Rocket launching method and device, electronic equipment and computer readable storage medium

Abstract

The application discloses a rocket launching method and device, electronic equipment and computer readable storage medium, and relates to the fields of aerospace technology and rocket launching technology. The method comprises the following steps: receiving a task instruction corresponding to a rocket, wherein the task instruction indicates to execute a first task or a second task; in the case that the task instruction indicates to execute the first task, packaging the rocket fairing and a satellite into a vertical attitude star cover combination, controlling the star cover combination to be docked with the rocket into a target component on a launching ship, and launching the target component; in the case that the task instruction indicates to execute the second task, packaging the rocket fairing, the satellite and the rocket into a horizontal attitude whole component, and launching the whole component on the launching ship. The application solves the technical problem of low efficiency of launching a rocket at sea due to the lack of standardization of the docking mode of the rocket and the satellite in the prior art.

Description

Technical Field

[0001] This application relates to the fields of aerospace technology and rocket launch technology, and more specifically, to a rocket launch method, apparatus, electronic equipment, and computer-readable storage medium. Background Technology

[0002] Rocket launches at a launch site require following specific procedures and processes to complete technical preparations within the rocket factory in the technical area. They are then transported to the launch pad in the launch area, where further launch preparations are completed according to established procedures before ignition and launch. This entire process is known as the technical procedure for rocket launches. When launching a rocket at sea, after completing technical preparations, the rocket must be loaded onto a ship and launched from the sea area. Therefore, its technical procedure has its own unique characteristics and differences.

[0003] Under current rocket-to-satellite launch technology, if a rocket launch is required at sea, the rocket and satellite need to be transported separately to the same area for pre-assembly and docking before being transported by ship to the designated launch area. However, since different types of satellites have different requirements for transportation conditions, the actual rocket-satellite docking and transportation methods have different requirements for the satellite's attitude. However, current technology usually relies on human experience to determine the satellite's transportation attitude and docking procedures under different transportation attitudes, which may lead to excessive adjustment operations during the rocket launch process, resulting in the technical problem of low efficiency in launching rockets at sea.

[0004] There is currently no effective solution to the above problems. Summary of the Invention

[0005] This application provides a rocket launch method, apparatus, electronic device, and computer-readable storage medium to at least solve the technical problem of low efficiency in sea-launched rockets due to the lack of standardization in the docking method between rockets and satellites in the prior art.

[0006] According to one aspect of this application, a rocket launch method is provided, comprising: receiving a mission command corresponding to the rocket, wherein the mission command instructs the execution of a first mission or a second mission, the first mission instructing that a satellite to be launched by the rocket needs to be transported in a vertical attitude, and the second mission instructing that a satellite to be launched by the rocket does not need to be transported in a vertical attitude; when the mission command instructs the execution of the first mission, encapsulating the rocket fairing and the satellite into a vertically oriented satellite-fairing assembly, controlling the docking of the satellite-fairing assembly with the rocket as a target component on a launch ship, and launching the target component, wherein the launch ship is a vessel used for launching rockets; when the mission command instructs the execution of the second mission, encapsulating the rocket fairing, the satellite, and the rocket into a horizontally oriented integral component, and launching the integral component from the launch ship.

[0007] Optionally, the rocket launch method further includes: before receiving the launch mission command corresponding to the rocket, obtaining a list of the satellite's constituent materials, wherein the list of constituent materials is used to record the names of N materials that make up the satellite, where N is an integer greater than 1; detecting whether the list of constituent materials includes the name of a target material, wherein the target material is a material that needs to maintain stability in a vertical attitude; if the list of constituent materials includes the name of the target material, determining that the mission command instructs the execution of a first mission; if the list of constituent materials does not include the name of the target material, determining that the mission command instructs the execution of a second mission.

[0008] Optionally, the rocket launch method also includes: after the satellite array assembly is transported to the target sea area where the launch ship is located by a transport ship, adjusting the satellite array assembly to a horizontal attitude; and docking the satellite array assembly in the horizontal attitude with the rocket in the horizontal attitude as a target component.

[0009] Optionally, the rocket launch method further includes: moving the rocket to the launch platform in a horizontal attitude before the control satellite array assembly is docked with the rocket as the target component on the launch ship; fixing the launch platform and the rocket on the launch platform to the launch ship; and controlling the launch ship to move to the target sea area.

[0010] Optionally, the rocket launch method further includes: when the mission command instructs the execution of a second mission, encapsulating the horizontally oriented rocket fairing and the horizontally oriented rocket as a first component; and encapsulating the first component and the horizontally oriented satellite as an integral component.

[0011] Optionally, the rocket launch method further includes: after encapsulating the rocket fairing, satellite, and rocket into a horizontally oriented integral assembly, moving the integral assembly to the launch platform in a horizontal orientation; fixing the launch platform and the integral assembly on the launch platform to the launch ship, and controlling the launch ship to move to the target sea area.

[0012] Optionally, the rocket launch method further includes: adjusting the target component to a target angle attitude based on the sway amplitude of the launch vessel; and launching the target component at the target angle attitude.

