Power measurement and control system and method for liquid carrier rocket

Abstract

The invention provides a power measurement and control system and method for a liquid carrier rocket, and relates to the field. Comprising a to-be-tested real equipment system used for completing a rocket body test; the simulator is used for installing a simulation equipment system, and simulation equipment in the simulation equipment system is in one-to-one correspondence with real equipment in the real equipment system; the control machine is in communication connection with the real equipment system and / or the simulator and is used for issuing a target instruction to the real equipment system and / or the simulator in the rocket body testing process; the front-end machine is in communication connection with the control machine and the simulator and is used for forwarding first feedback information after the simulator executes the target instruction to generate the first feedback information; the monitoring machine is in communication connection with the front-end machine, the real equipment system and the simulator and is used for receiving first feedback information and / or second feedback information in the rocket body testing process and monitoring the first feedback information and / or the second feedback information; the second feedback information is feedback information generated after the real equipment system executes the target instruction.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of industrial digitization, and in particular to a power measurement and control system and method for a liquid carrier rocket. BACKGROUND

[0002] Developing a high-reliability, low-cost, reusable liquid carrier rocket is the trend of future commercial spaceflight. To meet the needs of rapid transportation, convenient disassembly, multiple testing, and repeated launch of liquid rockets, the corresponding liquid rocket power measurement and control equipment should also have the function of adapting to various launch tasks. In order to ensure the safety of the liquid rocket power measurement and control equipment in use, it is usually necessary to test the liquid carrier rocket power measurement and control system, and after passing the test, it is put into use. In related technologies, the liquid carrier rocket power measurement and control system test needs to be put into a real machine, which is prone to the problem of low test efficiency. SUMMARY

[0003] The present application provides a power measurement and control system and method for a liquid carrier rocket, which solves the problem of low test efficiency in related technologies.

[0004] In a first aspect, the present application provides a power measurement and control system for a liquid carrier rocket, the system comprising:

[0005] a real device system to be tested, for completing a rocket body test;

[0006] a simulator for installing a simulation device system, the simulation devices in the simulation device system corresponding one-to-one to the real devices in the real device system;

[0007] a control machine in communication connection with the real device system and / or the simulator, for issuing a target instruction to the real device system and / or the simulator during the rocket body test;

[0008] a front-end machine in communication connection with the control machine and the simulator, for forwarding first feedback information after the simulator executes the target instruction to generate the first feedback information;

[0009] a monitoring machine in communication connection with the front-end machine, the real device system, and the simulator, respectively, for receiving and monitoring first feedback information and / or second feedback information during the rocket body test, the second feedback information being feedback information generated after the real device system executes the target instruction.

[0010] Optionally, the real device system comprises an on-board subsystem and a ground subsystem, the on-board subsystem comprises an on-board sensor and an on-board valve, the ground subsystem comprises a recovery device, a gas source, a filling gas adjusting valve, a relay combination, a ground valve, a ground sensor, the simulation device system comprises a simulated on-board subsystem and a simulated ground subsystem.

[0011] Optionally, the rocket body test comprises at least a power control internal test, a power control and filling gas coordination test, a rocket body factory test and a rocket body assembly test, the power control internal test comprises a first communication test, the power control and filling gas coordination test comprises a second communication test, the rocket body factory test comprises a third communication test, and the rocket body assembly test comprises a fourth communication test.

[0012] Optionally, after sequentially passing through the power control internal test, the power control and filling gas coordination test, the rocket body factory test and the rocket body assembly test, it is determined that the power control system test passes the rocket body test.

[0013] Optionally, during the first communication test, the control machine is configured to sequentially issue the target instruction to the simulated on-board subsystem and the simulated ground subsystem in the simulator.

[0014] The front-end machine is configured to forward the first feedback information to the control machine and the monitoring machine, respectively.

[0015] After the first feedback information passes the first communication test, the control machine is further configured to issue a launch instruction to the simulator according to a launch process, the launch process being a real launch process of the liquid carrier rocket.

[0016] Optionally, during the second communication test, the control machine is configured to sequentially issue the target instruction to the ground subsystem in the real device system and the simulated on-board subsystem in the simulator.

