Rocket containment release control method and device

Abstract

The invention relates to a rocket contained release control method and device. The method comprises the steps that engine working state information sent by a plurality of controllers in a target rocket is obtained; wherein the target rocket comprises a plurality of first-stage engines, each first-stage engine is associated with a sensor and a controller, and the controller is used for obtaining sensor data collected by the sensor after the corresponding first-stage engine is started and generating working state information of the corresponding first-stage engine based on the sensor data; and on the basis of the working state information, generating a control signal indicating whether the target rocket is restrained to be released or not. Therefore, whether each primary engine is in a normal working state or not can be judged in time only by acquiring the working state information of each primary engine, so that the calculation pressure of a flight control computer can be reduced, the processing timeliness can be improved, the deployment of cables on a rocket can be reduced, and the weight of the cables on the rocket can be reduced.

Description

Technical Field

[0001] The present disclosure relates to the field of rocket launching technology, and in particular to a rocket restraining and releasing control method and device. Background Art

[0002] For liquid rockets with multiple engines working in parallel, it is necessary to confirm that all engines have started normally before the rocket is allowed to fly away from the launch pad. A commonly used method is to first secure the rocket with the launch pad's restraint release device. After all the rocket's engines have started normally, the restraint release device releases the rocket. If some of the engines start abnormally, the restraint release device remains in the restrained state, and the rocket is still fixed on the launch pad, and an emergency shutdown of the entire rocket is performed.

[0003] However, for reusable liquid rockets, one stage usually has 9 or more engines in parallel. In related technologies, the flight control computer usually needs to monitor the working status of the rocket body and multiple engines at the same time, so that the flight control computer collects and processes the sensor data of multiple engines at the same time, which puts high demands on the data processing capability of the flight control computer. At the same time, a large number of sensor cables are connected from the bottom of the rocket to the flight control computer at the top, which will make the cables on the rocket very complicated and increase the weight of the cables. Summary of the invention

[0004] The present invention provides a rocket restraint release control method and device.

[0005] According to a first aspect of the present disclosure, a rocket restraint release control method is provided, the method comprising:

[0006] Acquire engine operating status information respectively sent by multiple controllers in a target rocket; wherein the target rocket includes multiple first-stage engines, each first-stage engine is associated with a sensor and a controller, and the controller is used to acquire sensor data collected by the sensor after the corresponding first-stage engine is started, and generate the operating status information of the corresponding first-stage engine based on the sensor data;

[0007] Based on the working status information, a control signal is generated to determine whether the target rocket is to be released.

[0008] According to a second aspect of the present disclosure, a rocket restraint release control device is provided, the device comprising:

[0009] An engine working state information acquisition module is used to acquire engine working state information respectively sent by multiple controllers in a target rocket; wherein the target rocket includes multiple first-stage engines, each first-stage engine is associated with a sensor and a controller, and the controller is used to acquire sensor data collected by the sensor after the corresponding first-stage engine is started, and generate the working state information of the corresponding first-stage engine based on the sensor data;

[0010] A control signal generating module is used to generate a control signal for determining whether the target rocket is to be released based on the working status information.

[0011] According to a third aspect of the present disclosure, an electronic device is provided, which includes a memory and a processor, wherein a computer program is stored in the memory, and when the processor executes the program, the method described above is implemented.

[0012] According to a fourth aspect of the present disclosure, a computer-readable storage medium is provided, on which a computer program is stored, and when the program is executed by a processor, the above method of the present disclosure is implemented.

[0013] According to a fifth aspect of the present disclosure, a computer program product is provided, including a computer program, wherein the computer program implements the above method of the present disclosure when executed by a processor.