[0013] According to another aspect of this application, a rocket launch device is also provided, comprising: a receiving unit for receiving mission instructions corresponding to the rocket, wherein the mission instructions indicate the execution of a first mission or a second mission, the first mission indicating that the satellite to be launched by the rocket needs to be transported in a vertical attitude, and the second mission indicating that the satellite to be launched by the rocket does not need to be transported in a vertical attitude; a first mission execution unit for, when the mission instructions indicate the execution of the first mission, encapsulating the rocket fairing and the satellite into a vertically oriented satellite fairing assembly, controlling the satellite fairing assembly to dock with the rocket as a target component on a launch ship, and launching the target component, wherein the launch ship is a vessel used for launching rockets; and a second mission execution unit for, when the mission instructions indicate the execution of the second mission, encapsulating the rocket fairing, the satellite, and the rocket into a horizontally oriented integral component, and launching the integral component on a launch ship.

[0014] According to another aspect of this application, a computer-readable storage medium is also provided, wherein a computer program is stored in the computer-readable storage medium, wherein the computer program, when running, controls the device where the computer-readable storage medium is located to execute any of the above-mentioned rocket launch methods.

[0015] According to another aspect of this application, an electronic device is also provided, wherein the electronic device includes one or more processors and a memory for storing one or more programs, wherein when the one or more programs are executed by the one or more processors, the one or more processors cause the one or more processors to implement the rocket launch method of any of the above.

[0016] In this application, a method of dividing rocket launch missions based on the rocket's transport attitude is adopted. First, the mission command corresponding to the rocket is received. This mission command indicates either a first mission or a second mission. The first mission indicates that the satellite to be launched by the rocket needs to be transported in a vertical attitude, while the second mission indicates that the satellite to be launched by the rocket does not need to be transported in a vertical attitude. When the mission command indicates the execution of the first mission, the rocket fairing and satellite are packaged into a vertically oriented satellite-fairing assembly. The satellite-fairing assembly is docked with the rocket from the launch ship as the target component, and then launched. The launch ship is a vessel used for launching rockets. When the mission command indicates the execution of the second mission, the rocket fairing, satellite, and rocket are packaged into a horizontally oriented integral component, and the integral component is launched from the launch ship.

[0017] As can be seen from the above, this application sets up corresponding docking procedures for rockets and satellites for two scenarios: satellites that need to be transported in a vertical attitude and satellites that do not need to be transported in a vertical attitude. This ensures that different types of satellites can be stably docked with rockets and moved to launch ships. Furthermore, through the standardized design of the docking procedure, the technical effect of shortening the launch cycle of sea-based rocket launch missions is achieved, avoiding a large amount of human interference and solving the technical problem of low efficiency of sea-based rocket launches caused by the lack of standardization in the docking method between rockets and satellites in the prior art. Attached Figure Description

[0018] The accompanying drawings, which are included to provide a further understanding of this application and form part of this application, illustrate exemplary embodiments and are used to explain this application, but do not constitute an undue limitation of this application. In the drawings:

[0019] Figure 1 This is a flowchart of an optional rocket launch method according to an embodiment of this application;

[0020] Figure 2 This is a flowchart of an optional task type determination according to an embodiment of this application;

[0021] Figure 3 This is a flowchart illustrating the execution of an optional first task according to an embodiment of this application;

[0022] Figure 4 This is an execution flowchart of an optional second task according to an embodiment of this application;

[0023] Figure 5 This is a schematic diagram of an optional rocket launch device according to an embodiment of this application;

[0024] Figure 6 This is a schematic diagram of an electronic device provided according to an embodiment of this application. Detailed Implementation

[0025] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0026] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this application described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0027] It should also be noted that all information and data involved in this application are authorized by the user or fully authorized by all parties. For example, this system has an interface with the relevant user or organization. Before obtaining relevant information, it needs to send an acquisition request to the aforementioned user or organization through the interface, and obtain the relevant information after receiving consent from the aforementioned user or organization.

[0028] According to an embodiment of this application, an embodiment of a rocket launch method is provided. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0029] Figure 1 This is a flowchart of an optional rocket launch method according to an embodiment of this application, such as... Figure 1 As shown, the method includes the following steps:

[0030] Step S101: Receive the mission instructions corresponding to the rocket.

[0031] In step S101, the mission instruction indicates the execution of a first mission or a second mission. The first mission indicates that the satellite launched by the rocket needs to be transported in a vertical attitude, while the second mission indicates that the satellite launched by the rocket does not need to be transported in a vertical attitude.

[0032] In one optional embodiment, a rocket launch management system (hereinafter referred to as the management system) can serve as the execution entity of the rocket launch method of this application embodiment. The management system can be a software system or an embedded system combining software and hardware. Alternatively, the management system can be an integrated system of at least one software and at least one hardware device, wherein the at least one hardware device and at least one software constituting the management system can communicate based on a preset communication protocol.