[0017] The front-end machine is configured to forward the first feedback information and / or the second feedback information to the control machine and the monitoring machine, respectively.

[0018] After the first feedback information and / or the second feedback information pass the second communication test, the control machine is further configured to issue a launch instruction to the real device system and / or the simulator according to a launch process, the launch process being a real launch process of the liquid carrier rocket.

[0019] Optionally, during the third communication test, the control machine is configured to sequentially issue the target instruction to the on-board subsystem in the real device system and the simulated ground subsystem in the simulator.

[0020] The front-end machine is configured to forward the first feedback information and / or the second feedback information to the control machine and the monitoring machine, respectively.

[0021] After the first feedback information and / or the second feedback information pass the third communication test, the control machine is further configured to issue a launch instruction to the real device system and / or the simulator according to a launch process, the launch process being a real launch process of the liquid carrier rocket.

[0022] Optionally, during the fourth communication test, the control machine is configured to issue a target instruction to the on-board subsystem and the ground subsystem in the real device system in sequence.

[0023] The front-end machine is configured to forward the second feedback information to the control machine and the monitoring machine, respectively.

[0024] After the second feedback information passes the fourth communication test, the control machine is further configured to issue a launch instruction to the real device system according to a launch process, the launch process being a real launch process of the liquid carrier rocket.

[0025] Optionally, the control machine comprises a main control machine and a backup control machine, and the front-end machine comprises a main front-end machine and a backup front-end machine.

[0026] In a second aspect, the present application further provides a dynamic power control method for a liquid carrier rocket, which is applied to the system as described in the first aspect, and the method comprises:

[0027] Obtaining first feedback information and / or second feedback information.

[0028] Determining whether the liquid carrier rocket passes the rocket body test according to the first feedback information and / or the second feedback information.

[0029] In a third aspect, the present application further provides an electronic device, which comprises:

[0030] A processor;

[0031] A memory for storing processor-executable instructions;

[0032] The processor is configured to execute the instructions to implement the method provided in the second aspect of the present application.

[0033] In a fourth aspect, the present application further provides a computer-readable storage medium, when the instructions in the readable storage medium are executed by the processor of an electronic device, the electronic device is enabled to execute the method provided in the second aspect of the present application.

[0034] In a fifth aspect, the present application further provides a computer program product comprising a computer program which, when executed by a processor, performs the method according to the second aspect of the present application.

[0035] The present application provides a power measurement and control system for a liquid carrier rocket, the system comprising: a real device system to be tested, used to complete a rocket body test; a simulator, used to install a simulated device system, simulated devices in the simulated device system corresponding one-to-one to real devices in the real device system; a control machine in communication connection with the real device system and / or the simulator, used to issue a target instruction to the real device system and / or the simulator during the rocket body test; a front-end machine in communication connection with the control machine and the simulator, used to forward first feedback information after the simulator executes the target instruction to generate the first feedback information; a monitoring machine in communication connection with the front-end machine, the real device system and the simulator respectively, used to receive and monitor first feedback information and / or second feedback information during the rocket body test, the second feedback information being feedback information generated after the real device system executes the target instruction. In this way, since the simulator can simulate the real device system, it is possible to generate first feedback information and / or second feedback information with equivalent effects through the simulator in the case that part of the real devices are missing or cannot be accessed, and then after observing the first feedback information and / or the second feedback information on the monitoring machine, it is possible to determine whether the rocket body test is passed, to realize separate full-range coverage testing and to improve testing efficiency. BRIEF DESCRIPTION OF DRAWINGS

[0036] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor.

[0037] Figure 1 A conceptual diagram of a power measurement and control system for a liquid carrier rocket is provided for the embodiments of the present application;

[0038] Figure 2 A conceptual diagram of power measurement and control internal testing is provided for the embodiments of the present application;

[0039] Figure 3 A conceptual diagram of rocket body assembly testing is provided for the embodiments of the present application;

[0040] Figure 4 A flowchart of a power measurement and control method for a liquid carrier rocket is provided for the embodiments of the present application;

[0041] Figure 5 A structural block diagram of an electronic device is provided for an embodiment of the present application. DETAILED DESCRIPTION

[0042] Hereinafter, embodiments of the present disclosure will be described with reference to the accompanying drawings. It is to be understood, however, that the description is merely exemplary and is not intended to limit the scope of the present disclosure.