[0014] The rocket restraint release control method and device provided by the disclosed embodiment obtains the engine working status information respectively sent by multiple controllers in the target rocket, and generates a control signal of whether the target rocket restraint is released based on the working status information. Since the target rocket includes multiple first-stage engines, each first-stage engine is associated with a sensor and a controller, and the controller is used to obtain the sensor data collected by the sensor after the corresponding first-stage engine is started, and generate the working status information of the corresponding first-stage engine based on the sensor data. In this way, it is only necessary to obtain the working status information of each first-stage engine, and it is possible to timely determine whether each first-stage engine is in a normal working state, thereby reducing the calculation pressure of the flight control computer and improving the timeliness of processing, and it is also possible to reduce the deployment of cables on the rocket and reduce the weight of the cables on the rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Further details, features and advantages of the present disclosure are disclosed in the following description of exemplary embodiments in conjunction with the accompanying drawings, in which:

[0016] Figure 1 A schematic diagram of a rocket restraint release control provided for an exemplary embodiment of the present disclosure;

[0017] Figure 2 A flowchart of a rocket restraint release control method provided for an exemplary embodiment of the present disclosure;

[0018] Figure 3 A schematic block diagram of the functional modules of a rocket restraint and release control device provided for an exemplary embodiment of the present disclosure;

[0019] Figure 4 A structural block diagram of an electronic device provided for an exemplary embodiment of the present disclosure;

[0020] Figure 5 A structural block diagram of a computer system provided for an exemplary embodiment of the present disclosure. DETAILED DESCRIPTION

[0021] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although certain embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as being limited to the embodiments described herein, which are instead provided for a more thorough and complete understanding of the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not intended to limit the scope of protection of the present disclosure.

[0022] It should be understood that the various steps described in the method embodiments of the present disclosure may be performed in different orders and / or in parallel. In addition, the method embodiments may include additional steps and / or omit the steps shown. The scope of the present disclosure is not limited in this respect.

[0023] The term "including" and its variations used in this document are open inclusions, that is, "including but not limited to". The term "based on" means "based at least in part on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one other embodiment"; the term "some embodiments" means "at least some embodiments". Relevant definitions of other terms will be given in the description below. It should be noted that the concepts of "first", "second", etc. mentioned in this disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or interdependence of the functions performed by these devices, modules or units.

[0024] It should be noted that the modifications of "one" and "plurality" mentioned in the present disclosure are illustrative rather than restrictive, and those skilled in the art should understand that unless otherwise clearly indicated in the context, it should be understood as "one or more".

[0025] The names of the messages or information exchanged between multiple devices in the embodiments of the present disclosure are only used for illustrative purposes and are not used to limit the scope of these messages or information.

[0026] It is understandable that before using the technical solutions disclosed in the embodiments of the present disclosure, the types, scope of use, usage scenarios, etc. of the personal information involved in the present disclosure should be informed to the user and the user's authorization should be obtained in an appropriate manner in accordance with relevant laws and regulations.

[0027] For example, in response to receiving an active request from a user, a prompt message is sent to the user to clearly prompt the user that the operation requested to be performed will require obtaining and using the user's personal information. Thus, the user can autonomously choose whether to provide personal information to software or hardware such as an electronic device, application, server, or storage medium that performs the operation of the technical solution of the present disclosure according to the prompt message.

[0028] As an optional but non-limiting implementation, in response to receiving an active request from the user, the method of sending a prompt message to the user may be, for example, a pop-up window, in which the prompt message may be presented in text. In addition, the pop-up window may also carry a selection control for the user to choose "agree" or "disagree" to provide personal information to the electronic device. It is understandable that the above notification and the process of obtaining user authorization are only illustrative and do not constitute a limitation on the implementation of the present disclosure. Other methods that meet relevant laws and regulations may also be applied to the implementation of the present disclosure.

[0029] In the related art, the flight control computer receives the data collected by the sensors on each engine, processes the data uniformly through the flight control computer, and determines the working status of each engine. Since the flight control computer needs to receive the data collected by the sensors on each engine, the flight control computer needs to be configured with sufficient physical interfaces. Through these physical interfaces, a large number of sensor cables are connected from the bottom of the rocket to the flight control computer at the top, which makes the cables on the rocket very complicated and increases the weight of the cables. At the same time, since the flight control computer needs to process a large amount of data, it will bring a large data processing pressure to the flight control computer, so that the flight control computer cannot judge whether each engine is working normally in time, making the processing efficiency of the related art low.