[0033] Optionally, the rockets mentioned above can be of various types. For example, according to the power plant, the rockets mentioned above include, but are not limited to, nuclear-powered rockets and chemical fuel rockets (including liquid propellant rockets, solid propellant rockets, and hybrid solid-liquid propellant rockets); according to the structural form, the rockets mentioned above include, but are not limited to, tandem rockets and parallel rockets.

[0034] Optionally, the mission instructions corresponding to the rocket described above are used to indicate a first mission or a second mission, wherein the first mission is used to indicate the launch of at least one satellite that needs to be transported in a vertical attitude using a rocket. The second mission is used to indicate the launch of at least one satellite that does not need to be transported in a vertical attitude (e.g., a horizontal attitude) using a rocket.

[0035] Alternatively, the aforementioned satellites can be various types of satellites, such as communication satellites, meteorological observation satellites, etc.

[0036] It should be noted that mission instructions can be instructions entered by the user in the management system, or instructions automatically generated by the management system based on the equipment parameters of the rocket and satellite recorded in the system. For example, if the management system records that rocket 1 needs to launch a satellite of type T, it determines that satellite type T needs to be transported in a vertical attitude before launch, and thus generates mission instructions for rocket 1 to instruct the execution of the first mission. As another example, if the management system records that rocket 2 needs to launch a satellite of type R, it determines that satellite type R does not need to be transported in a vertical attitude before launch, and thus generates mission instructions for rocket 2 to instruct the execution of the second mission.

[0037] In step S102, when the mission command instructs the execution of the first mission, the rocket fairing and the satellite are encapsulated into a vertically oriented satellite fairing assembly. The satellite fairing assembly is docked with the rocket on the launch ship to form the target component, and the target component is launched.

[0038] In step S102, the launch vessel is a ship used to launch rockets.

[0039] Optionally, in the embodiments of this application, the first mission is to send a satellite into space by launching a rocket at sea. When the mission command instructs the execution of the first mission, since the satellite needs to be transported in a vertical attitude, the management system can control the packaging equipment to pre-package the rocket fairing and the satellite into a vertically oriented satellite fairing assembly. It should be noted that the packaging equipment can be at least one hardware device that makes up the management system, such as welding equipment or cutting equipment with packaging function.

[0040] In addition, since the rocket fairing is designed to be more vertical, encapsulating the rocket fairing and the satellite into a vertically oriented satellite fairing assembly also makes it easier for the satellite to maintain a vertical attitude.

[0041] Optionally, after the rocket fairing and satellite are packaged into a vertically aligned satellite-fairing assembly, the management system can instruct the transport ship to transport the satellite-fairing assembly to the target sea area, and instruct the launch ship to transport the rocket to the target sea area. The management system can also obtain the routes for transporting the satellite-fairing assembly and the rocket to the target sea area, and determine the transport time for the satellite-fairing assembly and the rocket respectively based on the sea conditions along the two routes, thereby ensuring that the satellite-fairing assembly and the rocket arrive at the target sea area as simultaneously as possible.

[0042] Optionally, after both the satellite array and the rocket reach the target sea area, the management system controls the satellite array to dock with the rocket as the target component on the launch ship and launches the target component. During the docking process, the satellite array and the rocket can be docked using docking equipment such as hoisting equipment or nesting equipment. The docking equipment is at least one hardware device that makes up the management system.

[0043] It should be noted that because rockets are typically large, they are generally transported horizontally. If the rocket and satellite were docked directly before reaching the target sea area, the requirement for the satellite to be transported vertically would not be met. Therefore, the management system instructs the execution of the first task, ensuring the satellite is transported safely and stably to the target sea area while maintaining a vertical attitude. The rocket, on the other hand, is transported horizontally to the target sea area. Finally, the docking of the rocket and satellite is completed in the target sea area. This ensures that the satellite will not malfunction due to not maintaining a vertical attitude during sea transport, and also enables the docking of the rocket and satellite.

[0044] In step S103, when the mission command instructs the execution of the second mission, the rocket fairing, satellite, and rocket are packaged into a horizontally oriented integral component, and the integral component is launched from the launch ship.

[0045] Optionally, in this embodiment of the application, the second mission is also to send a satellite into space by launching a rocket at sea. However, when the mission command instructs the execution of the second mission, the satellite does not need to be transported in a vertical attitude. Therefore, when executing the second mission, the management system can control the packaging equipment to pre-package the rocket fairing, the satellite, and the rocket into a horizontal overall component. It should be noted that the packaging equipment can be at least one hardware device that makes up the management system, such as welding equipment or cutting equipment with packaging function.

[0046] Optionally, after the rocket fairing, satellite, and rocket are packaged into a horizontally oriented integral component, the management system can instruct the launch ship to transport the integral component horizontally to the target sea area, and then launch the integral component from the launch ship upon arrival at the target sea area.