[0043] Developing a high-reliability, low-cost, reusable liquid carrier rocket is the trend of future commercial spaceflight. In order to meet the needs of rapid transportation, convenient disassembly, multiple tests, and repeated launches of liquid rockets, the corresponding liquid rocket power measurement and control equipment should also have the function of adapting to various launch tasks. In order to ensure the safety of the liquid rocket power measurement and control equipment in use, the liquid carrier rocket power measurement and control system usually needs to be tested, and after passing the test, it is put into use. In the related art, the liquid carrier rocket power measurement and control system test needs to be put into real machine, which is easy to have the problem of low test efficiency.

[0044] To this end, an embodiment of the present application proposes a power measurement and control system suitable for various launch tasks of liquid carrier rockets based on the development needs of power measurement and control equipment, and at the same time to meet the short frequency and fast characteristics of future commercial rockets. The system comprises: a real device system to be tested for completing rocket body testing; a simulator for installing a simulation device system, the simulation devices in the simulation device system correspond one-to-one to the real devices in the real device system; a control machine in communication connection with the real device system and / or the simulator for issuing target instructions to the real device system and / or the simulator during the rocket body testing; a front-end machine in communication connection with the control machine and the simulator for forwarding first feedback information after the simulator executes the target instructions to generate the first feedback information; a monitoring machine in communication connection with the front-end machine, the real device system, and the simulator respectively for receiving first feedback information and / or second feedback information and monitoring during the rocket body testing, the second feedback information being feedback information generated after the real device system executes the target instructions. In this way, since the simulator can simulate the real device system, it can generate first feedback information and / or second feedback information with the same effect through the simulator in the case of partial real device absence or inability to access, and then after observing the first feedback information and / or second feedback information on the monitoring machine, it can determine whether the rocket body testing is passed, realize separate full-range coverage testing, and improve test efficiency.

[0045] In addition, in the embodiment of the present application, the systems of the liquid carrier rocket are all integrated in the same place, and on the basis of reducing the number of simultaneous test products, the integrity of the control system matching is still guaranteed.

[0046] The technical solutions of the embodiments of the present application and how the technical solutions solve the above technical problems will be described in detail below with specific embodiments. The following specific embodiments can be combined with each other, and the same or similar concepts or processes can not be described again in some embodiments. The embodiments of the present application will be described below with reference to the drawings.

[0047] Figure 1 A conceptual diagram of a power measurement and control system for a liquid carrier rocket is provided in an embodiment of the present application. As shown in the figure, Figure 1 The power measurement and control system for a liquid carrier rocket provided in the embodiment of the present application includes a real device system, a simulator, a control machine, a front-end machine, and a monitoring machine.

[0048] In the embodiment of the present application, the real device system includes related devices of the liquid carrier rocket to be tested. For example, in the real device system, an on-board subsystem and a ground subsystem are included, the on-board subsystem includes on-board sensors and on-board valves, and the ground subsystem includes a retrieval device, an air source, a filling air supply regulating valve, a relay combination, a ground valve, and a ground sensor. The real device system can be used to complete rocket body testing and put into use after completing rocket body testing.

[0049] In the embodiment of the present application, the simulator can be used to install a simulated device system in a software installation manner, and the simulated devices in the simulated device system in the simulator one-to-one correspond to the real devices in the real device system. The simulated on-board subsystem can be a digital twin of the on-board subsystem in the real device system, and the simulated ground subsystem can be a digital twin of the ground subsystem in the real device system, or the digital processing of the real device system is realized in other digital simulation manners. For example, when the real device system includes the above-mentioned devices, the simulated on-board subsystem and the simulated ground subsystem can be included in the simulated device system accordingly. The simulated on-board subsystem can include simulated on-board sensors and simulated on-board valves, and the simulated ground subsystem can include a simulated retrieval device, a simulated air source, a simulated filling air supply regulating valve, a simulated relay combination, a simulated ground valve, and a simulated ground sensor.