[0030] Therefore, in order to solve the technical problems existing in the above-mentioned related technologies, Figure 1 As shown, Figure 1 A schematic diagram of a rocket restraint release control provided in an embodiment of the present disclosure. In the embodiment provided in the present disclosure, each first-stage engine is equipped with an independent control system and measurement system, and a dedicated engine controller is used to complete the control, measurement and working status monitoring of the engine.

[0031] In the embodiment, taking a liquid rocket with nine engines in parallel in one stage as an example, the controller of each engine collects the sensor data of the engine, analyzes and processes the data, and determines the current working state of the engine. The nine engine controllers of one stage serve as nodes of the control system bus on the rocket, and can send the working state of all engines to the flight control computer in real time. The flight control computer determines the working state of the engine and other systems on the rocket, and sends the working state of the system on the rocket to the restraint release system on the ground in real time.

[0032] In the embodiment, by adopting a distributed architecture to realize the judgment of the working status of multiple engines, the number of external interfaces of the flight control computer can be reduced, physical interfaces and data processing capacity resources can be saved, and the system complexity can be reduced. It is possible to realize the local acquisition and data processing of engine sensor data, obtain the working status of the current engine, and thus reduce the risk of interference in long-distance transmission of sensor data, and also improve the reliability of engine status judgment. In this way, the flight control computer only needs to obtain the working status information of each first-stage engine, and can timely judge whether each first-stage engine is in a normal working state, thereby reducing the calculation pressure of the flight control computer and improving the timeliness of processing, and can also reduce the deployment of cables on the rocket and reduce the weight of cables on the rocket.

[0033] like Figure 1 As shown, in the embodiment, 9 first-stage engines are deployed on the rocket as an example for explanation. The working status of the 9 first-stage engines is determined by their respective engine controllers, and the working status of all rocket engines is summarized by the flight control computer. If the release condition is met, the instruction is sent to the restraint release system through the digital interface, and the unlocking device is activated by the restraint release system. If the release condition is not met, the on-rocket control system automatically executes instructions such as emergency shutdown, and the restraint release system remains locked. Among them, if all first-stage engines are in normal working condition, it can be determined that the release condition is met. Otherwise, it is determined that the release condition is not met.

[0034] In the embodiment, by configuring a multifunctional controller for each engine, the sensor data collected by the engine can be processed nearby, and the engine working state can be judged according to a predetermined criterion, and the judgment result is sent to the flight control computer in real time through the arrow control bus. The scheme that can be adopted in the embodiment uses the engine state information in a simple digital form, for example, 00 indicates that the engine is in a normal working state, and 11 indicates that the engine is in an abnormal working state. Since the embodiment can summarize the working state of each engine through the flight control computer, and then obtain the judgment result, the judgment result can be sent by the flight control computer to the restraint release system through the arrow-to-ground interface, so that the embodiment can achieve a simple structure and high reliability restraint release judgment.

[0035] Based on the above embodiments, the present disclosure also provides a rocket restraint release control method, such as Figure 2 As shown, the method may include the following steps:

[0036] In step S210, engine operating status information respectively sent by multiple controllers in the target rocket is obtained.

[0037] Among them, the target rocket includes multiple first-stage engines, each of which is associated with a sensor and a controller. The controller is used to obtain sensor data collected by the sensor after the corresponding first-stage engine is started, and generate working status information of the corresponding first-stage engine based on the sensor data.

[0038] In the embodiment, combined Figure 1 As shown, each engine is provided with a sensor and a controller. After each engine is started, the controller can obtain the sensor data collected by the sensor, and compare the sensor data with the preset data to determine whether the engine is in a normal working state. For example, the sensor data can be compared with a preset threshold value to determine whether the working state of the engine is normal, and then the engine working state information is generated and sent to the flight control computer, so that the flight control computer can obtain the engine working state information sent by each controller, and the engine working state information may include information indicating normal working state or abnormal working state.