[0047] Based on the content of steps S101 to S103 above, it can be seen that in this application, the rocket launch mission is divided according to the rocket's transport attitude. First, the mission command corresponding to the rocket is received. The mission command indicates whether to execute a first mission or a second mission. The first mission indicates that the satellite launched by the rocket needs to be transported in a vertical attitude, while the second mission indicates that the satellite launched by the rocket does not need to be transported in a vertical attitude. When the mission command indicates to execute the first mission, the rocket fairing and the satellite are packaged into a vertically oriented satellite-fairing assembly. The satellite-fairing assembly is docked with the rocket on the launch ship as the target component, and the target component is launched. The launch ship is a vessel used to launch rockets. When the mission command indicates to execute the second mission, the rocket fairing, the satellite, and the rocket are packaged into a horizontally oriented integral component, and the integral component is launched from the launch ship.

[0048] As can be seen from the above, this application sets up corresponding docking procedures for rockets and satellites for two scenarios: satellites that need to be transported in a vertical attitude and satellites that do not need to be transported in a vertical attitude. This ensures that different types of satellites can be stably docked with rockets and moved to launch ships. Furthermore, through the standardized design of the docking procedure, the technical effect of shortening the launch cycle of sea-based rocket launch missions is achieved, avoiding a large amount of human interference and solving the technical problem of low efficiency of sea-based rocket launches caused by the lack of standardization in the docking method between rockets and satellites in the prior art.

[0049] In one alternative embodiment, Figure 2 This is a flowchart of an optional task type determination according to an embodiment of this application, such as... Figure 2 As shown, it includes the following steps:

[0050] Step S201: Obtain the list of materials that make up the satellite. The list of materials is used to record the names of N materials that make up the satellite, where N is an integer greater than 1.

[0051] Optionally, the N materials include, but are not limited to, the materials of the satellite's fuel, positioning devices, communication devices, and other components.

[0052] Step S202: Detect whether the name of the target material is included in the list of constituent materials, wherein the target material is the material that needs to maintain stability in a vertical orientation.

[0053] Optionally, the target material can be a specific type of material. For example, the target material could be a type of fuel with poor stability. If a satellite carries this fuel, it needs to maintain a vertical attitude as much as possible to avoid malfunctions caused by the fuel swaying in other attitudes. Alternatively, the target material could be a material used to compose a positioning device, and this positioning device needs to maintain high positioning accuracy in a vertical attitude. Therefore, the satellite equipped with this positioning device needs to maintain a vertical attitude as much as possible during transportation.

[0054] Step S203: If the name of the target material is included in the bill of materials, determine the task instruction to execute the first task.

[0055] In step S204, if the name of the target material is not included in the list of constituent materials, a task instruction is determined to instruct the execution of a second task.

[0056] It should be noted that through the above process, the management system can automatically determine the mission type based on the satellite's material list without requiring manual input. This not only avoids the error-prone problem caused by manual mission type determination but also improves the efficiency of mission type determination.

[0057] In one alternative embodiment, after the satellite array assembly is transported to the target sea area where the launch ship is located by a transport vessel, the management system can adjust the satellite array assembly to a horizontal attitude, and then dock the satellite array assembly in the horizontal attitude with the rocket in the horizontal attitude as the target component.

[0058] Optionally, after the satellite array assembly is transported to the target sea area where the launch ship is located by transport vessels, in order to reduce the difficulty of docking, the management system can use hoisting equipment and other equipment to adjust the satellite array assembly to a horizontal attitude. Then, the satellite array assembly in a horizontal attitude docks with the rocket in a horizontal attitude to form the target component. Finally, the target component is adjusted to a vertical attitude to prepare for launch.

[0059] It should be noted that since the docking operation is relatively short and does not require prolonged turbulence at sea, the satellite-enclosure assembly can be temporarily adjusted to a horizontal attitude. After docking the satellite-enclosure assembly with the rocket as the target component, the target component can be readjusted to a vertical attitude. This minimizes the difficulty of docking the satellite and rocket without affecting the satellite's stability. Since rockets are usually quite large, docking in a horizontal attitude is much less difficult than docking in a vertical attitude.

[0060] In one alternative embodiment, before the satellite array assembly is docked with the rocket as the target component on the launch ship, the management system can move the rocket horizontally to the launch platform using hoisting equipment, then fix the launch platform and the rocket on the launch platform to the launch ship, and control the launch ship to move to the target sea area.

[0061] Optionally, during the execution of the first mission, the rocket and the satellite array are transported to the target sea area respectively. The rocket can be transported directly to the target sea area by the launch ship, and the rocket is fixed in a horizontal position on the launch platform of the launch ship.

[0062] In an alternative embodiment, when the mission command instructs the execution of a second mission, the management system first encapsulates the horizontally oriented rocket fairing and the horizontally oriented rocket into a first component, and then encapsulates the first component and the horizontally oriented satellite into an integral component.

[0063] Optionally, when performing the second mission, since it is not necessary to transport the satellite in a vertical attitude, the horizontally oriented rocket fairing and the horizontally oriented rocket can be packaged into a first component directly on land before heading to the target sea area, and then the first component and the horizontally oriented satellite can be packaged into an integral component.

