Rocket launching control method and system, electronic equipment and medium

Abstract

The invention relates to the technical field of spaceflight launching, and provides a rocket launching control method and system, electronic equipment and a medium. For each group of pre-injection programs, if a control instruction is abnormal or has a fault in front of a coupling point, processing the abnormality or the fault; at the coupling point corresponding to the non-last control instruction, if the control instruction is still abnormal or the fault is not eliminated, judging whether the control instruction is in the lowest emission condition range or not, and if the control instruction is not in the lowest emission condition range, abandoning the abnormal or fault part of the control instruction; and S4, when the abnormity or the fault of the control instruction exists at the last coupling point and is still not eliminated, judging whether the abnormity or the fault of the control instruction is in the lowest emission condition range or not, if not, abandoning the abnormity or the fault part of the control instruction, and igniting and emitting according to preset time. According to the scheme, the coupling point setting of various spaceflight launches can be determined, more fault and exception handling time can be gained, and the normal launch of the rocket in the launch window can be ensured.

Description

Technical Field

[0001] The present invention relates to the technical field of space launch, and in particular, to a rocket launch control method, system, electronic device, and medium. Background Art

[0002] After a large cryogenic liquid rocket is filled, once it cannot be launched within the current window, on the one hand, it will cause significant economic losses due to the large amount of cryogenic propellant volatilization, and on the other hand, it may cause the cryogenic propellant to leak out and pose a significant accident risk.

[0003] Eliminating abnormalities and faults in the launch procedure and ensuring that the rocket can be launched normally within the launch window are technical problems that urgently need to be solved nowadays.

[0004] Therefore, there is a need to provide a rocket launch control method, system, electronic device, and medium that can clarify the setting of coupling points for various space launches, facilitate the parties participating in space launches to unify their working rhythms, strive for more time to handle faults and abnormalities, improve the ability of the pre-launch procedure of space launches to cope with various emergencies, and ensure that the rocket can be launched normally within the launch window.

[0005] The above information disclosed in the background art section is only used to enhance the understanding of the background of the present application, and therefore it may include information that does not constitute the prior art known to those of ordinary skill in the art. Summary of the Invention

[0006] The main objective of the present invention is to overcome the problem that the rocket cannot be launched normally within the launch window, and provide a rocket launch control method, system, electronic device, and medium that can clarify the setting of coupling points for various space launches, facilitate the parties participating in space launches to unify their working rhythms, strive for more time to handle faults and abnormalities, improve the ability of the pre-launch procedure of space launches to cope with various emergencies, and ensure that the rocket can be launched normally within the launch window.

[0007] To achieve the above objective, the first aspect of the present invention provides a rocket launch control method, including the following steps:

[0008] S1: Set multiple groups of pre-launch procedures, each group of pre-launch procedures includes multiple control instructions, and each control instruction sets a coupling point, where the coupling point is the countdown node of the control instruction;

[0009] S2: For each group of pre-launch procedures, before the coupling point, if there is an abnormal or faulty control instruction, handle the abnormality or fault;

[0010] S3: At the coupling point corresponding to the non-last control instruction, if there is still an abnormality or a fault in a control instruction that has not been eliminated, determine whether it is within the minimum launch condition range. If it is not within the minimum launch condition range, discard the abnormal or faulty part of the control instruction. Otherwise, handle the abnormality or fault urgently.

[0011] S4: At the last coupling point, when there is an abnormality or fault in the control instruction that has not been eliminated, determine whether it is within the minimum launch condition range. If it is not within the minimum launch condition range, discard the abnormal or faulty part of the control instruction, and ignite and launch at the scheduled time; otherwise, determine the possible loss of the abnormal or faulty part in the decoupling minimum launch condition. If the possible loss is within an acceptable range, discard the abnormal or faulty part, and ignite and launch at the scheduled time; otherwise, if the abnormality or fault is processed before the trailing edge of the launch window, ignite and launch; if the abnormality or fault cannot be processed before the trailing edge of the launch window, postpone or suspend the launch.

[0012] According to an exemplary embodiment of the present invention, in step S1, the pre-launch procedure includes a pre-launch procedure for an unmanned conventional propellant launch vehicle, a pre-launch procedure for a manned space conventional propellant launch vehicle, a pre-launch procedure for a liquid oxygen-kerosene cryogenic propellant launch vehicle, a pre-launch procedure for a liquid oxygen-methane cryogenic propellant launch vehicle, and a pre-launch procedure for a cryogenic propellant launch vehicle containing liquid hydrogen.