[0050] In the embodiment of the present application, the simulator can be one electronic device or multiple electronic devices cooperating with each other. The electronic device can be a server, such as a standalone physical server, a server cluster composed of multiple servers, and a cloud server capable of cloud computing.

[0051] In the embodiment of the present application, a control machine is further included in communication connection with the real device system and / or the simulator, for issuing a target instruction to the real device system and / or the simulator during the process of the missile body test. The target instruction can be any test instruction preset in advance and sent in sequence, or a certain test instruction manually specified and sent. The target instruction can include at least one test instruction for completing the missile body test.

[0052] In the embodiment of the present application, a front-end machine is further included in communication connection with the control machine and the simulator, for forwarding first feedback information generated by the simulator after executing the target instruction. The front-end machine can forward the first feedback information to the control machine, or to a monitoring machine mentioned below. The first feedback information is information generated by the simulator after receiving and executing the target instruction, for example, feedback information of "execution success" sent after executing a certain target instruction.

[0053] In the embodiment of the present application, a monitoring machine is further included in communication connection with the front-end machine, the real device system and the simulator, for receiving and monitoring the first feedback information and / or second feedback information during the process of the missile body test. The second feedback information is feedback information generated by the real device system after executing the target instruction.

[0054] In the embodiment of the present application, the front-end machine can also be in communication connection with the real device in the real device system, so as to forward the second feedback information from the real device to the monitoring machine. The monitoring machine can directly receive the first feedback information and / or the second feedback information, or receive the first feedback information and / or the second feedback information through the forwarding of the front-end machine. In this way, since the simulator can simulate the real device system, the first feedback information and / or the second feedback information with the same effect can be generated by the simulator in the case that part of the real device is missing or cannot be accessed, so that whether the missile body test is passed can be determined after observing the first feedback information and / or the second feedback information on the monitoring machine, the full-range coverage test is realized alone, and the test efficiency is improved.

[0055] In the embodiment of the present application, in order to further improve the data security in the test process, the control machine and the front-end machine can adopt a master-backup policy, that is, the control machine can include a master control machine and a backup control machine, and the front-end machine can include a master front-end machine and a backup front-end machine. In the normal test process, the master control machine and / or the master front-end machine can be used for work, and when the master control machine and / or the master front-end machine appear problems and are down, the backup control machine and / or the backup front-end machine can be correspondingly used for test.

[0056] In the embodiment of the present application, the missile body test at least includes a power measurement and control internal test, a power measurement and control and filling gas coordination test, a missile body factory test and a missile body assembly test. After sequentially passing through the power measurement and control internal test, the power measurement and control and filling gas coordination test, the missile body factory test and the missile body assembly test, it is determined that the power measurement and control system passes the missile body test. The object of the power measurement and control internal test can be the power measurement and control part in the liquid carrier rocket, and the object of the power measurement and control and filling gas coordination test can be the power measurement and control function and the filling gas function in the liquid carrier rocket.

[0057] In the embodiment of the present application, in the internal of each test process, it can also be divided into a communication test and a function test. The communication test can be used to test whether the communication link between the test equipment (such as a real device system and a control machine) is normal. After the communication test passes, the function test can be performed on the test equipment. The function test can be used to test whether the set function of the test equipment can normally run in the real launch process. For example, the power measurement and control internal test includes a first communication test, the power measurement and control and filling gas coordination test includes a second communication test, the missile body factory test includes a third communication test, and the missile body assembly test includes a fourth communication test.