[0039] Specifically, based on the sensor data, it is determined whether the corresponding first-stage engine is in a normal working state. When the corresponding first-stage engine is in a normal working state, working state information including a normal mark is generated. Alternatively, when the corresponding first-stage engine is in an abnormal working state, working state information including an abnormal mark is generated.

[0040] For example, the working status information of the normal mark can be 00, and the working status information of the abnormal mark can be 11, etc., and the embodiment is not limited thereto. In this way, when the flight control computer receives the working status information sent by each controller, it can promptly determine whether each first-stage engine is in a normal working state.

[0041] In step S220, based on the working status information, a control signal is generated to determine whether the target rocket is to be restrained and released.

[0042] In the embodiment, it is necessary that all the first-stage engines are in normal working state to ensure that the rocket can be launched normally. Therefore, according to the working state information sent by each controller, if it is determined that each first-stage engine is in normal working state, a control signal for the rocket's containment release can be generated so that the target rocket can be launched normally. If at least one of all the first-stage engines is in an abnormal working state, in order to avoid the failure of the rocket launch, an emergency shutdown instruction can be generated, and the emergency shutdown instruction can be sent to each first-stage engine to perform an emergency shutdown on the target rocket, and a control signal for prohibiting the release of the rocket's containment is generated, so that the containment release system remains in a locked state.

[0043] The rocket restraint release control method provided by the disclosed embodiment obtains the engine working state information respectively sent by multiple controllers in the target rocket, and generates a control signal for whether the target rocket restraint is released based on the working state information. Since the target rocket includes multiple first-stage engines, each first-stage engine is associated with a sensor and a controller, and the controller is used to obtain the sensor data collected by the sensor after the corresponding first-stage engine is started, and generate the working state information of the corresponding first-stage engine based on the sensor data. In this way, it is only necessary to obtain the working state information of each first-stage engine, and it is possible to timely determine whether each first-stage engine is in a normal working state, thereby reducing the calculation pressure of the flight control computer and improving the timeliness of processing, and it is also possible to reduce the deployment of cables on the rocket and reduce the weight of the cables on the rocket.

[0044] Based on the above embodiment, when generating a control signal for determining whether to release the target rocket, the above step S220 may further include the following steps:

[0045] Step S221, based on the working status information, determine whether multiple first-stage engines in the target rocket are in normal working condition.

[0046] In the embodiment, if it is determined that all the first-stage engines are in normal working condition, it can be determined that the first-stage engines in the target rocket are in normal working condition. Otherwise, if at least one first-stage engine is in abnormal working condition, it can be determined that the first-stage engines in the target rocket are not all in normal working condition.

[0047] Step S222, when multiple first-stage engines in the target rocket are in normal working condition, a control signal for restraining and releasing the rocket is generated.

[0048] In the embodiment, if the multiple first-stage engines in the target rocket are in normal working state, a control signal for rocket restraint and release is generated, and the control signal for rocket restraint and release is sent to the restraint and release system, so that the restraint and release system restrains and releases the target rocket at a corresponding time based on the received control signal for rocket restraint and release.

[0049] In the embodiment, when multiple first-stage engines in the target rocket are not all in normal working state, the target rocket is shut down in an emergency, and a control signal for prohibiting the release of the rocket is generated. The control signal for prohibiting the release of the rocket is sent to the restraint release system, so that the restraint release system maintains the restraint state of the target rocket when receiving the control signal for prohibiting the release of the rocket.

[0050] Based on the above embodiments, in the embodiments provided by the present disclosure, when the controller determines that the corresponding first-stage engine is in a non-working state based on the sensor data, that is, when the engine is in an abnormal working state, the target fault type of the first-stage engine can be obtained according to the sensor data. And the target fault execution script corresponding to the target fault type is obtained, and the target fault execution script is executed to solve the abnormality of the first-stage engine. Among them, different fault types can be pre-configured with fault execution scripts, and these fault execution scripts are executed to solve the faults of the fault type.