[0013] According to an example embodiment of the present invention, the coupling points of the unmanned conventional propellant launch vehicle pre-launch procedures include the air pipe connector falling off, the plug-out falling off, and the launch vehicle ignition;

[0014] The coupling points of the pre-launch procedure of the conventional propellant carrier rocket for manned space flight include: before the astronauts enter the cabin, unplugging and dropping, and ignition of the carrier rocket;

[0015] The coupling points of the pre-launch procedure of the liquid oxygen-kerosene cryogenic propellant carrier rocket include: kerosene filling, liquid oxygen filling, kerosene vacuuming, discharge connector falling off, and carrier rocket ignition;

[0016] The coupling points of the pre-launch procedure of the liquid oxygen-methane cryogenic propellant carrier rocket include: methane filling start, liquid oxygen filling start, methane vacuuming, charging and discharging connector detachment, and carrier rocket ignition;

[0017] The coupling points of the pre-launch procedure of the cryogenic propellant carrier rocket containing liquid hydrogen include the start of kerosene filling, the start of liquid oxygen filling, the start of liquid hydrogen filling, kerosene vacuuming, the fall-off of the charging and discharging connector, and the ignition of the carrier rocket.

[0018] According to an exemplary embodiment of the present invention, step S2 further includes: before the coupling point, releasing the coupling point in advance for some control instructions or releasing some constraints at the coupling point in advance.

[0019] According to an exemplary embodiment of the present invention, the decoupling points for early release include the trachea connector, unplugging and falling off, power transfer coupling on the rocket, coupling between the hydrogen and oxygen systems, and the coupling point between the control system and the power system.

[0020] As a second aspect of the present invention, the present invention provides a rocket launch control system, including: a pre-launch program setting module, a fault handling module, and a launch handling module;

[0021] The pre-launch program setting module is used to set multiple groups of pre-launch programs. Each group of pre-launch programs includes multiple control instructions, and each control instruction sets a coupling point, where the coupling point is the countdown node of the control instruction;

[0022] The fault handling module is used to handle anomalies or faults generated by the pre-launch program;

[0023] The launch handling module is connected to the pre-launch program setting module and the fault handling module, and is used to obtain the pre-launch program; for each group of pre-launch programs, before the coupling point, if there is an anomaly or fault in a control instruction, it instructs the fault handling module to handle the anomaly or fault; at the coupling point corresponding to the non-last control instruction, if there is still an anomaly or fault in a control instruction that has not been eliminated, it determines whether it is within the range of the minimum launch conditions. If it is not within the range of the minimum launch conditions, it discards the abnormal or faulty part of the control instruction and ignites and launches according to a predetermined time; otherwise, it judges the possible loss of the abnormal or faulty part in the decoupling minimum launch conditions. If the possible loss is within an acceptable range, it discards the abnormal or faulty part and ignites and launches according to a predetermined time. Otherwise, if the anomaly or fault is processed before the trailing edge of the launch window, it ignites and launches. If the anomaly or fault cannot be processed before the trailing edge of the launch window, it delays or suspends the launch.

[0024] As a third aspect of the present invention, the present invention provides an electronic device, including:

[0025] One or more processors;

[0026] A storage device for storing one or more programs;

[0027] When the one or more programs are executed by the one or more processors, the one or more processors are caused to implement the rocket launch control method.

[0028] As a fourth aspect of the present invention, the present invention provides a computer-readable medium, on which a computer program is stored, and when the program is executed by a processor, the rocket launch control method is implemented.

[0029] The advantageous effects of the present invention are:

[0030] The present invention dynamically decouples and reconstructs the pre-launch program in real time, dynamically undoes the coupling points in the program according to the progress of the pre-launch program and the status of the entire system in real time, and reconstructs the pre-launch program in real time to ensure that the launch can be ignited on time within the current launch window. Specifically:

[0031] 1) Clarify the setting of coupling points for various types of space launches, so as to facilitate the unification of work rhythms among all parties involved in space launches and facilitate the standardization and regularization of pre-launch procedure design;

[0032] 2) The main method of coupling point decoupling is given to buy more time for fault and abnormal handling in the pre-launch procedure of space launch;

[0033] 3) The main method of real-time reconstruction of the pre-launch program of space launch is given, which improves the ability of the pre-launch program of space launch to deal with various emergencies. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The above and other objects, features and advantages of the present application will become more apparent by describing in detail the exemplary embodiments thereof with reference to the accompanying drawings. The accompanying drawings described below are only some embodiments of the present application, and it is clear to a person skilled in the art that other accompanying drawings can be obtained from these accompanying drawings without creative effort.