[0058] In the embodiment of the present application, Figure 2 The conceptual diagram of the power measurement and control internal test provided in the embodiment of the present application is shown in FIG. 1. Figure 2 As shown in FIG. 1, in the power measurement and control internal test, the test equipment in the real device system can include a control machine, a monitoring machine, a front-end machine, a relay combination, a front-end equivalent host computer (a display mechanism corresponding to the front-end machine). The test equipment in the analog device system (i.e., the digital simulation of the device in the real device system, hereinafter represented by the simulator) can include an analog on-missile measurement and control system, an analog retrieval device, an analog gas source, an analog filling gas regulating valve, an analog ground valve and an analog ground sensor. Figure 2

[0059] In the embodiment of the present application, Figure 2 The front-end machine 1 and the front-end machine 2 in FIG. 1 are main and backup settings, that is, a main front-end machine and a backup front-end machine, respectively. Correspondingly, the control machine 1 and the control machine 2 are also main and backup settings. The related settings in the following Figure 3 Figure 2

[0060] In the embodiment of the present application, in the process of the first communication test in the power measurement and control internal test, the control machine can be used to sequentially issue the target instruction to the analog on-missile subsystem and the analog ground subsystem in the simulator. The front-end machine is used to forward the first feedback information to the control machine and the monitoring machine, respectively. The specific test process can be referred to the following examples. It should be understood that the examples are not limited.​​​

[0061] For example, the control machine first sends a target instruction (e.g., an on-off control instruction). Specifically, the control machine sends an on-off control instruction to the front-end machine, the front-end machine drives the relay combination to output an on-off signal to the simulator. The simulator sends first feedback information (e.g., an on-off feedback signal) to the front-end host computer, simulates the valve switching state of the real device system in response to the target instruction, and collects the on-off control signal state of the relay combination to send to the front-end machine, which sends the on-off state to the control machine and the monitoring machine.

[0062] In the embodiment of the present application, the target instruction can also be an analog control instruction, and correspondingly, the first feedback information is an analog output card state. Specifically, the control machine sends an analog control instruction. The front-end machine is sent an analog control instruction, the front-end machine drives the analog output card, the front-end host computer receives the analog output card state, simulates the state of the real regulating valve, collects the analog output card signal state to send to the front-end machine, and the front-end machine sends the analog state to the control machine and the monitoring machine.

[0063] In addition, other devices in the real device system can also send instructions, for example, the front-end host computer sends an on-off control instruction to the front-end machine, the front-end machine drives the relay combination to output an on-off signal to the simulator, collects the on-off control signal state of the relay combination to send to the front-end machine, and the front-end machine sends the on-off state to the control machine and the monitoring machine.

[0064] In the embodiment of the present application, the front-end host computer can also send an analog control instruction to the front-end machine, the front-end machine drives the analog output card, collects the analog output card signal state to send to the front-end machine, and the front-end machine sends the analog state to the control machine and the monitoring machine.

[0065] In the embodiment of the present application, the target instruction can also be a control signal type, such as an arrow valve, a recovery device, and a gas source control signal. For example, the control machine sends an arrow valve, a recovery device, and a gas source control signal, and uses an equivalent device as a control instruction execution terminal. The equivalent device transmits a control instruction execution feedback signal to the control machine and the monitoring machine.

[0066] After the first feedback information is tested through the first communication, the control machine is further configured to send a launch instruction to the simulator according to a launch process. The launch process is a real launch process of the liquid carrier rocket. That is, according to the real power system launch process, the test field control process is tested, and the simulator is used instead of the real product to debug the rationality of the internal process of the power measurement and control.

[0067] In the embodiment of the present application, the gaseous supply is generally fixed at the launch site. In the actual development process, the gaseous supply needs to be matched with the power measurement and control before the rocket enters the site, and the matching test (i.e., the second communication test) and the launch process test need to be performed. Therefore, the real product of the simulated rocket measurement and control system is not tested, and the real product of the power measurement and control and the gaseous supply system is tested. In the coordinated test of the power measurement and control and the gaseous supply, the tested equipment in the real equipment system can include: a control machine, a monitoring machine, a front-end machine, a relay combination, a ground sensor, a ground valve, a gaseous supply regulating valve, a withdrawal device, and a gas source. The tested equipment in the simulated equipment system (i.e., the digital simulation of the equipment in the real equipment system, which is represented by the simulator hereinafter) can include: a simulated rocket measurement and control system.

[0068] In the embodiment of the present application, in the process of the second communication test in the coordinated test of the power measurement and control and the gaseous supply, the control machine is used to sequentially issue target instructions to the ground subsystem in the real equipment system and the simulated rocket measurement and control system in the simulator. The front-end machine is used to forward the first feedback information and / or the second feedback information to the control machine and the monitoring machine, respectively. The specific test process can be referred to the following examples. It should be understood that the examples are not limited.

