preset threshold, if the duration is greater than the preset threshold, determining that the physical parameter is abnormal, and sending an abnormal signal and an emergency shutdown signal of the physical parameter to the simulation measurement and control system to control the dynamic simulation system to shut down.
The central computer controls the relevant electromagnetic valves according to the shutdown time sequence after the thrust adjustment is completed so as to complete the shutdown time sequence of the engine, and the dynamics simulation system responds to the shutdown time sequence control of the central computer so as to complete the simulation of the shutdown process.
It should be noted that, in this embodiment, the dynamic simulation system may include: the engine dynamic model, the regulating valve servo model, the sensor model, the CAN bus communication model and the like are established in advance before a simulation test. The engine dynamic model comprises a propellant supply circuit dynamic model, a combustion chamber dynamic model, a turbine pump dynamic model, a noise model and the like.
The control valve servo model analyzes a valve control instruction sent by a center computer from a CAN bus, responds to the valve control instruction through a second-order linear system, and adds a dead zone, a zero position, a loop width and the like of a servo system so as to realize the simulation of the real physical characteristics of the control valve servo system.
The sensor model is used for simulating the measuring process and output of a real sensor, simulating the measuring process of the real sensor through a first-order inertia link and adding response delay, and converting relevant physical parameters of an engine into a voltage quantity of 0-5V for simulating an output signal of the real sensor.
The CAN bus communication model is used for communication between the dynamic simulation system and a central computer and between the dynamic simulation system and the simulation measurement and control system, information to be sent is firstly compiled into a data frame format according to a CAN communication protocol when data are sent, the data are sent according to frames, and the data CAN be used after data frames are analyzed according to the CAN communication protocol when the data are received.
The simulation test method for thrust adjustment provided by the embodiment of the specification simulates the test run process of a simulated engine through a quick and reliable simulation means, namely, before the real ignition hot test run, the working condition, the thrust adjustment and the parameter change condition of the engine are simulated and predicted, the correctness of an engine control system and a thrust adjustment algorithm is verified, and reference is provided for the hot test run, so that the risk in the development process of the hot test run and a liquid rocket engine is greatly reduced, the hot test run times are effectively reduced, the development cost of the liquid rocket engine is reduced, and the waste of manpower, material resources, financial resources and the like is reduced.
Based on the same inventive concept, with reference to fig. 3, this embodiment further provides a simulation test system for thrust adjustment, including: the system comprises an analog measurement and control system, a dynamics simulation system and a central computer which is respectively connected with the analog measurement and control system and the dynamics simulation system;
the dynamic simulation system is used for simulating the dynamic and thermodynamic running processes of the liquid rocket engine, and sends physical parameters required by closed-loop control of thrust adjustment of the liquid rocket engine to the central computer; the simulation measurement and control system is used for generating test run binding parameters and sending the test run binding parameters to the central computer; the central computer is used for generating a valve control instruction according to the trial binding parameters and the physical parameters and sending the valve control instruction to the dynamics simulation system; and the dynamics simulation system performs dynamics and thermodynamics simulation on the liquid rocket engine according to the valve control instruction to obtain updated physical parameters and sends the updated physical parameters to the central computer for generating a new valve control instruction.
Optionally, the simulation test system further comprises a simulation upper computer, and the simulation upper computer is respectively connected with the simulation measurement and control system and the dynamics simulation system and is used for model configuration, test run binding parameter configuration, parameter detection and data recording.
The simulation upper computer can modify the simulation test control system and the dynamic simulation system model, configure the functions and parameters of the model, and modify and configure the parameters of the test run binding.
The simulation upper computer can control the simulation test and control system to send a start operation command and an ignition permission command for starting a central computer navigation board according to user requirements, and sends a time system signal for starting a test run to the central computer and the dynamic simulation system.
The simulation upper computer further comprises a display interface, monitors the running state and the test run process of the simulation test control system, and displays the engine parameters and the thrust regulation closed-loop control indexes in real time.
The simulation upper computer can also record data, and store simulation measurement and control system time sequence instructions generated in the simulation process, invention control instructions of the central computer, physical parameters of the engine and the like according to set sampling step length for post data analysis.
In this embodiment, other descriptions about the simulation measurement and control system, the dynamic simulation system, the central computer, and the simulation upper computer have been described in detail in the foregoing, and are not described herein again.
It should be noted that after the central computer completes coding and the simulation measurement and control system and the dynamics simulation system model are established, the systems are integrated and connected, so that the liquid rocket engine thrust adjustment simulation test system can be established, and joint debugging and semi-physical simulation tests can be developed.