[0035] Figure 1 The structural diagram of the rocket launch control system is schematically shown.

[0036] Figure 2 A step diagram of a rocket launch control method is schematically shown. Figure 3 The structure of an electronic device is schematically shown. Figure 4 A structural diagram of a computer medium is schematically shown. DETAILED DESCRIPTION

[0037] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this application will be comprehensive and complete and will fully convey the concepts of the example embodiments to those skilled in the art. The same reference numerals in the figures represent the same or similar parts, and thus their repeated description will be omitted.

[0038] In addition, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments. In the following description, numerous specific details are provided to give a thorough understanding of the embodiments of the present application. However, those skilled in the art will realize that the technical solutions of the present application may be practiced without one or more of the specific details, or other methods, components, devices, steps, etc. may be adopted. In other cases, well-known methods, devices, implementations, or operations are not shown or described in detail to avoid obscuring aspects of the present application.

[0039] The block diagrams shown in the drawings are only functional entities and do not necessarily correspond to physically independent entities. That is, these functional entities may be implemented in software form, or implemented in one or more hardware modules or integrated circuits, or implemented in different networks and / or processor devices and / or microcontroller devices.

[0040] The flowcharts shown in the drawings are only illustrative and do not necessarily include all the content and operations / steps, nor are they necessarily executed in the described order. For example, some operations / steps can be decomposed, while some operations / steps can be combined or partially combined, so the actual execution order may change according to the actual situation.

[0041] It should be understood that although terms such as first, second, and third may be used herein to describe various components, these components should not be limited by these terms. These terms are used to distinguish one component from another. Therefore, the first component discussed below may be referred to as the second component without departing from the teachings of the concept of the present application. As used herein, the term "and / or" includes any one of the associated listed items and all combinations of one or more of them.

[0042] Those skilled in the art can understand that the drawings are only schematic diagrams of exemplary embodiments, and the modules or processes in the drawings are not necessarily essential for implementing the present application, so they cannot be used to limit the protection scope of the present application.

[0043] According to the first specific embodiment of the present invention, the present invention provides a rocket launch control system, as Figure 1 shown, including: a pre-launch program setting module, a fault handling module, and a launch processing module.

[0044] The pre-launch program setting module is used to set multiple groups of pre-launch programs. Each group of pre-launch programs includes multiple control instructions, and each control instruction sets a coupling point, and the coupling point is the countdown node of the control instruction.

[0045] The fault handling module is used to handle the anomalies or faults generated by the pre-launch program.

[0046] The launch processing module is connected to the pre-launch program setting module and the fault handling module, and is used to obtain the pre-launch program; for each set of pre-launch programs, before the coupling point, if there is an abnormality or a fault in the control instruction, the fault handling module is instructed to handle the abnormality or the fault; at the coupling point corresponding to the non-last control instruction, if there is still an abnormality or a fault in the control instruction that has not been eliminated, it is judged whether it is within the range of the minimum launch conditions. If it is not within the range of the minimum launch conditions, the abnormal or faulty part of the control instruction is discarded, and ignition and launch are carried out according to the predetermined time; otherwise, it is judged the possible loss of the abnormal or faulty part in the decoupled minimum launch conditions. If the possible loss is within the acceptable range, the abnormal or faulty part is discarded, and ignition and launch are carried out according to the predetermined time. Otherwise, if the abnormality or the fault is processed before the trailing edge of the launch window, ignition and launch are carried out. If the abnormality or the fault cannot be processed before the trailing edge of the launch window, the launch is postponed or suspended.

[0047] As the second specific embodiment of the present invention, the present invention provides a rocket launch control method, as Figure 2 shown, including the following steps:

[0048] S1: Set multiple sets of pre-launch programs, each set of pre-launch programs includes multiple control instructions, and each control instruction is provided with a coupling point, and the coupling point is the countdown node of the control instruction.

[0049] The coupling point of the pre-launch program is a countdown node artificially set at a critical point of the program progress in order to coordinate the work of each system (each system in manned space launch includes: astronaut system, application system, manned spacecraft system, launch vehicle system, launch site system, TT&C system, etc.; conventional space launch generally includes: spacecraft system, launch vehicle system, launch site system, TT&C system, etc., and can also be further subdivided according to actual situations), maintain the rhythm of the launch program and facilitate command decision-making. At the coupling point, it is required that each relevant system complete the specified work and use this as a condition for whether to continue the subsequent work. Decoupling means canceling the coupling point or a specific coupling content on the coupling point.