[0069] For example, according to the real gaseous supply test, the control machine performs matching test on the gas source, the withdrawal device, the gaseous supply regulating valve, the ground valve, and the sensor, respectively. The gas source, the withdrawal device, the front-end machine, and the sensor send the collected signals (i.e., the second feedback information) to the control machine and the monitoring machine. The test can be divided into single-point live-wire test without gas, system live-wire test without gas, single-point live-wire test with gas, and system live-wire test with gas.

[0070] After the first feedback information and / or the second feedback information pass the second communication test, the control machine is further used to issue launch instructions to the real equipment system and / or the simulator according to the launch process. The launch process is the real launch process of the liquid carrier rocket. That is, according to the real launch process of the power system, the test site control process test is performed, the launch process test is performed using the real test product, and the launch task is completed.

[0071] In the embodiment of the present application, the arrow body needs to be tested before delivery in the assembly stage, and the power measurement and control and the matching test of the arrow measurement and control need to be carried out without the participation of the pre-filling gas, and the launch process test (i.e., the arrow body delivery test described above) needs to be carried out, so the real product of the simulated filling gas does not participate in the test. In the arrow body delivery test, the participating devices in the real device system can include: a control machine, a monitoring machine, a front-end machine, a relay combination, an arrow measurement and control system. The participating devices in the simulated device system (i.e., the digital simulation of the devices in the real device system, hereinafter represented by the simulator) can include: a simulated ground sensor, a simulated ground valve, a simulated filling gas regulating valve, a simulated withdrawal device, and a simulated gas source.

[0072] In the embodiment of the present application, in the process of the third communication test in the arrow body delivery test, the control machine is used to sequentially issue target instructions to the arrow subsystem in the real device system and the simulated ground subsystem in the simulator; and the front-end machine is used to forward the first feedback information and / or the second feedback information to the control machine and the monitoring machine, respectively. The specific test process can be referred to the following examples. It should be understood that the examples are not limiting.

[0073] According to the real arrow-controlled single machine and system, the control machine controls the arrow valve in the arrow measurement and control system, and the arrow sensor sends the collected data (i.e., the second feedback information) to the control machine and the monitoring machine, realizing the matching test of the power measurement and control and the arrow measurement and control.

[0074] After the first feedback information and / or the second feedback information pass the third communication test, the control machine is further used to issue launch instructions to the real device system and / or the simulator according to the launch process, and the launch process is the real launch process of the liquid carrier rocket. That is, according to the real power system launch process, the test field control process test is carried out, the launch process test is carried out using the real participating product, and the launch task is completed.

[0075] In the embodiment of the present application, after the arrow body enters, the filling gas system is also ready, and all products are tested in a real state, and the arrow body assembly test is completed. Figure 3 The conceptual diagram of the arrow body assembly test provided in the embodiment of the present application is shown in FIG. 1. Figure 3 As shown in FIG. 1, in the arrow body assembly test, the participating devices in the real device system can include: an arrow subsystem and a ground subsystem.

[0076] In this embodiment of the invention, during the fourth communication test in the rocket body assembly test, the control unit is used to sequentially issue target commands to the onboard subsystem and the ground subsystem in the actual equipment system; the front-end unit is used to forward the second feedback information to the control unit and the monitoring unit respectively. The specific test procedure can be referred to in the following example. It should be understood that the example is not a limitation.

[0077] Power measurement and control matching test with onboard measurement and control, and propellant and gas supply matching test (fourth communication test): Based on the actual onboard controlled units and systems, and the actual propellant and gas supply units and equipment, the control unit controls the onboard valves, ground valves, propellant and gas supply regulating valves, retraction device, and gas source, and issues target commands. Onboard sensors send the collected onboard data (second feedback information) to the control unit and monitoring unit, while ground sensors, front-end units, retraction device, and gas source send the collected ground equipment data to the control unit and monitoring unit, realizing the matching test between the power measurement and control system and the actual launch system.