In summary, the simulation test system for thrust adjustment provided by the embodiment of the present specification simulates a test run process of a simulated engine through a fast and reliable simulation means, i.e. before a real ignition hot test run, the simulation indicates the working condition, thrust adjustment and parameter change condition of the engine, verifies the correctness of an engine control system and a thrust adjustment algorithm, and provides reference for the hot test run, thereby greatly reducing the risk in the process of hot test run and liquid rocket engine development, effectively reducing the times of hot test run, reducing the development cost of a liquid rocket engine, and reducing the waste of manpower, material resources, financial resources and the like.
It can be clearly understood by those skilled in the art that, for convenience and brevity of description, the specific working process of the simulation test apparatus for thrust adjustment described above may refer to the corresponding process in the foregoing method, and will not be described in detail herein.
On the basis of the above, the present embodiment provides a readable storage medium, on which a computer program is stored, and the computer program is executed by a processor to implement the thrust force adjustment simulation test method according to any one of the foregoing embodiments.
In summary, the present embodiment provides a simulation test method, system and electronic device for thrust adjustment, which can automatically bind and check test parameters, can automatically control a test run process according to a time sequence, simulate working conditions, thrust adjustment and parameter change conditions of an engine in advance before real test run, verify correctness of an engine control system and a thrust adjustment algorithm, provide reference for the hot test run, greatly reduce risks in the process of the hot test run and the liquid rocket engine development, and effectively reduce the number of hot test run times, reduce development cost of the liquid rocket engine, and reduce waste of manpower, material resources, financial resources and the like by using a simulation means, aiming at the problems of high risk, high cost and long development period of the liquid rocket engine thrust adjustment.
As will be clear to those skilled in the art, for convenience and brevity of description, the specific working process of the readable storage medium described above may refer to the corresponding process in the foregoing method, and will not be described in detail herein.
While the invention has been described with reference to specific embodiments, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. A simulation test method for thrust adjustment is characterized by being applied to a simulation test system for thrust adjustment, and comprising the following steps:
acquiring a trial binding parameter sent by a simulation measurement and control system and a physical parameter sent by a dynamics simulation system;
generating a valve control instruction according to the acquired trial binding parameters and physical parameters, and sending the valve control instruction to the dynamics simulation system;
the dynamics simulation system carries out dynamics and thermodynamics simulation on the liquid rocket engine according to the valve control instruction to obtain updated physical parameters;
and obtaining an updated valve control instruction according to the trial-run binding parameters and the updated physical parameters, and sending the updated valve control instruction to the dynamics simulation system for performing dynamics and thermodynamics simulation on the liquid rocket engine.
2. The thrust force adjustment simulation test method according to claim 1, wherein before generating the valve control command according to the acquired trial run binding parameters and physical parameters, the method further comprises:
receiving a starting operation command and an ignition permission command which are sent by the simulation measurement and control system and used for starting a navigation panel;
and receiving a time system signal sent by the simulation measurement and control system, and controlling the actions of the simulation test electromagnetic valve and the initiating explosive device.
3. The thrust force adjustment simulation test method of claim 1, further comprising:
judging whether the numerical value of the physical parameter exceeds a corresponding preset range or not for each updated physical parameter, and if so, calculating the duration time for the numerical value of the physical parameter to exceed the preset range;
and comparing the duration with a corresponding preset threshold, if the duration is greater than the preset threshold, determining that the physical parameter is abnormal, and sending an abnormal signal and an emergency shutdown signal of the physical parameter to the simulation measurement and control system to control the dynamic simulation system to shut down.
4. The thrust modulation simulation test method of claim 1, wherein the dynamics simulation system performs dynamics and thermodynamics simulation on the liquid rocket engine according to the valve control command to obtain updated physical parameters, comprising:
and the dynamics simulation system receives and analyzes the valve control instruction from the CAN bus, and performs dynamic and thermodynamic simulation calculation on the liquid rocket engine to obtain updated physical parameters, wherein the physical parameters comprise engine thrust chamber pressure, engine flow and engine pump back pressure.
5. The thrust force adjustment simulation test method according to claim 1, wherein the trial binding parameters include an initial opening of a regulating valve and an initial value of an engine flow.
6. The method for simulation test of thrust force adjustment according to claim 1, wherein the valve control command includes a methane auxiliary valve opening command, an oxygen auxiliary valve opening command, and an oxygen main valve opening command.