[0050] The pre-launch programs include non-manned conventional propellant launch vehicle pre-launch programs, manned spaceflight conventional propellant launch pre-launch programs, liquid oxygen-kerosene cryogenic propellant launch vehicle pre-launch programs, liquid oxygen-methane cryogenic propellant launch vehicle pre-launch programs, and cryogenic propellant launch vehicle pre-launch programs containing liquid hydrogen.

[0051] The liquid oxygen-kerosene cryogenic propulsion launch vehicle means that the propellants used by the launch vehicle are kerosene (fuel) and liquid oxygen (oxidizer), which are like the gasoline used by a car and are the power sources for the launch vehicle to fly. Since the rocket has to work in a vacuum, kerosene must have liquid oxygen as an oxidizer to burn in a vacuum environment. Since the temperature range of liquid oxygen is -183°C to -218.8°C, it is also called a cryogenic propellant launch vehicle.

[0052] The meaning of a liquid oxygen-methane cryogenic propellant launch vehicle is similar to that of a liquid oxygen-kerosene cryogenic propellant launch vehicle.

[0053] A cryogenic propellant launch vehicle containing liquid hydrogen, such as the Long March 5 launch vehicle, means that the propellant used in the launch vehicle contains liquid hydrogen.

[0054] The coupling points of the pre-launch procedure of a non-manned conventional propellant launch vehicle include the disconnection of the gas pipe connector, the disconnection of the plug, and the ignition of the launch vehicle.

[0055] The disconnection of the gas pipe connector. The gas pipe connector is a connecting device between the rocket power system and the ground system. It usually has 7 pipes, so it is also called a seven-pipe connector. The meaning of disconnection is that the gas pipe connector separates from the launch vehicle.

[0056] The disconnection of the plug. The plug is a connecting device between the rocket electrical system and the ground system. The meaning of disconnection is that the plug separates from the launch vehicle.

[0057] The start of kerosene filling means starting to fill kerosene into the kerosene storage tank of the launch vehicle, referring to both the instruction to start filling kerosene and the moment to start filling kerosene.

[0058] The start of liquid oxygen filling means starting to fill liquid oxygen into the liquid oxygen storage tank of the launch vehicle, referring to both the instruction to start filling liquid oxygen and the moment to start filling liquid oxygen.

[0059] The evacuation of kerosene means pumping out the gas in the kerosene storage tank and engine of the launch vehicle so that only kerosene remains inside them.

[0060] The disconnection of the filling and drainage connector. The filling and drainage connector is a connector between the ground filling pipeline and the rocket, just like the filling gun when refueling a car. The ground fills the propellant into the rocket through this connector. When the rocket fails to launch on time, the propellant in the rocket propellant storage tank can also be drained through this connector.

[0061] The start of liquid hydrogen filling means starting to fill liquid hydrogen into the liquid hydrogen storage tank of the launch vehicle, referring to both the instruction to start filling liquid hydrogen and the moment to start filling liquid hydrogen.

[0062] The coupling points of the pre-launch procedure of a manned spaceflight conventional propellant launch vehicle include: before the astronauts enter the cabin, the disconnection of the plug, and the ignition of the launch vehicle.

[0063] The coupling points of the pre-launch procedure of a liquid oxygen-kerosene cryogenic propellant launch vehicle include: the start of kerosene filling, the start of liquid oxygen filling, the evacuation of kerosene, the disconnection of the filling and drainage connector, and the ignition of the launch vehicle.

[0064] The coupling points of the pre-launch procedure of a liquid oxygen-methane cryogenic propellant launch vehicle include: methane filling begins, liquid oxygen filling begins, methane vacuuming, the filling and exhaust connectors fall off, and the launch vehicle ignition.

[0065] Theoretically, the connector should fall off at 0 seconds in the countdown. In reality, due to concerns that failure to fall off at 0 seconds may lead to catastrophic consequences, it is made to fall off in advance at -3 minutes.

[0066] The pre-launch procedures for a cryogenic propellant carrier rocket containing liquid hydrogen include: starting to fill kerosene, starting to fill liquid oxygen, starting to fill liquid hydrogen, kerosene vacuuming, detachment of the filling and exhaust connectors, and ignition of the carrier rocket.

[0067] S2: For each set of pre-shooting programs, before the coupling point, if there is an abnormality or failure in any control instruction, the abnormality or failure is handled.