[0078] After the second feedback information passes the fourth communication test, the control unit is also used to issue launch commands to the actual equipment system according to the launch procedure, which is the actual launch procedure of the liquid-fueled launch vehicle. That is, based on the actual propulsion system launch procedure, the test range control procedure is tested, the actual test product is used to test the launch procedure, and the launch mission is completed.

[0079] The propulsion measurement and control system for liquid-fueled launch vehicles provided by this invention allows each device to perform independent self-testing, improving the reliability of each individual device. Internal matching tests can be performed separately within the propulsion measurement and control system, increasing system-wide testing efficiency. Each part of the propulsion measurement and control system and the propellant supply system can be matched and debugged separately, improving inter-system testing efficiency. Matching tests between the propulsion measurement and control system and the onboard measurement and control system can simulate the entire process without requiring actual testing of the propellant supply system. Furthermore, even if some products cannot be tested in their actual state, matching and process tests can still be performed without affecting the test flow, improving testing efficiency. In addition, with all major propulsion measurement and control system products complete, the actual launch process can be simulated without requiring actual testing of other system products. Finally, current rocket launches require all control systems to be jointly tested and debugged in the same location; this method reduces the number of products tested simultaneously without affecting the integrity of the control system matching.

[0080] In this embodiment of the invention, a power measurement and control method for a liquid-fueled launch vehicle is also provided, applied to the system described above. For example... Figure 4 As shown, the method includes steps 410 and 420.

[0081] Step 410: Obtain the first feedback information and / or the second feedback information;

[0082] Step 420, judging whether the liquid carrier rocket passes the rocket body test according to the first feedback information and / or the second feedback information. The rocket body test at least includes a power measurement and control internal test, a power measurement and control and filling gas coordination test, a rocket body factory test and a rocket body assembly test. After sequentially passing the power measurement and control internal test, the power measurement and control and filling gas coordination test, the rocket body factory test and the rocket body assembly test, it is determined that the power measurement and control system test passes the rocket body test.

[0083] Figure 5 A structural block diagram of an electronic device is provided for implementation of the present application. As shown in Figure 5 The electronic device provided by the embodiment of the present application includes a processor 510 and a memory 520, and the memory is used to store instructions executable by the processor; wherein the processor is configured to execute the instructions to implement the power measurement and control method for the liquid carrier rocket as shown in Figure 4

[0084] In the exemplary embodiment, the electronic device can be implemented by one or more application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), controllers, microcontrollers, microprocessors or other electronic elements for executing the above method.

[0085] In the exemplary embodiment, a non-transitory computer readable storage medium including instructions, such as a memory including instructions, is also provided, and the above method can be executed by the processor of the device to complete the above method. For example, the non-transitory computer readable storage medium can be a ROM, a random access memory (RAM), a CD-ROM, a magnetic tape, a floppy disk and an optical data storage device, etc. The non-transitory computer readable storage medium, when the instructions in the storage medium are executed by the processor of the electronic device, enables the electronic device to execute the power measurement and control method for the liquid carrier rocket as shown in Figure 4

[0086] The present application also provides a computer program product, including a computer program, which, when executed by a processor, implements the power measurement and control method for the liquid carrier rocket as shown in Figure 4

[0087] ​​​In the above description, detailed explanation is not given to the technical details such as the configuration of each layer. However, it should be understood by those skilled in the art that the layer, region, etc. of the desired shape can be formed by various technical means. In addition, a method different from the above-described method can be devised by those skilled in the art in order to form the same structure. In addition, although each embodiment is described above separately, this does not mean that the measures in each embodiment cannot be used advantageously in combination.

[0088] Although preferred embodiments of the application have been described herein, it will be apparent to those skilled in the art that various modifications and changes can be made to the embodiments without departing from the spirit and scope of the application. Accordingly, it is intended that all such modifications and changes be included within the scope of the application as set forth in the following claims and their equivalents.

[0089] Obviously, numerous modifications and variations of the present application are possible in light of the above teachings. It is therefore to be understood that within the scope of the appended claims and their equivalents, the application can be practiced otherwise than as specifically described.