[0051] In an embodiment, when executing the target fault execution script, the working state information sent by the target controller to the flight control computer may carry a fault processing identifier, and the fault processing identifier indicates that the fault of the corresponding first-stage engine is handled normally. When the flight control computer detects the working state information carrying the fault processing identifier, even if the working state information is an abnormal working state, the flight control computer may be in a waiting state, for example, it may wait for a target duration. If the normal working state information sent by the target controller is received within the target duration, it means that the first-stage engine has completed the fault processing by executing the target fault script. Otherwise, if the normal working state information sent by the target controller is not received within the target duration, it can be determined that the first-stage engine is still in an abnormal working state, and the flight control computer can generate a control signal for whether the target rocket is restrained and released based on the engine working state information sent by each controller.

[0052] Specifically, in the embodiment, the sensor can also classify the working state of the corresponding first-level engine into multiple levels according to the sensor data. Among them, different levels indicate the degree of normal working state of the first-level engine, such as abnormal, poor, general, good and excellent. Abnormal means that the engine cannot work normally, poor means that the engine can just work normally, but is on the edge of normal or abnormal, and is prone to failure; general means that the engine is in a normal working state; good means that the working state of the engine is relatively good; excellent means that the working state of the engine is very excellent and is not prone to problems.

[0053] In an embodiment, the above-mentioned different levels may correspond to different weights or scores respectively. If at least one of the multiple first-stage engines is in an abnormal working state, indicating that the target rocket is not suitable for launch, the target rocket may be shut down immediately and a control signal for restraining the rocket and prohibiting its release may be generated.

[0054] In an embodiment, if there is no engine in abnormal working condition among the multiple first-stage engines, a weighted sum can be performed according to the levels corresponding to each first-stage engine to obtain the total score of the target rocket. In this way, the current working status of the target rocket can be determined based on the total score, which makes it convenient for the staff to judge whether it is necessary to continue to launch the target rocket based on the total score.

[0055] For example, when all or most of the first-stage engines have a poor grade, the total score of the target rocket is low, indicating that the target rocket may have a risk of failure at any time. At this time, the staff can choose to stop the rocket launch in order to overhaul the rocket and improve the success rate of the rocket launch.

[0056] In the embodiment, if the total score of the target rocket is low, the rocket may be easily affected by atmospheric resistance, earth gravity or shock during launch, causing the engine on the edge of normal or abnormal working state to fail. Therefore, the success rate of rocket launch can be improved by terminating the launch and overhauling the rocket.

[0057] In the case of dividing each functional module according to each function, an embodiment of the present disclosure provides a rocket restraint and release control device, which can be a server, a terminal, or a chip applied to a server. Figure 3 A schematic block diagram of the functional modules of a rocket restraint release control device provided by an exemplary embodiment of the present disclosure. Figure 3 As shown, the rocket restraint release control device includes:

[0058] The engine working state information acquisition module 10 is used to acquire the engine working state information respectively sent by multiple controllers in the target rocket; wherein the target rocket includes multiple first-stage engines, each first-stage engine is associated with a sensor and a controller, and the controller is used to acquire the sensor data collected by the sensor after the corresponding first-stage engine is started, and generate the working state information of the corresponding first-stage engine based on the sensor data;

[0059] The control signal generating module 20 is used to generate a control signal for determining whether the target rocket is to be restrained or not based on the working status information.

[0060] In another embodiment provided by the present disclosure, the engine operating status information acquisition module is specifically used to:

[0061] Based on the sensor data, determining whether the corresponding first-stage engine is in a normal working state;

[0062] When the corresponding first-stage engine is in a normal working state, generating working state information including a normal identification;

[0063] When the corresponding first-stage engine is in an abnormal working state, working state information including an abnormality indicator is generated.

[0064] In another embodiment provided by the present disclosure, the control signal generating module is specifically used to:

[0065] Based on the working status information, determining whether multiple first-stage engines in the target rocket are all in a normal working state;

[0066] When the multiple first-stage engines in the target rocket are in normal working condition, a control signal for the rocket restraint and release is generated.