[0068] Before the coupling point, the coupling point is released in advance for some control instructions or some constraints at the coupling point are released in advance.

[0069] Decoupling means releasing the coupling point or releasing some of the constraints at the coupling point.

[0070] The coupling points that are released in advance include the detachment of the air pipe connector, the detachment of the plug, the arrow-to-electric coupling, the coupling between the hydrogen and oxygen systems, and the coupling points between the control system and the power system.

[0071] For the trachea connector, we utilize the increased reliability of various rocket systems to decouple the trachea connector of conventional propellant launch vehicles and move key actions such as the trachea connector detachment forward to gain more working time margin for subsequent work.

[0072] As the number of flights increases, the quality problems will be learned from experience, and the reliability of various systems of my country's rockets will continue to be tested and iterated. For example, the reliability of the CZ-2F launch vehicle has been improved from 0.97 at the beginning of the design to 0.9894 today. The time for the air pipe connector to fall off of the conventional launch vehicle CZ-2 series and CZ-4 series has also been shortened from the original -40 minutes to -50 minutes and -70 minutes.

[0073] For the unplugging and detaching conditions, the relationship between the participating systems is utilized to decouple the conditions for the unplugging and detaching of manned conventional propellant launch vehicles, such as astronauts' voice communication between the ground and the sky. The minimum launch condition is changed from good voice quality to normal operation of all related systems to reduce the possibility of delaying the launch.

[0074] Among the systems under test, there is a relatively independent relationship with each other. Even if all systems are normal, due to the influence of the working environment, a certain state of the entire system may show abnormal conditions. Just like the astronaut's space-ground communication, even if all systems are working properly, the space-ground voice communication may be interrupted due to interference in the wireless communication line.

[0075] For the on-board power transfer coupling, by increasing the battery capacity and design margin, etc., decouple the on-board power transfer coupling, and advance key actions such as the power transfer of the control system and the measurement system, so as to increase the working time margin of relevant systems. On-board power transfer means that before the rocket uses electricity, it is supplied by the ground. Power transfer is to cut off the ground power supply and supply power by the rocket's battery. The control system generally refers to the system that controls the rocket flight. The measurement system generally refers to the system that measures the working status of each system of the rocket.

[0076] Decouple the coupling between the hydrogen and oxygen systems. In the conventional procedure, after the liquid oxygen is filled, it is necessary to wait for the liquid hydrogen to be filled as well, and then pressurize their respective storage tanks and empty the filling pipelines together. After decoupling, the storage tank pressurization and the filling pipeline emptying can be carried out separately for the liquid oxygen and liquid hydrogen systems without having to wait for each other. For the pre-launch action coupling between the hydrogen and oxygen systems, decouple the pre-launch action coupling between the hydrogen and oxygen systems, reduce the working constraint relationship between the liquid hydrogen and liquid oxygen systems, and ensure that once a certain system fails, it will not affect the operation of the other system.

[0077] Decouple the coupling between the control system and the power system. In the conventional procedure, the power transfer, start calculation of the control system and the gas source opening command of the engine gas cylinder of the power system should be issued simultaneously. After decoupling, the two can be issued separately. For the coupling between the control system and the power system, decouple the coupling between the control system and the power system, reduce the working constraint relationship between the two systems before launch, so that the fault handling only needs to consider the logic relationship of this system, in order to increase the freedom of the working procedures of relevant systems.

[0078] The procedures mentioned above are classified according to the rocket type. Each rocket has a control system and a power system, and each type of rocket has its own pre-launch procedure. Therefore, the control system and the power system are related to all the procedures mentioned above.

[0079] Before the coupling point, the system with an anomaly or fault disposes of it by itself. At the coupling point, all systems keep their operations synchronized according to the agreement.

[0080] S3: At the coupling point corresponding to the non-last control instruction, if there are still anomalies or faults in the control instruction that have not been eliminated, then judge whether it is within the range of the minimum launch conditions. If it is not within the range of the minimum launch conditions, then discard the abnormal or faulty part of the control instruction. Otherwise, handle this anomaly or fault emergently.

[0081] The minimum launch conditions refer to the situation where the rocket cannot be ignited and launched when these conditions are not met. Almost every launch has its own minimum launch conditions. The range consists of numerous key parameters of systems such as the spacecraft system, rocket system, launch site system, TT&C communication system, etc. If any one of these parameters does not meet the requirements, the rocket cannot be ignited and launched. For example, the ground wind speed not exceeding 10 m / s, the normal operation of ground safety control equipment, normal key telemetry parameters on the rocket, and normal key telemetry parameters on the spacecraft are all among the minimum launch conditions.