[0064] It should be noted that horizontal docking of the rocket fairing, rocket, and satellite can reduce the difficulty of docking, thereby improving docking efficiency.

[0065] In one alternative embodiment, after the rocket fairing, satellite, and rocket are packaged into a horizontally oriented integral assembly, the management system can move the integral assembly horizontally to the launch platform, then fix the launch platform and the integral assembly on the launch platform to the launch ship, and control the launch ship to move to the target sea area.

[0066] Optionally, during the second mission, the management system can use hoisting equipment to move the entire component horizontally to the launch platform. Then, the management system uses nesting devices or other equipment with fixing functions to secure the launch platform and the entire component on it to the launch vessel. Finally, after the entire component is successfully secured to the launch vessel, the management system controls the launch vessel to move to the target sea area.

[0067] In an alternative embodiment, the management system may also adjust the target component to a target angle attitude based on the sway amplitude of the launch vessel, and then launch the target component at the target angle attitude.

[0068] Optionally, the target component (i.e., the combination of rocket, rocket fairing, and satellite) needs to be launched at the target angle. However, since the launch ship will sway due to the flow of seawater during sea launch, the swaying amplitude of the launch ship needs to be taken into account when adjusting the target component to the target angle to ensure the accuracy of the target component's attitude and thus guarantee the successful launch of the target component.

[0069] In an alternative embodiment, while performing the second mission, the management system can also adjust the overall component to a target angle attitude based on the sway amplitude of the launch ship, and then launch the overall component at the target angle attitude.

[0070] In one alternative embodiment, Figure 3 This is an execution flowchart of an optional first task according to an embodiment of this application, such as... Figure 3 As shown, the first mission can be divided into three phases: the entry and technical preparation phase, the transfer and boarding and joint training at sea phase, and the docking and launch phase.

[0071] Optionally, such as Figure 3 As shown, during the site entry and technical preparation phase, on the one hand, the rocket and ground equipment enter the site, and then the technical preparation of the rocket is completed, followed by the transfer of the rocket to the launch platform; on the other hand, the satellite and ground equipment enter the site, and then the technical preparation of the satellite is completed, followed by the vertical assembly of the satellite and rocket fairing to obtain the satellite-fairing assembly.

[0072] Optionally, such as Figure 3 As shown, during the transfer and boarding and joint training at sea phases, one aspect is transferring the satellite shield assembly onto the ship; the other aspect is transferring the launch platform carrying the rocket onto the ship (that is, moving the launch platform carrying the rocket onto the launch ship), and then conducting rocket-ship joint training operations (that is, controlling the launch ship to sail while carrying the rocket). After the rocket-ship joint training operations are completed, the launch ship is controlled to sail to the target sea area.

[0073] Optionally, such as Figure 3 As shown, during the docking and launch phase, both the transport ship carrying the satellite array and the launch ship carrying the rocket arrive at the target sea area. The management system controls the satellite array to flip from a vertical position to a horizontal position, and then docks the satellite array with the rocket horizontally. After successful docking, the rocket is launched to send the satellite into space.

[0074] In one alternative embodiment, Figure 4 This is an execution flowchart of an optional second task according to an embodiment of this application, such as... Figure 4 As shown, the second mission can be divided into three phases: preparation phase, transfer and boarding and joint training at sea phase, and launch phase.

[0075] Optionally, such as Figure 4 As shown, during the preparation phase, on one hand, the rocket and ground equipment arrive at the site, and then the horizontal docking operation of the rocket body is completed (that is, the rocket and rocket fairing are horizontally docked as the first component); on the other hand, the satellite and ground equipment arrive at the site, and then the technical preparation of the satellite is completed. Subsequently, the horizontal docking of the satellite and rocket is completed (that is, the first component and the technically prepared satellite are horizontally docked). After that, the full rocket horizontal test is carried out (that is, the overall component consisting of the rocket fairing, satellite and rocket is tested in a horizontal attitude). After the test is completed, the entire rocket (i.e., the overall component) is transferred to the launch platform.

[0076] Optionally, such as Figure 4 As shown, during the transfer and boarding phase and the joint training at sea phase, the launch platform carrying the full rocket is transferred to the launch ship, and then the rocket-ship joint training operation is carried out (i.e., controlling the launch ship to sail while carrying the full rocket). After the rocket-ship joint training operation is completed, the launch ship is controlled to sail to the target sea area.

[0077] Optionally, such as Figure 4 As shown, during the launch phase, the entire rocket is tested in the target sea area, and after the test is completed, the entire rocket is launched.

[0078] In summary, in this embodiment, the rocket launch mission is divided based on the rocket's transport attitude. First, the mission command corresponding to the rocket is received. This mission command indicates either a first mission or a second mission. The first mission indicates that the satellite to be launched by the rocket needs to be transported in a vertical attitude, while the second mission indicates that the satellite to be launched by the rocket does not need to be transported in a vertical attitude. When the mission command indicates the execution of the first mission, the rocket fairing and satellite are encapsulated into a vertically oriented satellite-fairing assembly. The satellite-fairing assembly is docked with the rocket from the launch ship to form the target component, and then launched. The launch ship is a vessel used for launching rockets. When the mission command indicates the execution of the second mission, the rocket fairing, satellite, and rocket are encapsulated into a horizontally oriented integral component, and the integral component is launched from the launch ship.