Claims

1. A power measurement and control system for a liquid-fueled launch vehicle, characterized in that, The system includes: The actual equipment system to be tested is used to complete the rocket body test; A simulator is used to install a simulated device system, wherein the simulated devices in the simulated device system correspond one-to-one with the real devices in the real device system. A control unit that is communicatively connected to the real equipment system and / or the simulator is used to issue target commands to the real equipment system and / or the simulator during the rocket body test. A front-end unit that is communicatively connected to the control unit and the simulator is used to forward the first feedback information after the simulator executes the target instruction and generates the first feedback information; A monitoring unit that is communicatively connected to the front-end machine, the real equipment system, and the simulator is used to receive and monitor first feedback information and / or second feedback information during the rocket body test. The second feedback information is the feedback information generated after the real equipment system executes the target instruction.

2. The system according to claim 1, characterized in that, The real equipment system includes an on-rocket subsystem and a ground subsystem. The on-rocket subsystem includes on-rocket sensors and on-rocket valves. The ground subsystem includes a retrieval device, a gas source, a gas supply regulating valve, a relay assembly, ground valves, and ground sensors. The simulated equipment system includes a simulated on-rocket subsystem and a simulated ground subsystem.

3. The system according to claim 2, characterized in that, The rocket body test includes at least the internal power measurement and control test, the power measurement and control and propellant supply coordination test, the rocket body factory test, and the rocket body assembly test. The internal power measurement and control test includes a first communication test, the power measurement and control and propellant supply coordination test includes a second communication test, the rocket body factory test includes a third communication test, and the rocket body assembly test includes a fourth communication test.

4. The system according to claim 3, characterized in that, After passing the internal power measurement and control test, the power measurement and control and gas supply coordination test, the rocket body factory test, and the rocket body assembly test in sequence, it is determined that the power measurement and control system has passed the rocket body test.

5. The system according to claim 4, characterized in that, During the first communication test, the control unit is used to sequentially send the target command to the simulated rocket subsystem and the simulated ground subsystem in the simulator; The front-end unit is used to forward the first feedback information to the control unit and the monitoring unit respectively; After the first feedback information passes the first communication test, the control unit is also used to issue a launch command to the simulator according to the launch procedure, which is the actual launch procedure of the liquid-fueled launch vehicle.

6. The system according to claim 4, characterized in that, During the second communication test, the control unit is used to sequentially send target commands to the ground subsystem in the real equipment system and the simulated rocket subsystem in the simulator; The front-end unit is used to forward the first feedback information and / or the second feedback information to the control unit and the monitoring unit, respectively. After the first feedback information and / or the second feedback information pass the second communication test, the control unit is also used to issue launch commands to the real equipment system and / or the simulator according to the launch procedure, wherein the launch procedure is the real launch procedure of the liquid launch vehicle.

7. The system according to claim 4, characterized in that, During the third communication test, the control unit is used to sequentially issue target commands to the onboard subsystem in the real equipment system and the simulated ground subsystem in the simulator; The front-end unit is used to forward the first feedback information and / or the second feedback information to the control unit and the monitoring unit, respectively. After the first feedback information and / or the second feedback information pass the third communication test, the control unit is also used to issue launch commands to the real equipment system and / or the simulator according to the launch procedure, wherein the launch procedure is the real launch procedure of the liquid launch vehicle.

8. The system according to claim 4, characterized in that, During the fourth communication test, the control unit is used to sequentially issue target commands to the onboard subsystem and the ground subsystem in the actual equipment system; The front-end unit is used to forward the second feedback information to the control unit and the monitoring unit respectively; After the second feedback information passes the fourth communication test, the control unit is also used to issue a launch command to the actual equipment system according to the launch procedure, which is the actual launch procedure of the liquid launch vehicle.

9. The system according to claim 1, characterized in that, The control unit includes a main control unit and a backup control unit, and the front-end unit includes a main front-end unit and a backup front-end unit.

10. A power measurement and control method for a liquid-fueled launch vehicle, applied to the system as described in any one of claims 1-9, characterized in that, The method includes: Obtain first and / or second feedback information; Based on the first feedback information and / or the second feedback information, determine whether the liquid-fueled launch vehicle has passed the rocket body test.

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