[0082] At the coupling point, when the anomaly or fault has not been eliminated yet, the decision-making body confirms whether it is within the range of the minimum launch conditions. If it is not within the range of the minimum launch conditions, the abnormal or faulty part is discarded, and the pre-launch procedure continues to advance; otherwise, the abnormal or faulty system undergoes emergency disposal, the normal system continues to advance, and the relevant systems work in alignment at the subsequent coupling points.

[0083] S4: At the last coupling point (launch vehicle ignition), when there is still an anomaly or fault in the control command that has not been eliminated, it is judged whether it is within the range of the minimum launch conditions. If it is not within the range of the minimum launch conditions, the abnormal or faulty part of the control command is discarded, and the rocket is ignited and launched at the scheduled time; otherwise, it is judged the possible losses of the abnormal or faulty part in the decoupled minimum launch conditions. If the possible losses are within the acceptable range, the abnormal or faulty part is discarded, and the rocket is ignited and launched at the scheduled time. Otherwise, if the anomaly or fault is processed before the trailing edge of the launch window, the rocket is ignited and launched; if the anomaly or fault cannot be processed before the trailing edge of the launch window, the launch is postponed or suspended.

[0084] Possible losses, such as a rocket telemetry image failure, where the ground will not be able to see the live TV image inside the rocket fairing, but it will not have any impact on the normal flight of the rocket. Whether the possible losses are acceptable is subjective.

[0085] After the launch is postponed or suspended, the entire system transfers to the predetermined safe recovery point.

[0086] This solution focuses on how to ensure the launch is carried out within the current launch window and minimize the risk of postponed launch. It implements the principle of "emergency disposal for abnormal systems, continuous advancement of normal systems, and alignment of work at subsequent coupling points", applies space launch condition control technology based on state transition, and realizes real-time reconstruction of the pre-launch procedure.

[0087] This solution dynamically decouples and reconstructs the pre-launch procedure in real time according to the progress of the space launch pre-launch procedure and the state of the entire system. It dynamically releases the coupling points in the procedure in real time and reconstructs the pre-launch procedure in real time to ensure that the rocket can be ignited and launched on time within the current launch window. Specifically:

[0088] 1) Define the coupling point settings for various space launches, facilitating the unification of work rhythms among all parties participating in space launches and promoting the standardization and normalization of pre-launch procedures.

[0089] 2) Present the main methods for decoupling coupling points, allowing more time for troubleshooting and handling anomalies in pre-launch procedures for space launches.

[0090] 3) Present the main methods for real-time reconstruction of pre-launch procedures for space launches, enhancing the ability of pre-launch procedures to handle various emergencies.

[0091] According to the third specific embodiment of the present invention, the present invention provides an electronic device, as Figure 3 shown, Figure 3 is a block diagram of an electronic device shown according to an exemplary embodiment.

[0092] Next, refer to Figure 3 to describe the electronic device 300 according to this embodiment of the present application. Figure 3 The electronic device 300 shown is merely an example and should not impose any limitations on the functions and usage scope of the embodiments of the present application.

[0093] As Figure 3 shown, the electronic device 300 is presented in the form of a general computing device. The components of the electronic device 300 may include, but are not limited to: at least one processing unit 310, at least one storage unit 320, a bus 330 connecting different system components (including the storage unit 320 and the processing unit 310), a display unit 340, etc.

[0094] Among them, the storage unit stores program code, and the program code can be executed by the processing unit 310, enabling the processing unit 310 to execute the steps according to various exemplary embodiments of the present application described in this specification. For example, the processing unit 310 can execute the steps shown in the second specific embodiment.

[0095] The storage unit 320 may include a readable medium in the form of a volatile storage unit, such as a random access storage unit (RAM) 3201 and / or a cache storage unit 3202, and may further include a read-only storage unit (ROM) 3203.

[0096] The storage unit 320 may also include a program / utility 3204 having a set (at least one) of program modules 3205. Such program modules 3205 include, but are not limited to: an operating system, one or more application programs, other program modules, and program data. Each or some combination of these examples may include the implementation of a network environment.

[0097] The bus 330 can represent one or more of several types of bus structures, including a memory unit bus or a memory unit controller, a peripheral bus, an accelerated graphics port, a processing unit, or a local bus using any of the various bus structures.