[0067] In another embodiment provided by the present disclosure, the device further includes:

[0068] The control signal sending module is used to send the control signal of the rocket restraint and release to the restraint and release system, so that the restraint and release system restrains and releases the target rocket at a corresponding time based on the received control signal of the rocket restraint and release.

[0069] In another embodiment provided by the present disclosure, the device further includes:

[0070] The first control module is used to perform an emergency shutdown of the target rocket and generate a control signal for prohibiting the release of the rocket when the multiple first-stage engines in the target rocket are not all in a normal working state.

[0071] In another embodiment provided by the present disclosure, the device further includes:

[0072] The second control module is used to send the control signal of the rocket restraint and release prohibition to the restraint and release system, so that the restraint and release system maintains the restraint state of the target rocket when receiving the control signal of the rocket restraint and release prohibition.

[0073] The rocket restraint release control device provided by the disclosed embodiment obtains the engine working state information respectively sent by multiple controllers in the target rocket, and generates a control signal for whether the target rocket restraint is released based on the working state information. Since the target rocket includes multiple first-stage engines, each first-stage engine is associated with a sensor and a controller, and the controller is used to obtain the sensor data collected by the sensor after the corresponding first-stage engine is started, and generate the working state information of the corresponding first-stage engine based on the sensor data. In this way, it is only necessary to obtain the working state information of each first-stage engine, and it is possible to timely determine whether each first-stage engine is in a normal working state, thereby reducing the calculation pressure of the flight control computer and improving the timeliness of processing, and it is also possible to reduce the deployment of cables on the rocket and reduce the weight of the cables on the rocket.

[0074] An embodiment of the present disclosure also provides an electronic device, comprising: at least one processor; and a memory for storing instructions executable by the at least one processor; wherein the at least one processor is configured to execute the instructions to implement the above method disclosed in the embodiment of the present disclosure.

[0075] Figure 4 The structure diagram of an electronic device provided by an exemplary embodiment of the present disclosure is shown in FIG. Figure 4 As shown, the electronic device 1800 includes at least one processor 1801 and a memory 1802 coupled to the processor 1801 , and the processor 1801 can execute corresponding steps in the above method disclosed in the embodiment of the present disclosure.

[0076] The processor 1801 may also be referred to as a central processing unit (CPU), which may be an integrated circuit chip having signal processing capabilities. Each step in the method disclosed in the embodiment of the present disclosure may be completed by an integrated logic circuit of hardware in the processor 1801 or by instructions in the form of software. The processor 1801 may be a general-purpose processor, a digital signal processor (DSP), an ASIC (Application Specific Integrated Circuit), a field-programmable gate array (FPGA) or other programmable logic devices, discrete gates or transistor logic devices, discrete hardware components. A general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc. The steps of the method disclosed in the embodiment of the present disclosure may be directly embodied as being executed by a hardware decoding processor, or may be executed by a combination of hardware and software modules in a decoding processor. The software module may be located in a memory 1802, such as a random access memory, a flash memory, a read-only memory, a programmable read-only memory or an electrically erasable programmable memory, a register, or other mature storage media in the art. The processor 1801 reads the information in the memory 1802 and completes the steps of the method in combination with its hardware.

[0077] In addition, when various operations / processes according to the present disclosure are implemented by software and / or firmware, they can be transmitted from a storage medium or a network to a computer system having a dedicated hardware structure, such as Figure 5 The computer system 1900 shown is installed with the programs constituting the software. When the various programs are installed, the computer system can perform various functions, including the functions described above. Figure 5 A structural block diagram of a computer system provided for an exemplary embodiment of the present disclosure.

[0078] Computer system 1900 is intended to represent various forms of digital electronic computer devices, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. Electronic devices can also represent various forms of mobile devices, such as personal digital processing, cellular phones, smart phones, wearable devices, and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely examples and are not intended to limit the implementation of the present disclosure described and / or claimed herein.