[0079] As can be seen from the above, this application sets up corresponding docking procedures for rockets and satellites for two scenarios: satellites that need to be transported in a vertical attitude and satellites that do not need to be transported in a vertical attitude. This ensures that different types of satellites can be stably docked with rockets and moved to launch ships. Furthermore, through the standardized design of the docking procedure, the technical effect of shortening the launch cycle of sea-based rocket launch missions is achieved, avoiding a large amount of human interference and solving the technical problem of low efficiency of sea-based rocket launches caused by the lack of standardization in the docking method between rockets and satellites in the prior art.

[0080] According to an embodiment of this application, an embodiment of a rocket launcher is also provided. Figure 5 This is a schematic diagram of an optional rocket launch device according to an embodiment of this application, such as... Figure 5 As shown, the rocket launch device includes: a receiving unit 501, a first mission execution unit 502, and a second mission execution unit 503.

[0081] The receiving unit 501 is used to receive mission instructions corresponding to the rocket, wherein the mission instructions indicate the execution of a first mission or a second mission, the first mission indicating that the satellite launched by the rocket needs to be transported in a vertical attitude, and the second mission indicating that the satellite launched by the rocket does not need to be transported in a vertical attitude; the first mission execution unit 502 is used to encapsulate the rocket fairing and the satellite into a vertically oriented satellite fairing assembly when the mission instructions indicate the execution of the first mission, control the docking of the satellite fairing assembly with the rocket as the target component on the launch ship, and launch the target component, wherein the launch ship is a ship used to launch rockets; the second mission execution unit 503 is used to encapsulate the rocket fairing, the satellite, and the rocket into a horizontally oriented integral component when the mission instructions indicate the execution of the second mission, and launch the integral component on the launch ship.

[0082] Optionally, the rockets mentioned above can be of various types. For example, according to the power plant, the rockets mentioned above include, but are not limited to, nuclear-powered rockets and chemical fuel rockets (including liquid propellant rockets, solid propellant rockets, and hybrid solid-liquid propellant rockets); according to the structural form, the rockets mentioned above include, but are not limited to, tandem rockets and parallel rockets.

[0083] Optionally, the mission instructions corresponding to the rocket described above are used to indicate a first mission or a second mission, wherein the first mission is used to indicate the launch of at least one satellite that needs to be transported in a vertical attitude using a rocket. The second mission is used to indicate the launch of at least one satellite that does not need to be transported in a vertical attitude (e.g., a horizontal attitude) using a rocket.

[0084] Alternatively, the aforementioned satellites can be various types of satellites, such as communication satellites, meteorological observation satellites, etc.

[0085] Optionally, in this embodiment of the application, the first mission is to send a satellite into space by launching a rocket at sea. When the mission command instructs the execution of the first mission, since the satellite needs to be transported in a vertical attitude, the management system (corresponding to the rocket launch device) can control the packaging equipment to pre-package the rocket fairing and the satellite into a vertically oriented satellite fairing assembly. It should be noted that the packaging equipment can be at least one hardware device that makes up the management system, such as welding equipment or cutting equipment with packaging function.

[0086] In addition, since the rocket fairing is designed to be more vertical, encapsulating the rocket fairing and the satellite into a vertically oriented satellite fairing assembly also makes it easier for the satellite to maintain a vertical attitude.

[0087] Optionally, after the rocket fairing and satellite are packaged into a vertically aligned satellite-fairing assembly, the management system can instruct the transport ship to transport the satellite-fairing assembly to the target sea area, and instruct the launch ship to transport the rocket to the target sea area. The management system can also obtain the routes for transporting the satellite-fairing assembly and the rocket to the target sea area, and determine the transport time for the satellite-fairing assembly and the rocket respectively based on the sea conditions along the two routes, thereby ensuring that the satellite-fairing assembly and the rocket arrive at the target sea area as simultaneously as possible.

[0088] Optionally, after both the satellite array and the rocket reach the target sea area, the management system controls the satellite array to dock with the rocket as the target component on the launch ship and launches the target component. During the docking process, the satellite array and the rocket can be docked using docking equipment such as hoisting equipment or nesting equipment. The docking equipment is at least one hardware device that makes up the management system.

[0089] It should be noted that because rockets are typically large, they are generally transported horizontally. If the rocket and satellite were docked directly before reaching the target sea area, the requirement for the satellite to be transported vertically would not be met. Therefore, the management system instructs the execution of the first task, ensuring the satellite is transported safely and stably to the target sea area while maintaining a vertical attitude. The rocket, on the other hand, is transported horizontally to the target sea area. Finally, the docking of the rocket and satellite is completed in the target sea area. This ensures that the satellite will not malfunction due to not maintaining a vertical attitude during sea transport, and also enables the docking of the rocket and satellite.