[0098] The electronic device 300 can also communicate with one or more external devices 300' (such as a keyboard, a pointing device, a Bluetooth device, etc.), devices that enable a user to interact with the electronic device 300, and / or any device with which the electronic device 300 can communicate with one or more other computing devices (such as a router, a modem, etc.). Such communication can be carried out through the input / output (I / O) interface 350. Moreover, the electronic device 300 can also communicate with one or more networks (such as a local area network (LAN), a wide area network (WAN), and / or a public network, such as the Internet) through the network adapter 360. The network adapter 360 can communicate with other modules of the electronic device 300 through the bus 330. It should be understood that, although not shown in the figure, other hardware and / or software modules can be used in conjunction with the electronic device 300, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems, etc.

[0099] From the description of the above embodiments, those skilled in the art can easily understand that the exemplary embodiments described herein can be implemented by software, or by a combination of software and necessary hardware.

[0100] Therefore, according to the fourth specific embodiment of the present invention, the present invention provides a computer-readable medium. As Figure 4 shown, the technical solution according to the embodiment of the present invention can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a USB flash drive, a mobile hard disk, etc.) or on a network, including several instructions to enable a computing device (which can be a personal computer, a server, or a network device, etc.) to execute the above method according to the embodiment of the present invention.

[0101] The software product may employ any combination of one or more readable media. The readable media can be a readable signal medium or a readable storage medium. The readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the foregoing. More specific examples (a non-exhaustive list) of the readable storage medium include: an electrical connection having one or more wires, a portable 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 disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.

[0102] The computer-readable storage medium may include a data signal propagated in a baseband or as part of a carrier wave, in which the readable program code is carried. Such a propagated data signal may take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the foregoing. The readable storage medium may also be any readable medium other than the readable storage medium, which can send, propagate, or transmit a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on the readable storage medium may be transmitted using any appropriate medium, including but not limited to wireless, wireline, optical fiber cable, RF, etc., or any suitable combination of the foregoing.

[0103] The program code for performing the operations of the present invention may be written in any combination of one or more programming languages, including object-oriented programming languages such as Java, C++, etc., and also including conventional procedural programming languages such as the "C" language or similar programming languages. The program code may be executed entirely on the user computing device, partially on the user device, executed as a stand-alone software package, partially on the user computing device and partially on a remote computing device, or entirely on the remote computing device or server. In the case of a remote computing device, the remote computing device may be connected to the user computing device through any type of network, including a local area network (LAN) or a wide area network (WAN), or may be connected to an external computing device (e.g., by using an Internet service provider to connect through the Internet).

[0104] The above-mentioned computer-readable medium carries one or more programs, and when the one or more programs are executed by a device, the computer-readable medium realizes the functions of the second specific embodiment.

[0105] Those skilled in the art can understand that the above-mentioned modules can be distributed in the device according to the description of the embodiments, or can be correspondingly changed and distributed in one or more devices that are only different from this embodiment. The modules of the above embodiments can be combined into one module, or can be further split into multiple sub-modules.

[0106] Through the description of the above embodiments, those skilled in the art can easily understand that the exemplary embodiments described herein can be implemented by software, or can be implemented by the way of software combined with necessary hardware. Therefore, the technical solution according to the embodiment of the present invention can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (which can be a CD-ROM, a USB flash drive, a mobile hard disk, etc.) or on a network, including several instructions to enable a computing device (which can be a personal computer, a server, a mobile terminal, or a network device, etc.) to execute the method according to the embodiment of the present invention.

[0107] The above specifically shows and describes the exemplary embodiments of the present invention. It should be understood that the present invention is not limited to the detailed structure, setting mode or implementation method described herein; on the contrary, the present invention is intended to cover various modifications and equivalent settings included in the spirit and scope of the appended claims.

Claims

1. A rocket launch control method, characterized in that: The following steps are involved: S1: multiple groups of pre-shooting programs are set, each group of pre-shooting programs includes multiple control instructions, each control instruction is set with a coupling point, and the coupling point is the countdown node of the control instruction; S2: For each set of pre-fire programs, before the coupling point, if there is an abnormality or failure in any control instruction, the abnormality or failure is processed; S3: At the coupling point corresponding to the non-last control instruction, if there is still an abnormality or a fault in a control instruction that has not been eliminated, determine whether it is within the minimum launch condition range. If it is not within the minimum launch condition range, discard the abnormal or faulty part of the control instruction. Otherwise, handle the abnormality or fault urgently. S4: At the last coupling point, when there is an abnormality or fault in the control instruction that has not been eliminated, determine whether it is within the minimum launch condition range. If it is not within the minimum launch condition range, discard the abnormal or faulty part of the control instruction, and ignite and launch at the scheduled time; otherwise, determine the possible loss of the abnormal or faulty part in the decoupling minimum launch condition. If the possible loss is within an acceptable range, discard the abnormal or faulty part, and ignite and launch at the scheduled time; otherwise, if the abnormality or fault is processed before the trailing edge of the launch window, ignite and launch; if the abnormality or fault cannot be processed before the trailing edge of the launch window, postpone or suspend the launch.