[0079] like Figure 5 As shown, the computer system 1900 includes a computing unit 1901, which can perform various appropriate actions and processes according to a computer program stored in a read-only memory (ROM) 1902 or a computer program loaded from a storage unit 1908 to a random access memory (RAM) 1903. In the RAM 1903, various programs and data required for the operation of the computer system 1900 can also be stored. The computing unit 1901, the ROM 1902, and the RAM 1903 are connected to each other via a bus 1904. An input / output (I / O) interface 1905 is also connected to the bus 1904.

[0080] A plurality of components in the computer system 1900 are connected to the I / O interface 1905, including: an input unit 1906, an output unit 1907, a storage unit 1908, and a communication unit 1909. The input unit 1906 may be any type of device capable of inputting information to the computer system 1900, and the input unit 1906 may receive input digital or character information, and generate key signal inputs related to user settings and / or function control of the electronic device. The output unit 1907 may be any type of device capable of presenting information, and may include, but is not limited to, a display, a speaker, a video / audio output terminal, a vibrator, and / or a printer. The storage unit 1908 may include, but is not limited to, a disk, an optical disk. The communication unit 1909 allows the computer system 1900 to exchange information / data with other devices over a network such as the Internet, and may include, but is not limited to, a modem, a network card, an infrared communication device, a wireless communication transceiver, and / or a chipset, such as a Bluetooth™ device, a WiFi device, a WiMax device, a cellular communication device, and / or the like.

[0081] The computing unit 1901 may be a variety of general and / or special processing components with processing and computing capabilities. Some examples of the computing unit 1901 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various dedicated artificial intelligence (AI) computing chips, various computing units running machine learning model algorithms, digital signal processors (DSPs), and any appropriate processors, controllers, microcontrollers, etc. The computing unit 1901 performs the various methods and processes described above. For example, in some embodiments, the above methods disclosed in the embodiments of the present disclosure may be implemented as a computer software program, which is tangibly included in a machine-readable medium, such as a storage unit 1908. In some embodiments, part or all of the computer program may be loaded and / or installed on an electronic device via ROM 1902 and / or communication unit 1909. In some embodiments, the computing unit 1901 may be configured to perform the above methods disclosed in the embodiments of the present disclosure in any other appropriate manner (e.g., by means of firmware).

[0082] The embodiment of the present disclosure further provides a computer-readable storage medium, wherein when instructions in the computer-readable storage medium are executed by a processor of an electronic device, the electronic device is enabled to execute the above method disclosed in the embodiment of the present disclosure.

[0083] The computer-readable storage medium in the disclosed embodiments may be a tangible medium that may contain or store a program for use by or in conjunction with an instruction execution system, device, or equipment. The computer-readable storage medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, devices, or equipment, or any suitable combination of the foregoing. More specifically, the computer-readable storage medium may include an electrical connection based on one or more lines, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0084] The computer-readable medium may be included in the electronic device, or may exist independently without being incorporated into the electronic device.

[0085] The embodiments of the present disclosure further provide a computer program product, including a computer program, wherein when the computer program is executed by a processor, the above method disclosed in the embodiments of the present disclosure is implemented.

[0086] In embodiments of the present disclosure, computer program codes for performing the operations of the present disclosure may be written in one or more programming languages ​​or combinations thereof, including but not limited to object-oriented programming languages, such as Java, Smalltalk, C++, and conventional procedural programming languages, such as "C" language or similar programming languages. The program code may be executed entirely on a user's computer, partially on a user's computer, as an independent software package, partially on a user's computer, partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer via any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computer.

[0087] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present disclosure. In this regard, each square box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the module, the program segment or a part of the code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some implementations as replacements, the functions marked in the square box can also occur in a sequence different from that marked in the accompanying drawings. For example, two square boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each square box in the block diagram and / or flow chart, and the combination of the square boxes in the block diagram and / or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0088] The modules, components or units involved in the embodiments described in the present disclosure may be implemented by software or hardware, wherein the names of the modules, components or units do not, in some cases, limit the modules, components or units themselves.