[0090] As can be seen from the above, this application sets up corresponding docking procedures for rockets and satellites for two scenarios: satellites that need to be transported in a vertical attitude and satellites that do not need to be transported in a vertical attitude. This ensures that different types of satellites can be stably docked with rockets and moved to launch ships. Furthermore, through the standardized design of the docking procedure, the technical effect of shortening the launch cycle of sea-based rocket launch missions is achieved, avoiding a large amount of human interference and solving the technical problem of low efficiency of sea-based rocket launches caused by the lack of standardization in the docking method between rockets and satellites in the prior art.

[0091] Optionally, the rocket launch device further includes: an acquisition unit, a detection unit, a first determination unit, and a second determination unit. The acquisition unit is used to acquire a list of the satellite's constituent materials, wherein the list records the names of N materials that make up the satellite, where N is an integer greater than 1. The detection unit is used to detect whether the list of constituent materials includes the name of a target material, wherein the target material is the material that needs to maintain stability in a vertical attitude. The first determination unit is used to determine, if the list of constituent materials includes the name of the target material, that the mission instruction instructs the execution of a first mission. The second determination unit is used to determine, if the list of constituent materials does not include the name of the target material, that the mission instruction instructs the execution of a second mission.

[0092] Optionally, the target material can be a specific type of material. For example, the target material could be a type of fuel with poor stability. If the satellite carries this fuel, it needs to maintain a vertical attitude as much as possible to avoid malfunctions caused by the fuel swaying in other attitudes. Alternatively, the target material could be a material used to compose a positioning device, and this positioning device needs to maintain high positioning accuracy in a vertical attitude. Therefore, the satellite equipped with this positioning device needs to maintain a vertical attitude as much as possible during transportation.

[0093] It should be noted that through the above process, the mission type can be automatically determined by the satellite's list of constituent materials without the need for human input. This not only avoids the error-prone problem caused by manual mission type determination, but also improves the efficiency of mission type determination.

[0094] Optionally, the first mission execution unit 502 includes: an adjustment subunit and a docking subunit, wherein the adjustment subunit is used to adjust the satellite array assembly to a horizontal attitude after it has been transported to the target sea area where the launch ship is located by the transport ship; the docking subunit is used to dock the satellite array assembly in the horizontal attitude with the rocket in the horizontal attitude as a target component.

[0095] It should be noted that since the docking operation is relatively short and does not require prolonged turbulence at sea, the satellite-enclosure assembly can be temporarily adjusted to a horizontal attitude. After docking the satellite-enclosure assembly with the rocket as the target component, the target component can be readjusted to a vertical attitude. This minimizes the difficulty of docking the satellite and rocket without affecting the satellite's stability. Since rockets are usually quite large, docking in a horizontal attitude is much less difficult than docking in a vertical attitude.

[0096] Optionally, the rocket launch device further includes: a first moving unit and a first control unit. The first moving unit is used to move the rocket horizontally to the launch platform; the first control unit is used to secure the launch platform and the rocket on the launch platform to the launch vessel and control the launch vessel to move to the target sea area.

[0097] Optionally, the second mission execution unit 503 includes: a first packaging subunit and a second packaging subunit. The first packaging subunit is used to package the horizontally oriented rocket fairing and the horizontally oriented rocket into a first component when the mission command instructs the execution of the second mission; the second packaging subunit is used to package the first component and the horizontally oriented satellite into an integral component.

[0098] Optionally, the rocket launch device further includes: a second moving unit and a second control unit, wherein the second moving unit is used to move the overall assembly in a horizontal attitude to the launch platform; and the second control unit is used to fix the launch platform and the overall assembly on the launch platform to the launch ship and control the launch ship to move to the target sea area.

[0099] Optionally, the first mission execution unit 502 includes: a first adjustment subunit and a launch subunit. The first adjustment subunit is used to adjust the target component to a target angle attitude based on the sway amplitude of the launch vessel; the launch subunit is used to launch the target component to the target angle attitude.

[0100] According to another aspect of the embodiments of this application, a computer-readable storage medium is also provided, the computer-readable storage medium including a stored computer program, wherein, when the computer program is running, it controls the device where the computer-readable storage medium is located to execute any of the above-described rocket launch methods.

[0101] According to another aspect of the embodiments of this application, an electronic device is also provided, including: a processor; and a memory for storing executable instructions of the processor; wherein the processor is configured to perform the rocket launch method of any of the above via executing the executable instructions.

[0102] Figure 6 This is a schematic diagram of an electronic device provided according to an embodiment of this application, such as... Figure 6 As shown, this application provides an electronic device, which includes a processor, a memory, and a program stored in the memory and executable on the processor. When the processor executes the program, it implements any of the above-mentioned rocket launch methods.

[0103] The sequence numbers of the embodiments in this application are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0104] In the above embodiments of this application, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0105] In the several embodiments provided in this application, it should be understood that the disclosed technical content can be implemented in other ways. The device embodiments described above are merely illustrative; for example, the division of units can be a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the displayed or discussed mutual couplings, direct couplings, or communication connections may be through some interfaces; indirect couplings or communication connections between units or modules may be electrical or other forms.

[0106] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0107] Furthermore, the functional units in the various embodiments of this application can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0108] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods of the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as a USB flash drive, read-only memory (ROM), random access memory (RAM), portable hard drive, magnetic disk, or optical disk.

[0109] The above are merely preferred embodiments of this application. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of this application, and these improvements and modifications should also be considered within the scope of protection of this application.

Claims

1. A rocket launch method, characterized in that, include: Receive mission instructions corresponding to the rocket, wherein the mission instructions indicate the execution of a first mission or a second mission, the first mission indicates that the satellite launched by the rocket needs to be transported in a vertical attitude, and the second mission indicates that the satellite launched by the rocket does not need to be transported in a vertical attitude; When the mission instruction indicates that the first mission should be performed, the rocket fairing and the satellite are encapsulated into a vertically oriented satellite fairing assembly. The satellite fairing assembly is docked with the rocket as a target component on the launch ship, and the target component is launched. The launch ship is a vessel used to launch the rocket. When the mission instruction directs the execution of the second mission, the rocket fairing, the satellite, and the rocket are encapsulated as a horizontally aligned integral assembly, and the integral assembly is launched from the launch vehicle.

2. The rocket launch method according to claim 1, characterized in that, Before receiving the launch mission command corresponding to the rocket, the rocket launch method further includes: Obtain the list of constituent materials of the satellite, wherein the list of constituent materials is used to record the names of N materials that make up the satellite, where N is an integer greater than 1; Detect whether the list of constituent materials includes the name of a target material, wherein the target material is a material that needs to maintain stability in a vertical orientation; If the name of the target material is included in the list of constituent materials, the task instruction is determined to instruct the execution of the first task; If the name of the target material is not included in the list of constituent materials, the task instruction is determined to instruct the execution of the second task.

3. The rocket launch method according to claim 1, characterized in that, Controlling the docking of the satellite array with the rocket from the launch ship as the target assembly includes: After the satellite array assembly is transported to the target sea area where the launch ship is located by the transport vessel, the satellite array assembly is adjusted to a horizontal attitude; The satellite shield assembly in a horizontal orientation is docked with the rocket in a horizontal orientation to form the target component.

4. The rocket launch method according to claim 3, characterized in that, Before the launch vessel controls the satellite array assembly to dock with the rocket as the target component, the rocket launch method further includes: Move the rocket horizontally to the launch platform; The launch platform and the rocket on the launch platform are secured to the launch ship, and the launch ship is controlled to move to the target sea area.

5. The rocket launch method according to claim 1, characterized in that, When the mission instruction directs the execution of the second mission, the rocket fairing, the satellite, and the rocket are encapsulated as a horizontally aligned integral assembly, including: When the mission instruction indicates that the second mission should be performed, the horizontally oriented rocket fairing and the horizontally oriented rocket are encapsulated as a first component; The first component and the horizontally oriented satellite are packaged together as the overall component.

6. The rocket launch method according to claim 1, characterized in that, After encapsulating the rocket fairing, the satellite, and the rocket into a horizontally aligned integral assembly, the rocket launch method includes: The entire assembly is moved to the launch platform in a horizontal orientation; The launch platform and its components are secured to the launch vessel, and the launch vessel is controlled to move to the target sea area.

7. The rocket launch method according to claim 1, characterized in that, Launching the target component from the launch vessel includes: The target component is adjusted to the target angle attitude based on the sway amplitude of the launch vessel; The target component is launched at the target angle.

8. A rocket launching device, characterized in that, include: A receiving unit is used to receive mission instructions corresponding to the rocket, wherein the mission instructions indicate the execution of a first mission or a second mission, the first mission indicates that the satellite launched by the rocket needs to be transported in a vertical attitude, and the second mission indicates that the satellite launched by the rocket does not need to be transported in a vertical attitude. The first mission execution unit is configured to, when instructed by the mission command to execute the first mission, encapsulate the rocket fairing and the satellite into a vertically oriented satellite fairing assembly, control the satellite fairing assembly to dock with the rocket as a target component on the launch ship, and launch the target component, wherein the launch ship is a vessel used to launch the rocket; The second mission execution unit is used to encapsulate the rocket fairing, the satellite, and the rocket into a horizontally aligned integral assembly when the mission instruction indicates that the second mission should be executed, and to launch the integral assembly from the launch ship.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program, wherein when the computer program is executed, it controls the device containing the computer-readable storage medium to perform the rocket launch method according to any one of claims 1 to 7.

10. An electronic device, characterized in that, It includes one or more processors and a memory, the memory being used to store one or more programs, wherein when the one or more programs are executed by the one or more processors, the one or more processors cause the one or more processors to implement the rocket launch method according to any one of claims 1 to 7.

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