2. The rocket launch control method according to claim 1, characterized in that: In step S1, the pre-launch procedures include pre-launch procedures for unmanned conventional propellant launch vehicles, pre-launch procedures for manned space conventional propellant launch vehicles, pre-launch procedures for liquid oxygen and kerosene cryogenic propellant launch vehicles, pre-launch procedures for liquid oxygen and methane cryogenic propellant launch vehicles, and pre-launch procedures for cryogenic propellant launch vehicles containing liquid hydrogen.

3. The rocket launch control method according to claim 2, characterized in that: The coupling points of the unmanned conventional propellant launch vehicle pre-launch procedure include the detachment of the air pipe connector, the detachment of the plug, and the ignition of the launch vehicle; The coupling points of the pre-launch procedure of the conventional propellant carrier rocket for manned space flight include: astronaut entry, unplugging and detaching, and ignition of the carrier rocket; The coupling points of the pre-launch procedure of the liquid oxygen-kerosene cryogenic propellant carrier rocket include: kerosene filling, liquid oxygen filling, kerosene vacuuming, discharge connector falling off, and carrier rocket ignition; The coupling points of the pre-launch procedure of the liquid oxygen-methane cryogenic propellant carrier rocket include: methane filling start, liquid oxygen filling start, methane vacuuming, charging and discharging connector detachment, and carrier rocket ignition; The coupling points of the pre-launch procedure of the cryogenic propellant carrier rocket containing liquid hydrogen include: kerosene filling start, liquid oxygen filling start, liquid hydrogen filling start, kerosene vacuuming, charging and discharging connector falling off, and carrier rocket ignition.

4. The rocket launch control method according to claim 1, characterized in that: Step S2 also includes: before the coupling point, releasing the coupling point in advance for some control instructions or releasing some constraints at the coupling point in advance.

5. The rocket launch control method according to claim 4, characterized in that: The coupling points that are released in advance include the air pipe connector, plug-in disconnection, arrow-to-electricity coupling, coupling between the hydrogen and oxygen systems, and coupling points between the control system and the power system.

6. A rocket launch control system, characterized in that: include: Pre-launch program setting module, fault handling module, launch processing module; The pre-shooting program setting module is used to set multiple groups of pre-shooting programs, each group of pre-shooting programs includes multiple control instructions, each control instruction is set with a coupling point, and the coupling point is a countdown node of the control instruction; The fault handling module is used to handle the anomalies or faults generated by the pre-firing program; The launch processing module is connected to the pre-launch program setting module and the fault processing module to obtain the pre-launch program; for each set of pre-launch programs, before the coupling point, if there is an abnormality or a fault in a control instruction, the fault processing module is instructed to handle the abnormality or fault; at the coupling point corresponding to the non-last control instruction, if there is still an abnormality or a fault in a control instruction that has not been eliminated, it is determined whether it is within the minimum launch condition range. If it is not within the minimum launch condition range, the abnormal or faulty part of the control instruction is discarded, otherwise, the fault processing module is instructed to handle the abnormality or fault in an emergency; at the last At the coupling point, when there is an abnormality or fault in the control instruction that has not been eliminated, determine whether it is within the minimum launch condition range. If it is not within the minimum launch condition range, discard the abnormal or faulty part of the control instruction, and ignite and launch at the scheduled time; otherwise, determine the possible loss of the abnormal or faulty part in the decoupling minimum launch condition. If the possible loss is within an acceptable range, discard the abnormal or faulty part, and ignite and launch at the scheduled time; otherwise, if the abnormality or fault is processed before the trailing edge of the launch window, ignite and launch; if the abnormality or fault cannot be processed before the trailing edge of the launch window, postpone or suspend the launch.

7. An electronic device, characterized in that: include: one or more processors; A storage device for storing one or more programs; When the one or more programs are executed by the one or more processors, the one or more processors implement the rocket launch control method as described in any one of claims 1-6.

8. A computer readable medium having a computer program stored thereon, characterized in that: When the program is executed by the processor, it implements the rocket launch control method as described in any one of claims 1-6.

Images