[0089] The functions described above herein may be performed at least in part by one or more hardware logic components. For example, without limitation, exemplary hardware logic components that may be used include: field programmable gate arrays (FPGAs), application specific integrated circuits (ASICs), application specific standard products (ASSPs), systems on chip (SOCs), complex programmable logic devices (CPLDs), and the like.

[0090] The above descriptions are only some embodiments of the present disclosure and an explanation of the technical principles used. Those skilled in the art should understand that the scope of disclosure involved in the present disclosure is not limited to the technical solutions formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above disclosed concept. For example, a technical solution formed by replacing the above features with the technical features with similar functions disclosed in the present disclosure (but not limited to).

[0091] Although some specific embodiments of the present disclosure have been described in detail by way of example, it should be understood by those skilled in the art that the above examples are for illustration only and are not intended to limit the scope of the present disclosure. It should be understood by those skilled in the art that the above embodiments may be modified without departing from the scope and spirit of the present disclosure. The scope of the present disclosure is defined by the appended claims.

Claims

1. A rocket restraint release control method, characterized in that: The method comprises: Acquire engine operating status information respectively sent by multiple controllers in a target rocket; wherein the target rocket includes multiple first-stage engines, each first-stage engine is associated with a sensor and a controller, and the controller is used to acquire sensor data collected by the sensor after the corresponding first-stage engine is started, and generate the operating status information of the corresponding first-stage engine based on the sensor data; Based on the working status information, a control signal is generated to determine whether the target rocket is to be released.

2. The method according to claim 1, characterized in that The generating the working state information of the corresponding first-stage engine based on the sensor data comprises: Based on the sensor data, determining whether the corresponding first-stage engine is in a normal working state; When the corresponding first-stage engine is in a normal working state, generating working state information including a normal identification; Alternatively, when the corresponding first-stage engine is in an abnormal working state, working state information including an abnormality indicator is generated.

3. The method according to claim 1, characterized in that The generating of the control signal of whether the target rocket is to be restrained and released comprises: Based on the working status information, determining whether multiple first-stage engines in the target rocket are in a normal working state; When the multiple first-stage engines in the target rocket are in normal working condition, a control signal for the rocket restraint and release is generated.

4. The method according to claim 3, characterized in that The method further comprises: The control signal of the rocket restraint and release is sent to the restraint and release system, so that the restraint and release system restrains and releases the target rocket at a corresponding time based on the received control signal of the rocket restraint and release.

5. The method according to claim 3, characterized in that: The method further comprises: When the plurality of first-stage engines in the target rocket are not all in normal working condition, the target rocket is emergency shut down and a control signal for restraining and prohibiting release of the rocket is generated.

6. The method according to claim 5, characterized in that The method further comprises: A control signal for prohibiting the release of the rocket is sent to a restraint and release system, so that the restraint and release system maintains the restraint state of the target rocket when receiving the control signal for prohibiting the release of the rocket.

7. A rocket restraint release control device, characterized in that: The device comprises: An engine working state information acquisition module is used to acquire engine working state information respectively sent by multiple controllers in a target rocket; wherein the target rocket includes multiple first-stage engines, each first-stage engine is associated with a sensor and a controller, and the controller is used to acquire sensor data collected by the sensor after the corresponding first-stage engine is started, and generate the working state information of the corresponding first-stage engine based on the sensor data; A control signal generating module is used to generate a control signal for determining whether the target rocket is to be released based on the working status information.

8. An electronic device, characterized in that: include: at least one processor; a memory for storing the at least one processor-executable instruction; The at least one processor is configured to execute the instructions to implement the method according to any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that: When the instructions in the computer-readable storage medium are executed by a processor of an electronic device, the electronic device is enabled to perform the method as claimed in any one of claims 1 to 6.

10. A computer program product, characterized in that The method comprises a computer program, which implements the method according to any one of claims 1 to 6 when being executed by a processor.

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