7. A thrust modulated simulation test system, comprising: the system comprises a simulation measurement and control system, a dynamics simulation system and a central computer which is respectively connected with the simulation measurement and control system and the dynamics simulation system;
the dynamic simulation system is used for simulating the dynamic and thermodynamic running processes of the liquid rocket engine, and sends physical parameters required by closed-loop control of thrust regulation of the liquid rocket engine to the central computer; the simulation measurement and control system is used for generating trial run binding parameters and sending the parameters to the central computer; the central computer is used for generating a valve control instruction according to the trial binding parameters and the physical parameters and sending the valve control instruction to the dynamics simulation system; and the dynamics simulation system carries out dynamics and thermodynamics simulation on the liquid rocket engine according to the valve control instruction to obtain updated physical parameters and sends the updated physical parameters to the central computer for generating a new valve control instruction.
8. The thrust-adjusting simulation test system according to claim 7, further comprising a simulation upper computer, wherein the simulation upper computer is connected with the simulation measurement and control system and the dynamics simulation system respectively, and is used for model configuration, trial run binding parameter configuration, parameter detection and data recording.
9. An electronic device, characterized in that the electronic device comprises: memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing the thrust force adjusted simulation test method of any of claims 1-6 when executing the computer program.
10. A computer-readable storage medium, characterized in that a computer program is stored thereon, which program, when being executed by a processor, carries out a simulation test method of thrust adjustment according to any one of claims 1-6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211323852.5A CN115659508A (en) | 2022-10-27 | 2022-10-27 | Simulation test method and system for thrust adjustment and electronic equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211323852.5A CN115659508A (en) | 2022-10-27 | 2022-10-27 | Simulation test method and system for thrust adjustment and electronic equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115659508A true CN115659508A (en) | 2023-01-31 |
Family
ID=84992639
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211323852.5A Pending CN115659508A (en) | 2022-10-27 | 2022-10-27 | Simulation test method and system for thrust adjustment and electronic equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115659508A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116088349A (en) * | 2023-03-07 | 2023-05-09 | 东方空间技术(山东)有限公司 | LSTM-based rocket semi-physical simulation data anomaly evaluation method and decision device |
-
2022
- 2022-10-27 CN CN202211323852.5A patent/CN115659508A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116088349A (en) * | 2023-03-07 | 2023-05-09 | 东方空间技术(山东)有限公司 | LSTM-based rocket semi-physical simulation data anomaly evaluation method and decision device |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20090271169A1 (en) | Training Simulators for Engineering Projects | |
| US8498856B2 (en) | Simulation method, system and program | |
| US20100049486A1 (en) | Systems and Methods for Simulating Plant Operations | |
| CN115659508A (en) | Simulation test method and system for thrust adjustment and electronic equipment | |
| US8954920B2 (en) | Apparatus for developing embedded software and a process for making the same | |
| US8457936B2 (en) | Apparatus and methods for simulating a system steady state devoid of performing full transient operating conditions | |
| Rahmani et al. | Internet-based control of FCU hardware-in-the-loop simulators | |
| US20050102126A1 (en) | Control logic simulation-verification method and simulation-verification personal computer | |
| Miller et al. | 23 Real-Time Simulation of Physical Systems Using Simscape™ | |
| CN202886986U (en) | Verification system of control algorithm for motor | |
| WO2010005724A2 (en) | Systems and methods for automated simulation of a propulsion system and testing of propulsion control systems | |
| CN110837035A (en) | Software and hardware testing system and method for air conditioning system | |
| Wu et al. | Aeroelastic wind-tunnel test for aerodynamic uncertainty model validation | |
| Nanjundaswamy et al. | Development and calibration of on-board-diagnostic strategies using a micro-HiL approach | |
| KR102614431B1 (en) | Integrated simulation apparatus | |
| CN214670127U (en) | Fuel cell control algorithm hardware-in-the-loop test platform | |
| KR101672762B1 (en) | The method for realtime simulation and the realtime simulation apparatus | |
| Pascoal et al. | Estimation of APU failure parameters employing linear regression and neural networks | |
| KR102056812B1 (en) | Test bench system for electronic engine control unit of airplane gas turbin engine and test method using the same | |
| JP2004027930A (en) | Method for evaluating controlling device for vehicle | |
| CN114488842A (en) | Simulation test system and method for electronic speed regulator of diesel engine | |
| Mancini et al. | On checking equivalence of simulation scripts | |
| CN112988533A (en) | Safety protection test system and method | |
| CN112859642B (en) | Semi-physical simulation method and device for engine controller | |
| CN114609924A (en) | Fuel cell control algorithm hardware-in-loop test platform and test method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |