Data processing method, system, electronic equipment and medium for manned space launch

Abstract

The present invention relates to the field of space launch technology and provides a data processing method, system, electronic device, and medium for manned space launches. The method comprises the following steps: S1: obtaining a set of technical and process items for manned space launch duty; S2: obtaining four modes of manned space launch duty; S3: setting a safe recovery point; S4: setting a set of launch technical and process items corresponding to the four modes; S5: obtaining current launch conditions; if the emergency rescue launch conditions are met, launching is carried out in accordance with the emergency rescue technical and process item set; S6: if the conventional rescue launch conditions are met, launching is carried out in accordance with the conventional rescue technical and process item set; S7: during the launch process, if the emergency rescue launch conditions are met, launching is carried out in accordance with the emergency rescue technical and process item set; if the conventional rescue launch conditions are met, launching is carried out in accordance with the conventional rescue technical and process items; S8: repeating S5 to S7 until the launch is completed. This solution minimizes the mission process cycle while ensuring reliability and safety.

Description

Technical Field

[0001] The present invention relates to the field of space launch technology, and in particular to a data processing method, system, electronic equipment and medium for manned space launch. Background Art

[0002] When a spacecraft reentry capsule malfunctions on a manned space station, a new, intact spacecraft must be quickly launched from the ground and docked with the station to prevent the astronauts from being stranded. For example, on June 5, 2024, two American astronauts were stranded on the International Space Station for eight months due to a spacecraft malfunction and have been unable to return.

[0003] The production and launch preparation cycles for manned spacecraft and their carrier rockets are relatively long (production cycles exceeding three months, and launch preparation cycles approximately 50 days). The preparation of the test launch process flow is based on the test launch processes of previous space launch missions, the logistics procedures for space products (including manned spacecraft, carrier rockets, etc.) at the launch site, the technical requirements of each system for the launch site, the technical status and processes, and the launch site work procedures. The preparation process is as follows:

[0004] Step 1: Identify work items. For each mission system, including the spacecraft, vehicle, payload, and astronauts, perform a structural decomposition of the system's primary work at the launch site. Analyze each work activity and its logical relationships, as well as the resource requirements and support conditions at the launch site. Prioritize the primary work activities, estimate their duration, and create a list of key work items.

[0005] Step 2: Define the work content and timeline. Based on the main project work list provided by each system, the technical requirements of each system for the launch site, and other relevant technical documents, summarize the work content of each system, analyze the logical relationships between the various tasks, conduct system-wide work sequencing and parallel work project analysis, and estimate the project duration.

[0006] Step 3: Draw a process flow diagram. Based on the work structure breakdown, work item list, product logistics procedures, and resource provision, draw a test launch process flow diagram. Based on the product logistics diagram, the test launch process flow diagram clarifies the key tasks, logistics direction, information flow, and work area of ​​the space product at the launch site, using the list of key work items and their logical relationships. Essentially, it's a simplified process flow.

[0007] Step 4: Analyze the main work lines. The analysis of the main work lines is the process of finding the critical path in the planning network diagram. Based on the experience of previous space launch projects, the work before the docking of the spacecraft and the carrier is mainly based on the activities of the spacecraft at the launch site, while the work after the docking is mainly based on the activities of the assembly.

[0008] Step 5: Draw a preliminary draft of the test launch process flow. Based on the launch site tasks and their logical relationships, process flow diagrams, parallel work analysis, duration estimates, and resource support information, the draft test launch process flow is drawn, with the spacecraft approach as the starting point and the mainline work as the key path. The work of other systems is based on the mainline work as the benchmark.

[0009] Step 6: Clarify the quality review of key nodes. After the initial draft of the process is completed, it is necessary to analyze the key nodes of task implementation, clarify the quality control measures of key nodes, and mark them in the flow chart.

[0010] Step 7: Explain the arrangement of relevant process items. The test launch process should also explain the special items in the process development process, such as the arrangement of the total process time, the participating systems and status of the joint general inspection items, changes and adjustments to the test items, radio startup timing, command and dispatch calls, etc.

[0011] Step 8: Process Review and Approval. After the initial draft of the test and launch process is completed, it undergoes multiple rounds of discussions and consultations with each system. Once consensus is reached, the chief engineers of each system will sign and approve the draft process. This draft process is then submitted to the General Office of Aerospace Engineering. The General Office of Aerospace Engineering organizes a test and launch process review meeting, with the review committee composed of the chief engineers of each system. Once the process passes the review, it is approved by the Chief Engineer for implementation.

[0012] The existing technology does not take into account the existence of multiple modes in on-duty launches, resulting in the process design method being unable to meet the actual needs of the project; it does not take into account the different requirements for reliability and safety under different modes, resulting in the designed process being a "closed system" that cannot adapt well to various changing situations; it does not take into account the fact that on-duty aerospace products are always in good condition at the launch site, resulting in too many assembly and test items being arranged and the corresponding duration being too long; it does not take into account the extreme cases of the mission process cycle, that is, how to use the shortest process cycle while ensuring basic reliability and safety.

[0013] Therefore, it is necessary to provide a data processing method, system, electronic equipment and medium for manned space launch, which can fully consider all modes of on-duty launch (initial state, rolling, conventional rescue and emergency rescue), so that the process design method can meet the actual needs of on-duty launch; fully consider the different requirements for reliability and safety under different modes of on-duty launch, so that the process design can adapt well to various changing situations; fully consider the actual situation that on-duty aerospace products (manned spacecraft and launch vehicles) are always in good condition at the launch site, optimize assembly test items, and shorten the duration of corresponding work items; fully consider the extreme situations of emergency rescue, and make the mission process cycle as short as possible while ensuring basic reliability and safety.

[0014] The above information disclosed in this Background section is only for enhancement of understanding of the background of the application and therefore it may contain information that does not form the prior art that is already known to a person of ordinary skill in the art. Summary of the Invention

[0015] The main purpose of the present invention is to overcome the problem of long rocket launch cycle, and to provide a data processing method, system, electronic equipment and medium for manned space launch, which can fully consider all modes of on-duty launch (initial state, rolling, conventional rescue and emergency rescue), so that the process design method can meet the actual needs of on-duty launch; fully consider the different requirements for reliability and safety under different modes of on-duty launch, so that the process design can adapt well to various changing situations; fully consider the actual situation that on-duty aerospace products (manned spacecraft and carrier rockets) are always in good condition at the launch site, optimize assembly and test items, and shorten the duration of corresponding work items; fully consider the extreme situations of emergency rescue, and make the mission process cycle as short as possible while ensuring basic reliability and safety.

[0016] To achieve the above-mentioned purpose, the present invention provides a first aspect of a data processing method for a manned space launch, comprising the following steps:

[0017] S1: Obtain the manned space duty launch technology and process item set according to the conventional single manned space test launch standardization process (CSLP);

[0018] S2: Obtain four modes of manned space launch duty, namely initial launch, rolling launch, conventional rescue and emergency rescue;

[0019] S3: Set a safe recovery point;

[0020] S4: Based on the manned space duty launch technology and process item set and the safety recovery point, four launch technology and process item sets corresponding to different modes are set, namely the initial launch technology and process item set, the rolling launch technology and process item set, the conventional rescue technology and process item set, and the emergency rescue technology and process item set; the safety recovery point is in the launch technology and process item set corresponding to each mode;

[0021] S5: Obtain the current launch conditions, which include initial launch conditions, rolling launch conditions, conventional rescue launch conditions, and emergency rescue launch conditions. If the emergency rescue launch conditions are met, the launch is carried out according to the emergency rescue technical process item set. If there are no manned spacecraft and carrier rockets on duty at the launch site, the duty launch enters the initial launch mode.

[0022] S6: If the conditions for conventional rescue launch are met, the launch is carried out according to the conventional rescue technical process item set. If there is no manned spacecraft and carrier rocket on duty at the launch site, the on-duty launch enters the initial launch mode;

[0023] S7: During the initial launch, rolling launch, or conventional rescue process, at a safety recovery point, if the emergency rescue launch conditions are met, the current procedure is suspended and the launch is carried out according to the emergency rescue technical process item set; during the initial launch or rolling launch, at a safety recovery point, if the conventional rescue launch conditions are met, the current procedure is suspended and the launch is carried out according to the conventional rescue technical process item set;

[0024] S8: Repeat steps S5 to S7 until the launch is completed.

[0025] As an exemplary embodiment of the present invention, in step S1, the set of manned space launch technology and process items includes but is not limited to:

[0026] SD 1-1 : Determine the manned spacecraft on duty and the manned spacecraft in flight;

[0027] SD 1-2 : Designate duty manned spacecraft and manned spacecraft for flight;

[0028] SD2: manned spacecraft duty status setting;

[0029] SD3: Status maintenance of manned spacecraft on duty;

[0030] SD4: The duty status of the manned spacecraft on duty is lifted and the state is changed to the flight spacecraft state;

[0031] SD5: Manned spacecraft transfer launch area;

[0032] RD 1-1 : Determine the launch vehicle on duty and the launch vehicle to be flown;

[0033] RD 1-2 : Designate duty manned spacecraft and manned spacecraft for flight;

[0034] RD2: Launch vehicle duty status setting;

[0035] RD3: duty launch vehicle status maintenance;

[0036] RD4: The duty status of the on-duty launch vehicle is lifted and the status is changed to the flight rocket status;

[0037] RD5: Launch vehicle transfer area;

[0038] SR1: Ship-rocket launch area docking;

[0039] MD1: On-duty personnel, assemble.

[0040] As an example embodiment of the present invention, in step S2, the initial launch is that two manned spacecraft enter the launch site at the same time, one of which performs a flight mission and the other is on duty; two carrier rockets enter the launch site at the same time, one of which performs a flight mission and the other is on duty;

[0041] The rolling launch means that one manned spacecraft enters the launch site, passes the assembly test and is put into the duty state, and the spacecraft on duty performs the flight mission; one carrier rocket enters the launch site, passes the assembly test and is put into the duty state, and the carrier rocket on duty performs the flight mission;

[0042] The conventional rescue is that the spacecraft and carrier rocket on duty enter the conventional rescue launch procedure;

[0043] The emergency rescue is for the spacecraft and carrier rocket on duty to enter the emergency rescue launch procedure.

[0044] As an exemplary embodiment of the present invention, in step S3, the safety recovery point of the on-duty manned spacecraft is set to before the spacecraft is refueled, and the safety recovery point of the on-duty carrier rocket is set to before the ship-rocket docking.

[0045] As an exemplary embodiment of the present invention, in step S4, the method for setting the initial emission technology process item set includes:

[0046] S411: From the process start point to the safety recovery point, intercept the manned spacecraft technology process project SC in the conventional single manned space test launch standard process CSLP Ω- , by SD 1-1 , SC Ω- , SD2, SD3 constitute the manned spacecraft duty technical process project set Φ SD-1 ;

[0047] S412: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by R.D. 1-1 、R CΩ- , RD2, and RD3 constitute the manned space flight technology and process project set Φ RD-1 ;

[0048] S413: Take the manned spacecraft duty technical process project set Φ SD-1 and manned space flight technology and process project setΦ RD-1 , design duty process draft DDP1;

[0049] S414: Based on the duty process draft DDP1 and the conventional single manned space test launch standard process CSLP, the mission process draft for the initial launch is formed;

[0050] S415: Based on the draft mission process flow for the initial launch, the conflicts among disposal resources, time and technical process items, a set of initial launch technical process items is formed;

[0051] The method for setting up the rolling launch technology process project set includes:

[0052] S421: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by SD 1-2 , SC Ω- , SD2, SD3 constitute the manned spacecraft duty technical process project set Φ SD-2 ;

[0053] S422: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by R.D. 1-2 RC Ω- , RD2, and RD3 constitute the manned space flight technology and process project set Φ RD-2 ;

[0054] S423: Take the manned spacecraft duty technical process project set Φ SD-2 and manned space flight technology and process project setΦ RD-2 , design duty process draft DDP2;

[0055] S424: From the safety recovery point to the end of the process, intercept the launch vehicle technology process project SC in the conventional single manned space test launch standard process CSLP Ω+ , by SD4, SC Ω+ Composition of the manned spacecraft flight technology process project setΦ SD-3 ;

[0056] S425: From the safety recovery point to the end of the process, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω+ , by RD4, RC Ω+ Composition of manned space flight technology and process project setΦ RD-3 ;

[0057] S426: Take the manned spacecraft flight technology process project set Φ SD-3 and manned space flight technology and process project setΦ RD-3 , design and execute the flight process draft EDP1;

[0058] S427: Based on the duty process draft DDP2 and the flight process draft EDP1, the mission process draft for rolling launch is constructed;

[0059] S428: Based on the draft of the mission process flow for rolling launch, the conflicts among disposal resources, time and technical process items, a rolling launch technical process item set is formed;

[0060] The setting method of conventional rescue technical process item set includes:

[0061] S431: Obtain the process flow project set of manned conventional rescue launch mission Φ CR-1 :

[0062] MD1: Duty personnel assemble;

[0063] SD4: The duty status of the manned spacecraft on duty is lifted and the state is changed to the flight spacecraft state;

[0064] SD 4-1 : Refueling of manned spacecraft;

[0065] SD 4-2 : Manned spacecraft buckle cover;

[0066] SD5: The manned spacecraft is transferred to the rocket testing area;

[0067] RD4: The duty status of the on-duty launch vehicle is lifted and the status is changed to the flight launch vehicle status;

[0068] SR1-1: Ship-rocket technical area docking;

[0069] SR2: Ship-rocket combination transfer launch area;

[0070] SR3: Joint ship-rocket inspection;

[0071] SD6: refueling and launching of the launch vehicle;

[0072] S432: Take the manned conventional rescue launch mission process project set Φ CR-1 , design the draft mission process CRP for conventional rescue launch;

[0073] S433: Based on the CRP draft of the mission process for conventional rescue launch, the conflicts among disposal resources, time and technical process items, a set of conventional rescue technical process items is formed;

[0074] The setting methods of emergency rescue technical process project set include:

[0075] S441: Obtain the manned emergency rescue launch mission process project set Φ ER-1 :

[0076] MD1: Duty personnel assemble;

[0077] SD4: The duty status of the manned spacecraft on duty is lifted and the state is changed to the flight spacecraft state;

[0078] SD 4-1 : Refueling of manned spacecraft;

[0079] SD 4-2 : Manned spacecraft buckle cover;

[0080] SD5: Manned spacecraft transfer launch area;

[0081] RD4: The duty status of the on-duty launch vehicle is lifted and the status is changed to the flight launch vehicle status;

[0082] RD5: Launch vehicle transfer area;

[0083] SR 1-2 : Ship-rocket launching area docking;

[0084] SR3: Joint ship-rocket inspection;

[0085] SD6: refueling and launching of the launch vehicle;

[0086] S442: Get the manned emergency rescue launch mission process project set Φ ER-1 , design the mission process draft ERP for emergency rescue launch;

[0087] S443: Based on the draft ERP of the mission process flow for emergency rescue launch, handling resources, time and conflicts among technical process items, form an emergency rescue technical process item set.

[0088] As an example embodiment of the present invention, in step S5, the initial launch condition is a manned space launch in a normal state, and there is no manned spacecraft and carrier rocket on duty at the launch site;

[0089] Rolling launch conditions are normal manned space launches, and the launch site has manned spacecraft and corresponding carrier rockets on duty;

[0090] The conditions for a conventional rescue launch are that the return capsule parked at the manned space station fails, there are manned spacecraft and corresponding carrier rockets on duty at the launch site, and the astronauts in the space station have enough time to wait for a new manned spacecraft to arrive at the space station;

[0091] The conditions for emergency rescue launch are that the return capsule parked at the manned space station malfunctions, there are manned spacecraft and corresponding carrier rockets on duty at the launch site, and the astronauts in the space station need to return as soon as possible.

[0092] As a second aspect of the present invention, the present invention provides a data processing system for manned space launch, comprising:

[0093] The project acquisition module is used to obtain the manned space duty launch technology and process project set according to the conventional single manned space test launch standardization process CSLP;

[0094] The launch technology and process item set generation module is used to obtain the four modes of manned space duty launch, namely initial launch, rolling launch, conventional rescue and emergency rescue; set safety recovery points; set the launch technology and process item sets corresponding to the four modes according to the manned space duty launch technology and process item set and the safety recovery points, namely initial launch technology and process item set, rolling launch technology and process item set, conventional rescue technology and process item set and emergency rescue technology and process item set; the safety recovery points are in the launch technology and process item set corresponding to each mode;

[0095] The launch condition acquisition module is used to obtain the current launch conditions, which include initial launch conditions, rolling launch conditions, conventional rescue launch conditions, and emergency rescue launch conditions;

[0096] The launch execution module is used to determine the launch conditions. If the emergency rescue launch conditions are met, the launch is carried out in accordance with the emergency rescue technical process item set. If there are no manned spacecraft and carrier rockets on duty at the launch site, the on-duty launch enters the initial launch mode. If the conventional rescue launch conditions are met, the launch is carried out in accordance with the conventional rescue technical process item set. If there are no manned spacecraft and carrier rockets on duty at the launch site, the on-duty launch enters the initial launch mode. During the implementation of the initial launch, rolling launch or conventional rescue, at the safety recovery point, if the emergency rescue launch conditions are met, the current program is suspended and the launch is carried out in accordance with the emergency rescue technical process item set. During the implementation of the initial launch and rolling launch, at the safety recovery point, if the conventional rescue launch conditions are met, the current program is suspended and the launch is carried out in accordance with the conventional rescue technical process items. Repeat the judgment of the launch conditions and the mode conversion until the launch is completed.

[0097] As a third aspect of the present invention, the present invention provides an electronic device, comprising:

[0098] one or more processors;

[0099] a storage device for storing one or more programs;

[0100] When the one or more programs are executed by the one or more processors, the one or more processors are enabled to implement the data processing method for manned space launch.

[0101] As a fourth aspect of the present invention, the present invention provides a computer-readable medium having a computer program stored thereon, which implements the data processing method for manned space launch when the program is executed by a processor.

[0102] The advantages of the present invention are:

[0103] Aiming at the special need of space station rescue, the present invention develops a new space launch mode - on-duty launch (i.e., a space product is stored at the launch site and is on standby duty. Once a launch mission is received, it only needs to complete major tasks such as ship-rocket docking, refueling, and key indicator testing, and can be launched in a relatively short time). It proposes and solves the problem of designing the technical process flow for manned space on-duty launch, and divides manned space on-duty launch into four modes, namely initial launch, rolling launch, conventional rescue, and emergency rescue, so that the design of the technical process flow for manned space on-duty launch is more targeted. This solution designs corresponding technical process flow frameworks and the use conditions of each process flow for the four modes of manned space launch, which can significantly improve the work efficiency of manned space on-duty launch. This solution breaks the "one-time design, lifelong validity" development model of the existing technical solution, so that the technical process flow of each manned space launch can be quickly reconstructed according to the specific circumstances and changes of the mission. BRIEF DESCRIPTION OF THE DRAWINGS

[0104] The above and other objects, features, and advantages of the present application will become more apparent by describing in detail exemplary embodiments thereof with reference to the accompanying drawings. The drawings described below are merely some embodiments of the present application, and it is apparent to those skilled in the art that other drawings can be derived from these drawings without inventive effort.

[0105] Figure 1 The diagram schematically shows the steps of a method for processing data for a manned space launch.

[0106] Figure 2 The flowchart of the data processing method for manned space launch is schematically shown.

[0107] Figure 3 The figure schematically shows a structural diagram of an electronic device.

[0108] Figure 4 A diagram schematically illustrates the structure of a computer-readable medium. DETAILED DESCRIPTION

[0109] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be embodied in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete and will fully convey the concepts of the example embodiments to those skilled in the art. Like reference numerals in the drawings represent like or similar parts, and thus repetitive description thereof will be omitted.

[0110] In addition, described feature, structure or characteristic can be combined in one or more embodiments in any suitable manner.In the following description, many specific details are provided so as to provide a full understanding of the embodiments of the present application. However, it will be appreciated by those skilled in the art that the technical scheme of the present application can be put into practice without one or more of the specific details, or other methods, components, devices, steps etc. can be adopted. In other cases, known methods, devices, implementations or operations are not shown or described in detail to avoid blurring the various aspects of the application.

[0111] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically separate entities. That is, these functional entities may be implemented in software, in one or more hardware modules or integrated circuits, or in different networks and / or processor devices and / or microcontroller devices.

[0112] The flowcharts shown in the accompanying drawings are for illustrative purposes only and do not necessarily include all contents and operations / steps, nor must they be executed in the order described. For example, some operations / steps may be decomposed, while others may be combined or partially combined. Therefore, the actual execution order may vary depending on the actual situation.

[0113] It should be understood that although the terms first, second, third, etc. 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. Thus, the first component discussed below could be referred to as the second component without departing from the teachings of the present invention. As used herein, the term "and / or" includes any one and all combinations of one or more of the associated listed items.

[0114] Those skilled in the art will understand that the drawings are merely schematic diagrams of example embodiments, and the modules or processes in the drawings are not necessarily necessary for implementing the present application, and therefore cannot be used to limit the scope of protection of the present application.

[0115] According to a first specific embodiment of the present invention, the present invention provides a data processing system for manned space launch, including: a project acquisition module, a launch technology process project set generation module, a launch condition acquisition module, and a launch execution module.

[0116] The project acquisition module is used to obtain the manned space duty launch technology and process project set according to the conventional single manned space test launch standard process CSLP.

[0117] The launch technology and process project set generation module is used to obtain the four modes of manned space duty launch: initial launch, rolling launch, conventional rescue, and emergency rescue; set safety recovery points; and, based on the manned space duty launch technology and process project set and safety recovery points, set launch technology and process project sets corresponding to the four modes: initial launch technology and process project set, rolling launch technology and process project set, conventional rescue technology and process project set, and emergency rescue technology and process project set; the safety recovery points are included in the launch technology and process project set corresponding to each mode. Modes refer to the different states of the space launch system in different mission contexts. The four modes of duty launch represent a brand-new, full-process design technology tailored for the needs of duty launch.

[0118] The launch condition acquisition module is used to obtain the current launch conditions, which include initial launch conditions, rolling launch conditions, conventional rescue launch conditions and emergency rescue launch conditions.

[0119] The launch execution module is used to determine the launch conditions. If the emergency rescue launch conditions are met, the launch is carried out in accordance with the emergency rescue technical process item set. If there are no manned spacecraft and carrier rockets on duty at the launch site, the on-duty launch enters the initial launch mode. If the conventional rescue launch conditions are met, the launch is carried out in accordance with the conventional rescue technical process item set. If there are no manned spacecraft and carrier rockets on duty at the launch site, the on-duty launch enters the initial launch mode. During the implementation of the initial launch, rolling launch or conventional rescue, at the safety recovery point, if the emergency rescue launch conditions are met, the current program is suspended and the launch is carried out in accordance with the emergency rescue technical process item set. During the implementation of the initial launch and rolling launch, at the safety recovery point, if the conventional rescue launch conditions are met, the current program is suspended and the launch is carried out in accordance with the conventional rescue technical process items. The launch conditions are repeatedly determined and the mode is switched until the launch is completed.

[0120] As a second specific embodiment of the present invention, the present invention provides a data processing method for manned space launch, which adopts the data processing system for manned space launch of the first specific embodiment and mainly adopts switching of four launch modes as follows:

[0121] Initial emission:

[0122] Step 1: Use the initial launch technology process design method to complete the corresponding process design;

[0123] Step 2: Launch according to the initial launch technical process;

[0124] Step 3: After that, the manned spacecraft and carrier rocket at the launch site enter the duty state, and the duty launch enters the rolling launch mode.

[0125] Scroll Launch:

[0126] Step 1: Use the rolling launch technology process design method to complete the corresponding process design;

[0127] Step 2: Launch according to the rolling launch technology process;

[0128] Step 3. After this, the manned spacecraft and carrier rocket at the launch site remain on duty, and the duty launch remains in rolling launch mode.

[0129] Conventional rescue:

[0130] Step 1: Meet the conventional rescue launch conditions and use the conventional rescue launch technical process design method to complete the corresponding process design;

[0131] Step 2: Launch according to the conventional rescue launch technology process;

[0132] Step 3: After this, there are no manned spacecraft and carrier rocket on duty at the launch site, and the on-duty launch enters the initial launch mode.

[0133] Emergency rescue:

[0134] Step 1: Meet the emergency rescue launch conditions and use the emergency rescue launch technical process design method to complete the corresponding process design;

[0135] Step 2: Launch according to the emergency rescue launch technical process;

[0136] Step 3: After this, there are no manned spacecraft and carrier rocket on duty at the launch site, and the on-duty launch enters the initial launch mode.

[0137] Specifically:

[0138] The data processing method of the manned space launch in the second specific embodiment is as follows: Figure 1 and Figure 2 As shown, the following steps are included:

[0139] S1: Obtain the set of manned space duty launch technology and process items according to the conventional single manned space test launch standard process (CSLP).

[0140] Taking the conventional single manned space test launch specification process CSLP as the technical baseline, confirm the conventional manned space launch technology process project set, denoted as Φ (0) The conventional manned space launch technology and process item set is used as the basic set, and the following additional technology and process item sets are added to form the manned space duty launch technology and process item set Φ( 1 ).

[0141] That is, the manned space duty launch technology and process project set includes the conventional manned space launch technology and process project set and the additional technology and process project set.

[0142] The Conventional Single Manned Space Test Launch Procedure (CSLP) is a standardized procedure for single manned space launches that has been gradually improved and formed since the Shenzhou 5 launch. Its main work items include:

[0143] 1. Manned spacecraft (i.e. manned spacecraft technology project SC Ω- ):

[0144] The three cabins of the spacecraft are transported to the launch site, and the status of the cabins and individual transport equipment are inspected;

[0145] Final assembly of orbital module, return module and propulsion module;

[0146] Three-cabin docking and whole-ship orientation measurement;

[0147] Power on and status check of the entire ship's equipment;

[0148] Subsystem inspection and interface matching test between subsystems;

[0149] Whole ship model flight test and special test;

[0150] Loading of astronauts and application system onboard equipment;

[0151] Inspection of voice and image transmission of the sky-ground loop;

[0152] Spacecraft sorting and transfer;

[0153] Propellant filling and propellant gas cylinder charging;

[0154] The straps are installed and tightened and handed over to the rocket system for cover fastening.

[0155] 2. Launch vehicle (i.e. launch vehicle technology and process project RC Ω- ):

[0156] Transport the rocket to the launch site, restore its status and hand over the rocket body;

[0157] Lifting and docking;

[0158] Subsystem and matching stage testing;

[0159] General inspection and testing of technical areas;

[0160] escape tower assembly and testing;

[0161] Ship cover assembly transfer and docking, escape tower docking;

[0162] Propellant filling.

[0163] 3. Full system:

[0164] The ship-rocket combination is vertically transported to the launch area;

[0165] Full system launch drill;

[0166] Organize pre-launch inspection and launch according to the launch procedures.

[0167] Additional technical process project sets include:

[0168] SD 1-1 : Determine the manned spacecraft on duty and the manned spacecraft in flight; determine through technical review which spacecraft will take on the duty mission and which spacecraft will perform the flight mission.

[0169] SD 1-2 : Designate the manned spacecraft on duty and the manned spacecraft in flight; usually the newly arrived manned spacecraft takes on the duty mission, and the manned spacecraft on duty at the launch site performs the flight mission.

[0170] SD2: Setting the duty status of manned spacecraft; clarify the status of the manned spacecraft on duty during the duty period and complete its settings.

[0171] SD3: Status maintenance of manned spacecraft on duty.

[0172] SD4: The duty status of the manned spacecraft on duty is lifted and transferred to the flight spacecraft status.

[0173] SD5: Manned spacecraft transfers to the launch area.

[0174] RD 1-1 : Determine the on-duty launch vehicle and the flight launch vehicle; determine through technical review which rocket will undertake the on-duty mission and which rocket will perform the flight mission.

[0175] RD 1-2 : Designate the manned spacecraft on duty and the manned spacecraft in flight; usually the newly arrived launch vehicle is responsible for the duty mission; the launch vehicle on duty at the launch site performs the flight mission.

[0176] RD2: Launch vehicle duty status setting; clarify the status of the launch vehicle on duty during the duty period and complete its settings.

[0177] RD3: Maintaining the status of the on-duty launch vehicle.

[0178] RD4: The duty status of the on-duty carrier rocket is lifted and transferred to the flight rocket status.

[0179] RD5: Launch vehicle transfer area.

[0180] SR1: Ship-rocket docking at the launch area.

[0181] MD1: On-duty personnel, assemble.

[0182] S2: Obtain four modes of manned space launch duty, namely initial launch, rolling launch, conventional rescue and emergency rescue.

[0183] The first mode is the initial launch, which involves two manned spacecraft entering the launch site simultaneously, with one on a flight mission and the other on duty. Alternatively, two carrier rockets will enter the launch site simultaneously, with one on a flight mission and the other on duty. Implementation conditions: A normal manned space launch, with no manned spacecraft or carrier rockets on duty at the launch site.

[0184] The second mode is rolling launch. A manned spacecraft enters the launch site, passes assembly and testing, and then transitions to a duty state. The spacecraft on duty then carries out the mission. A carrier rocket enters the launch site, passes assembly and testing, and then transitions to a duty state. The carrier rocket on duty then carries out the mission. Implementation conditions: A normal manned space launch, with a manned spacecraft and corresponding carrier rocket on duty at the launch site.

[0185] The third mode is conventional rescue, in which the on-duty spacecraft and launch vehicle initiate a conventional rescue launch procedure. This occurs if a return capsule malfunctions at the manned space station, there are on-duty manned spacecraft and corresponding launch vehicles at the launch site, and the astronauts at the space station have sufficient time to wait for a new manned spacecraft to arrive. This sufficient time is greater than the cycle time required for a conventional rescue launch.

[0186] The fourth mode, emergency rescue, involves the on-duty spacecraft and launch vehicle entering the emergency rescue launch sequence. This occurs if a return capsule malfunctions at the manned space station, there are on-duty manned spacecraft and corresponding launch vehicles at the launch site, and the astronauts on board need to return as quickly as possible.

[0187] like Figure 2 As shown, Figure 2 The emission process of four modes is shown.

[0188] S3: Set a safe recovery point.

[0189] Set the safety recovery point Ω, which is the state when the duty spacecraft and the duty carrier rocket enter the rescue launch procedure.

[0190] The safety recovery point for the on-duty manned spacecraft is set before the spacecraft is refueled, and the safety recovery point for the on-duty carrier rocket is set before the ship-rocket docking.

[0191] The safe recovery points of other systems are set based on the need to effectively ensure the safe recovery points of manned spacecraft and launch vehicles. Other systems include: launch site system, measurement and control communication system, astronaut system, return landing site system, etc.

[0192] like Figure 2 As shown, Ω refers to the safe recovery point, CSLP Ω+ It is the work item of the program after the safe recovery point, CSLP Ω- It is the work item of the program before the safe recovery point.

[0193] S4: According to the manned space duty launch technology and process item set and the safety recovery point, four launch technology and process item sets corresponding to the modes are set, namely the initial launch technology and process item set, the rolling launch technology and process item set, the conventional rescue technology and process item set, and the emergency rescue technology and process item set; the safety recovery point is in the launch technology and process item set corresponding to each mode.

[0194] The method for setting up the initial launch technology process project set includes:

[0195] S410: Two manned spacecraft and two launch vehicles enter the site, and take the manned space launch technology and process project set Φ (1) , the manned space launch technology and process project set Φ (1) Including the conventional single manned space test launch standard process CSLP.

[0196] S411: From the process start point to the safety recovery point, intercept the manned spacecraft technology process project SC in the conventional single manned space test launch standard process CSLP Ω- , by SD 1-1 , SC Ω- , SD2, SD3 constitute the manned spacecraft duty technical process project set Φ SD-1 ; The starting point of the process is the time when the spacecraft enters the launch site;

[0197] S412: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by R.D. 1-1 RC Ω- , RD2, and RD3 constitute the manned space flight technology and process project set Φ RD-1 ;

[0198] S413: Take the manned spacecraft duty technical process project set Φ SD-1 and manned space flight technology and process project setΦ RD-1 , design duty process draft DDP1;

[0199] S414: Based on the duty process draft DDP1 and the conventional single manned space test launch standard process CSLP, the mission process draft for the initial launch is formed;

[0200] S415: Based on the draft mission process flow for initial launch, disposal resources, time and conflicts among technical process items, a set of initial launch technical process items is formed.

[0201] In S415, "time" refers to the time required to implement a technical project. Technical projects require resources and time to implement. To ensure that resources and time are adequate for implementation, conflicts between these two requirements must be resolved through coordination. For example, the time required to charge a spacecraft battery during initial launch, rolling launch, and conventional rescue launch is significantly longer than during emergency rescue launch.

[0202] Figure 2 The leftmost node of the uppermost blue line is the status of the on-duty rocket and spacecraft. 1-1 , SC Ω- , RD 1-1 RC Ω- After the safe recovery point, execute SD2, SD3, RD2, and RD3. The second blue line, as the left node, represents the flight of the rocket and spacecraft and the execution of the CLSP process.

[0203] The method for setting up the rolling launch technology process project set includes:

[0204] S420: One manned spacecraft and one carrier rocket are on duty at the launch site. One manned spacecraft and one carrier rocket enter the site. Take the manned space launch duty technology and process project set Φ (1) .

[0205] S421: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- ,like Figure 2 As shown by SD 1-2 , SC Ω- , SD2, SD3 constitute the manned spacecraft duty technical process project set Φ SD-2 ;

[0206] S422: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by R.D. 1-2 RC Ω- , RD2, and RD3 constitute the manned space flight technology and process project set Φ RD-2 ;

[0207] S423: Take the manned spacecraft duty technical process project set Φ SD-2 and manned space flight technology and process project setΦ RD-2, design the draft of the duty process DDP2; design the draft of the duty process DDP2 through the network planning technology, which is one of the most commonly used terms in project management and one of the most commonly used techniques for preparing project plans;

[0208] S424: From the safety recovery point to the end of the process, intercept the launch vehicle technology process project SC in the conventional single manned space test launch standard process CSLP Ω+ , by SD4, SC Ω+ Composition of the manned spacecraft flight technology process project setΦ SD-3 ; The end point of the process refers to the moment when the rocket ignites and takes off;

[0209] S425: From the safety recovery point to the end of the process, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω+ , by RD4, RC Ω+ Composition of manned space flight technology and process project setΦ RD-3 ;

[0210] S426: Take the manned spacecraft flight technology process project set Φ SD-3 and manned space flight technology and process project setΦ RD-3 , design the draft of the flight execution process EDP1; design the draft of the duty process DDP2 through network planning technology. Network planning technology is one of the most commonly used terms in project management and one of the most commonly used techniques for preparing project plans;

[0211] S427: Based on the duty process draft DDP2 and the flight process draft EDP1, the mission process draft for rolling launch is constructed;

[0212] S428: Based on the draft of the mission process flow for rolling launch, the handling resources, time and conflicts among the technical process items, a rolling launch technical process item set, namely the rolling launch mission process flow RLTP (Rolling Launch Technological Pocess), is formed.

[0213] Figure 2 The leftmost node of the green line represents the status of the newly arrived rocket and spacecraft. 1-2 , SC Ω- , RD 1-2 RC Ω- After the safety recovery point, execute SD2, SD3, RD2, and RD3; at the node (the on-duty rocket and spacecraft transfer to the flight rocket and spacecraft), execute SD4 and RD4, and after returning to the safety recovery point, execute CSLP Ω+ process.

[0214] The setting method of conventional rescue technical process item set includes:

[0215] S430: One manned spacecraft and one carrier rocket are on duty at the launch site. Take the manned space flight duty launch technology and process project set Φ (1) .

[0216] S431: Obtain the manned space launch duty technology and process project set Φ (1) :From the manned space duty launch technology and process project set Φ (1) The following items are extracted to obtain the process flow item set of manned conventional rescue launch mission Φ CR-1 :Manned space launch technology and process project collection Φ (1) as follows:

[0217] MD1: On-duty personnel, assemble.

[0218] SD4: The duty status of the manned spacecraft on duty is lifted and transferred to the flight spacecraft status.

[0219] SD 4-1 : Refueling of manned spacecraft.

[0220] SD 4-2 : Manned spacecraft buckle cover.

[0221] SD5: The manned spacecraft is transferred to the rocket testing area.

[0222] RD4: The duty status of the on-duty carrier rocket is lifted and transferred to the flight carrier rocket status.

[0223] SR 1-1 : Ship-rocket technical area docking.

[0224] SR2: The ship-rocket combination moves to the launch area.

[0225] SR3: Joint ship-rocket inspection.

[0226] SD6: Filling and launching the launch vehicle.

[0227] S432: Take the manned conventional rescue launch mission process project set Φ CR-1 , design the draft mission process CRP for conventional rescue launch;

[0228] S433: Based on the conventional rescue launch mission process draft CRP, disposal resources, time and conflicts among technical process items, a conventional rescue technical process item set, namely the emergency rescue launch mission process CRLTP (Conventional Rescue Launch Technological Pocess), is formed.

[0229] Figure 2In the figure, the yellow line is the conventional rescue launch process. First, execute MD1. At the node (the on-duty rocket and spacecraft transfer to the flight rocket and spacecraft), execute SD4 and RD4. After transferring to the safe recovery point, execute SD 4-1 , SD 4-2 , SD5, SR2, SR3, SD6 processes.

[0230] The setting methods of emergency rescue technical process project set include:

[0231] S440: One manned spacecraft and one carrier rocket are on duty at the launch site. Take the manned space flight duty launch technology and process project set Φ (1) .

[0232] S441: Obtain the manned emergency rescue launch mission process project set Φ ER-1 :From the manned space duty launch technology and process project set Φ (1) The following items are extracted to obtain the manned emergency rescue launch mission process project set Φ ER-1 :Manned emergency rescue launch mission process flow project set Φ ER-1 as follows:

[0233] MD1: On-duty personnel, assemble.

[0234] SD4: The duty status of the manned spacecraft on duty is lifted and transferred to the flight spacecraft status.

[0235] SD 4-1 : Refueling of manned spacecraft.

[0236] SD 4-2 : Manned spacecraft buckle cover.

[0237] SD5: Manned spacecraft transfers to the launch area.

[0238] RD4: The duty status of the on-duty carrier rocket is lifted and transferred to the flight carrier rocket status.

[0239] RD5: Launch vehicle transfer area.

[0240] SR 1-2 : Ship-rocket docking at the launch area.

[0241] SR3: Joint ship-rocket inspection.

[0242] SD6: Filling and launching the launch vehicle.

[0243] S442: Get the manned emergency rescue launch mission process project set Φ ER-1 , design the mission process draft ERP for emergency rescue launch;

[0244] S443: Based on the draft ERP of the mission process flow for emergency rescue launch, the conflicts among disposal resources, time and technical process items, an emergency rescue technical process item set is formed, namely the mission process flow ERLTP (Emergency Rescue Launch Technological Pocess).

[0245] Figure 2 In the figure, the red line is the emergency rescue launch process. First, execute MD1. At the node (the on-duty rocket and spacecraft transfer to the flight rocket and spacecraft), execute SD4 and RD4. After transferring to the safe recovery point, execute SD 4-1 , SD 4-2 、SD5、RD5、SR 1-2 , SR3, SD6 processes.

[0246] S5: Get the current launch conditions, which include initial launch conditions, rolling launch conditions, conventional rescue launch conditions, and emergency rescue launch conditions. If the emergency rescue launch conditions are met, the launch is carried out in accordance with the emergency rescue technical process item set. If there are no manned spacecraft and carrier rockets on duty at the launch site, the on-duty launch enters the initial launch mode.

[0247] The initial launch condition is a manned space launch under normal conditions, and there are no manned spacecraft and carrier rockets on duty at the launch site;

[0248] Rolling launch conditions are normal manned space launches, and the launch site has manned spacecraft and corresponding carrier rockets on duty;

[0249] The conditions for a conventional rescue launch are that the return capsule parked at the manned space station fails, there are manned spacecraft and corresponding carrier rockets on duty at the launch site, and the astronauts in the space station have enough time to wait for a new manned spacecraft to arrive at the space station;

[0250] The conditions for emergency rescue launch are that the return capsule parked at the manned space station malfunctions, there are manned spacecraft and corresponding carrier rockets on duty at the launch site, and the astronauts in the space station need to return as soon as possible.

[0251] S6: If the conditions for conventional rescue launch are met, the launch will be carried out in accordance with the conventional rescue technical process project set. If there is no manned spacecraft and carrier rocket on duty at the launch site, the on-duty launch will enter the initial launch mode.

[0252] S7: During the implementation of initial launch, rolling launch or conventional rescue, at the safety recovery point, if the emergency rescue launch conditions are met, the current procedure will be suspended and the launch will be carried out in accordance with the emergency rescue technical process item set; during the implementation of initial launch or rolling launch, at the safety recovery point, if the conventional rescue launch conditions are met, the current procedure will be suspended and the launch will be carried out in accordance with the conventional rescue technical process items.

[0253] Regardless of whether an initial launch or a rolling launch is being carried out, if the conditions for conventional rescue launch are met, the current program will be suspended and the launch will be carried out according to the conventional rescue launch process.

[0254] Regardless of whether the launch being carried out is an initial launch, a rolling launch or a conventional rescue launch, if the emergency rescue launch conditions are met, the current program will be suspended and the launch will be carried out according to the emergency rescue launch process.

[0255] Aiming at the special need of space station rescue, the present invention develops a new space launch mode - on-duty launch (i.e., a space product is stored at the launch site and is on standby duty. Once a launch mission is received, it only needs to complete major tasks such as ship-rocket docking, refueling, and key indicator testing, and can be launched in a relatively short time). It proposes and solves the problem of designing the technical process flow for manned space on-duty launch, and divides manned space on-duty launch into four modes, namely initial launch, rolling launch, conventional rescue, and emergency rescue, so that the design of the technical process flow for manned space on-duty launch is more targeted. This solution designs corresponding technical process flow frameworks and the use conditions of each process flow for the four modes of manned space launch, which can significantly improve the work efficiency of manned space on-duty launch. This solution breaks the "one-time design, lifelong validity" development model of the existing technical solution, so that the technical process flow of each manned space launch can be quickly reconstructed according to the specific circumstances and changes of the mission.

[0256] According to a third embodiment of the present invention, the present invention provides an electronic device, such as Figure 3 As shown, Figure 3 It is a block diagram of an electronic device according to an exemplary embodiment.

[0257] Refer to the following Figure 3 hereinafter, an electronic device 300 according to this embodiment of the present application is described. Figure 3 The electronic device 300 shown is merely an example and should not limit the functions and scope of use of the embodiments of the present application.

[0258] like Figure 3As shown, electronic device 300 is implemented as a general-purpose computing device. Components of 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 various system components (including storage unit 320 and processing unit 310), a display unit 340, and the like.

[0259] The storage unit stores program code, which can be executed by the processing unit 310, so that the processing unit 310 performs the steps described in this specification according to various exemplary embodiments of the present application. For example, the processing unit 310 can perform the steps shown in the second specific embodiment.

[0260] The storage unit 320 may include a readable medium in the form of a volatile storage unit, such as a random access memory unit (RAM) 3201 and / or a cache memory unit 3202 , and may further include a read-only memory unit (ROM) 3203 .

[0261] 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 including but not limited to: an operating system, one or more application programs, other program modules and program data, each of which or some combination may include an implementation of a network environment.

[0262] Bus 330 may represent one or more of several types of bus structures, including a memory bus or memory controller, a peripheral bus, an accelerated graphics port, a processing unit, or a local bus using any of a variety of bus architectures.

[0263] The electronic device 300 can also communicate with one or more external devices 300′ (e.g., a keyboard, pointing device, Bluetooth device, etc.), devices that allow a user to interact with the electronic device 300, and / or any device that allows the electronic device 300 to communicate with one or more other computing devices (e.g., a router, modem, etc.). This communication can occur via an input / output (I / O) interface 350. Furthermore, the electronic device 300 can communicate with one or more networks (e.g., a local area network (LAN), a wide area network (WAN), and / or a public network such as the Internet) via a network adapter 360. The network adapter 360 can communicate with other modules of the electronic device 300 via the bus 330. It should be understood that, although not shown in the figures, 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.

[0264] Through the description of the above embodiments, those skilled in the art can easily understand that the example embodiments described herein can be implemented by software, or by combining software with necessary hardware.

[0265] Therefore, according to a fourth embodiment of the present invention, the present invention provides a computer readable medium. Figure 4 As 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, and includes a number of 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.

[0266] The software product can be any combination of one or more readable media. The readable medium can be a readable signal medium or a readable storage medium. The readable storage medium can be, for example, but not limited to, a system, device or component of electricity, magnetism, light, electromagnetic, infrared, or semiconductor, or any combination thereof. More specific examples (non-exhaustive list) of readable storage media include: an electrical connection with 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 disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof.

[0267] The computer-readable storage medium may include a data signal propagated in baseband or as part of a carrier wave, wherein the readable program code is carried. The data signal propagated may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. The readable storage medium may also be any readable medium other than a readable storage medium, which may send, propagate, or transmit a program for use by or in conjunction with an instruction execution system, device, or component. The program code contained on the readable storage medium may be transmitted using any suitable medium, including but not limited to wireless, wired, optical cable, RF, etc., or any suitable combination thereof.

[0268] 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++, and the like, as well as conventional procedural programming languages ​​such as "C" or similar programming languages. The program code may be executed entirely on the user computing device, partially on the user device, as a stand-alone software package, partially on the user computing device and partially on a remote computing device, or entirely on a remote computing device or server. In cases involving a remote computing device, the remote computing device may be connected to the user computing device via 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., via the Internet using an Internet service provider).

[0269] The computer-readable medium carries one or more programs. When the one or more programs are executed by the device, the computer-readable medium implements the functions of the second specific embodiment.

[0270] Those skilled in the art will appreciate that the modules described above can be distributed in the device according to the description of the embodiment, or can be modified accordingly to be used in one or more devices that are different from the embodiment. The modules of the above embodiment can be combined into one module or further divided into multiple submodules.

[0271] Through the description of the above embodiments, it is easy for those skilled in the art to understand that the example embodiments described herein can be implemented by software or by combining software with necessary hardware. Therefore, the technical solutions according to the embodiments of the present invention can be embodied in the form of a software product, which can be stored in a non-volatile storage medium (such as a CD-ROM, a USB flash drive, a mobile hard disk, etc.) or on a network, and includes a number of instructions to enable a computing device (such as a personal computer, a server, a mobile terminal, or a network device, etc.) to execute the method according to the embodiments of the present invention.

[0272] While the exemplary embodiments of the present invention have been specifically illustrated and described above, it should be understood that the present invention is not limited to the detailed structures, configurations, or implementations described herein; rather, the present invention is intended to encompass various modifications and equivalent arrangements within the spirit and scope of the appended claims.

Claims

1. A method for processing data for manned space launch, characterized in that: The following steps are involved: S1: Obtain the manned space duty launch technology and process item set according to the conventional single manned space test launch standardization process (CSLP); The manned space launch duty technology and process project set includes but is not limited to: SD 1-1 : Determine the manned spacecraft on duty and the manned spacecraft in flight; SD 1-2 : Designate duty manned spacecraft and manned spacecraft for flight; SD2: manned spacecraft duty status setting; SD3: Status maintenance of manned spacecraft on duty; SD4: The duty status of the manned spacecraft on duty is lifted and the state is changed to the flight spacecraft state; SD5: Manned spacecraft transfer launch area; RD 1-1 : Determine the launch vehicle on duty and the launch vehicle to be flown; RD 1-2 : Designate duty manned spacecraft and manned spacecraft for flight; RD2: Launch vehicle duty status setting; RD3: duty launch vehicle status maintenance; RD4: The duty status of the on-duty launch vehicle is lifted and the status is changed to the flight rocket status; RD5: Launch vehicle transfer area; SR1: Ship-rocket launch area docking; MD1: Duty personnel assemble; S2: Obtain four modes of manned space launch duty, namely initial launch, rolling launch, conventional rescue and emergency rescue; S3: Set a safe recovery point; S4: According to the manned space duty launch technology and process item set and the safety recovery point, four launch technology and process item sets corresponding to the modes are set, namely the initial launch technology and process item set, the rolling launch technology and process item set, the conventional rescue technology and process item set, and the emergency rescue technology and process item set; The safety recovery point is in the launch technology and process project set corresponding to each mode; The method for setting up the initial launch technology process project set includes: S411: From the process start point to the safety recovery point, intercept the manned spacecraft technology process project SC in the conventional single manned space test launch standard process CSLP Ω- , by SD 1-1 , SC Ω- , SD2, SD3 constitute the manned spacecraft duty technical process project set Φ SD-1 ; S412: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by R.D. 1-1 RC Ω- , RD2, and RD3 constitute the manned space flight technology and process project set Φ RD-1 ; S413: Take the manned spacecraft duty technical process project set Φ SD-1 and manned space flight technology and process project setΦ RD-1 , design duty process draft DDP1; S414: Based on the duty process draft DDP1 and the conventional single manned space test launch standard process CSLP, the mission process draft for the initial launch is formed; S415: Based on the draft mission process flow for the initial launch, the conflicts among disposal resources, time and technical process items, a set of initial launch technical process items is formed; The method for setting up the rolling launch technology process project set includes: S421: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by SD 1-2 , SC Ω- , SD2, SD3 constitute the manned spacecraft duty technical process project set Φ SD-2 ; S422: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by R.D. 1-2 RC Ω- , RD2, and RD3 constitute the manned space flight technology and process project set Φ RD-2 ; S423: Take the manned spacecraft duty technical process project set Φ SD-2 and manned space flight technology and process project setΦ RD-2 , design duty process draft DDP2; S424: From the safety recovery point to the end of the process, intercept the launch vehicle technology process project SC in the conventional single manned space test launch standard process CSLP Ω +, by SD4, SC Ω +Constitute the manned spacecraft flight technology process project setΦ SD-3 ; S425: From the safety recovery point to the end of the process, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω +, by RD4, RC Ω +Constitute the manned space flight technology and process project setΦ RD-3 ; S426: Take the manned spacecraft flight technology process project set Φ SD-3 and manned space flight technology and process project setΦ RD-3 , design and execute the flight process draft EDP1; S427: Based on the duty process draft DDP2 and the flight process draft EDP1, the mission process draft for rolling launch is constructed; S428: Based on the draft of the mission process flow for rolling launch, the conflicts among disposal resources, time and technical process items, a rolling launch technical process item set is formed; The setting method of conventional rescue technical process item set includes: S431: Obtain the process flow project set of manned conventional rescue launch mission Φ CR-1 : MD1: Duty personnel assemble; SD4: The duty status of the manned spacecraft on duty is lifted and the state is changed to the flight spacecraft state; SD 4-1 : Refueling of manned spacecraft; SD 4-2 : Manned spacecraft buckle cover; SD5: The manned spacecraft is transferred to the rocket testing area; RD4: The duty status of the on-duty launch vehicle is lifted and the status is changed to the flight launch vehicle status; SR 1-1 : Ship-rocket technical area docking; SR2: Ship-rocket combination transfer launch area; SR3: Joint ship-rocket inspection; SD6: refueling and launching of the launch vehicle; S432: Take the manned conventional rescue launch mission process project set Φ CR-1 , design the draft mission process CRP for conventional rescue launch; S433: Based on the CRP draft of the mission process for conventional rescue launch, the conflicts among disposal resources, time and technical process items, a set of conventional rescue technical process items is formed; The setting methods of emergency rescue technical process project set include: S441: Get the manned emergency rescue launch mission process project set ΦER-1: MD1: Duty personnel assemble; SD4: The duty status of the manned spacecraft on duty is lifted and the state is changed to the flight spacecraft state; SD 4-1 : Refueling of manned spacecraft; SD 4-2 : Manned spacecraft buckle cover; SD5: Manned spacecraft transfer launch area; RD4: The duty status of the on-duty launch vehicle is lifted and the status is changed to the flight launch vehicle status; RD5: Launch vehicle transfer area; SR 1-2 : Ship-rocket launching area docking; SR3: Joint ship-rocket inspection; SD6: refueling and launching of the launch vehicle; S442: Get the manned emergency rescue launch mission process project set Φ ER-1 , design the mission process draft ERP for emergency rescue launch; S443: Based on the draft ERP of the emergency rescue launch mission process, the conflicts among disposal resources, time and technical process items, form an emergency rescue technical process item set; S5: Obtain the current launch conditions, which include initial launch conditions, rolling launch conditions, conventional rescue launch conditions, and emergency rescue launch conditions. If the emergency rescue launch conditions are met, the launch is carried out according to the emergency rescue technical process item set. If there are no manned spacecraft and carrier rockets on duty at the launch site, the duty launch enters the initial launch mode. S6: If the conditions for conventional rescue launch are met, the launch is carried out according to the conventional rescue technical process item set. If there is no manned spacecraft and carrier rocket on duty at the launch site, the on-duty launch enters the initial launch mode; S7: During the initial launch, rolling launch, or conventional rescue process, at a safety recovery point, if the emergency rescue launch conditions are met, the current procedure is suspended and the launch is carried out according to the emergency rescue technical process item set; during the initial launch or rolling launch, at a safety recovery point, if the conventional rescue launch conditions are met, the current procedure is suspended and the launch is carried out according to the conventional rescue technical process item set; S8: Repeat steps S5 to S7 until the launch is completed.

2. The method for processing data for manned space launch according to claim 1, wherein: In step S2, the initial launch is that two manned spacecraft enter the launch site at the same time, one of which performs a flight mission and the other is on duty; two carrier rockets enter the launch site at the same time, one of which performs a flight mission and the other is on duty; The rolling launch means that one manned spacecraft enters the launch site, passes the assembly test and is put into the duty state, and the spacecraft on duty performs the flight mission; one carrier rocket enters the launch site, passes the assembly test and is put into the duty state, and the carrier rocket on duty performs the flight mission; The conventional rescue is that the spacecraft and carrier rocket on duty enter the conventional rescue launch procedure; The emergency rescue is for the spacecraft and carrier rocket on duty to enter the emergency rescue launch procedure.

3. The data processing method for manned space launch according to claim 1, characterized in that: In step S3, the safety recovery point of the on-duty manned spacecraft is set to before the spacecraft is refueled, and the safety recovery point of the on-duty carrier rocket is set to before the ship-rocket docking.

4. The method for processing data for manned space launch according to claim 1, wherein: In step S5, the initial launch condition is a manned space launch in a normal state, and there is no manned spacecraft and carrier rocket on duty at the launch site; Rolling launch conditions are normal manned space launches, and the launch site has manned spacecraft and corresponding carrier rockets on duty; The conditions for a conventional rescue launch are that the return capsule parked at the manned space station fails, there are manned spacecraft and corresponding carrier rockets on duty at the launch site, and the astronauts in the space station have enough time to wait for a new manned spacecraft to arrive at the space station; The conditions for emergency rescue launch are that the return capsule parked at the manned space station malfunctions, there are manned spacecraft and corresponding carrier rockets on duty at the launch site, and the astronauts in the space station need to return as soon as possible.

5. A data processing system for manned space launch, characterized in that: include: The project acquisition module is used to obtain the manned space duty launch technology and process project set according to the conventional single manned space test launch standardization process CSLP; The manned space launch duty technology and process project set includes but is not limited to: SD 1-1 : Determine the manned spacecraft on duty and the manned spacecraft in flight; SD 1-2 : Designate duty manned spacecraft and manned spacecraft for flight; SD2: manned spacecraft duty status setting; SD3: Status maintenance of manned spacecraft on duty; SD4: The duty status of the manned spacecraft on duty is lifted and the state is changed to the flight spacecraft state; SD5: Manned spacecraft transfer launch area; RD 1-1 : Determine the launch vehicle on duty and the launch vehicle to be flown; RD 1-2 : Designate duty manned spacecraft and manned spacecraft for flight; RD2: Launch vehicle duty status setting; RD3: duty launch vehicle status maintenance; RD4: The duty status of the on-duty launch vehicle is lifted and the status is changed to the flight rocket status; RD5: Launch vehicle transfer area; SR1: Ship-rocket launch area docking; MD1: Duty personnel assemble; The launch technology and process project set generation module is used to obtain four modes of manned space duty launch, namely initial launch, rolling launch, conventional rescue and emergency rescue; Set up safe recovery points; According to the manned space duty launch technology and process item set and the safety recovery point, four modes of launch technology and process item sets are set, namely the initial launch technology and process item set, the rolling launch technology and process item set, the conventional rescue technology and process item set, and the emergency rescue technology and process item set; The safety recovery point is in the launch technology and process project set corresponding to each mode; The initial launch technology and process project set includes: S411: From the process start point to the safety recovery point, intercept the manned spacecraft technology process project SC in the conventional single manned space test launch standard process CSLP Ω- , by SD 1-1 , SC Ω- , SD2, SD3 constitute the manned spacecraft duty technical process project set Φ SD-1 ; S412: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by R.D. 1-1 RC Ω- , RD2, and RD3 constitute the manned space flight technology and process project set Φ RD-1 ; S413: Take the manned spacecraft duty technical process project set Φ SD-1 and manned space flight technology and process project setΦ RD-1 , design duty process draft DDP1; S414: Based on the duty process draft DDP1 and the conventional single manned space test launch standard process CSLP, the mission process draft for the initial launch is formed; S415: Based on the draft mission process flow for the initial launch, the conflicts among disposal resources, time and technical process items, a set of initial launch technical process items is formed; The setup of the rolling launch technology process project set includes: S421: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by SD 1-2 , SC Ω- , SD2, SD3 constitute the manned spacecraft duty technical process project set Φ SD-2 ; S422: From the process start point to the safety recovery point, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω- , by R.D. 1-2 RC Ω- , RD2, and RD3 constitute the manned space flight technology and process project set Φ RD-2 ; S423: Take the manned spacecraft duty technical process project set Φ SD-2 and manned space flight technology and process project setΦ RD-2 , design duty process draft DDP2; S424: From the safety recovery point to the end of the process, intercept the launch vehicle technology process project SC in the conventional single manned space test launch standard process CSLP Ω +, by SD4, SC Ω +Constitute the manned spacecraft flight technology process project setΦ SD-3 ; S425: From the safety recovery point to the end of the process, intercept the launch vehicle technology process project RC in the conventional single manned space test launch standard process CSLP Ω +, by RD4, RC Ω +Constitute the manned space flight technology and process project setΦ RD-3 ; S426: Take the manned spacecraft flight technology process project set Φ SD-3 and manned space flight technology and process project setΦ RD-3 , design and execute the flight process draft EDP1; S427: Based on the duty process draft DDP2 and the flight process draft EDP1, the mission process draft for rolling launch is constructed; S428: Based on the draft of the mission process flow for rolling launch, the conflicts among disposal resources, time and technical process items, a rolling launch technical process item set is formed; The setting of routine rescue technical process items includes: S431: Obtain the process flow project set of manned conventional rescue launch mission Φ CR-1 : MD1: Duty personnel assemble; SD4: The duty status of the manned spacecraft on duty is lifted and the state is changed to the flight spacecraft state; SD 4-1 : Refueling of manned spacecraft; SD 4-2 : Manned spacecraft buckle cover; SD5: The manned spacecraft is transferred to the rocket testing area; RD4: The duty status of the on-duty launch vehicle is lifted and the status is changed to the flight launch vehicle status; SR 1-1 : Ship-rocket technical area docking; SR2: Ship-rocket combination transfer launch area; SR3: Joint ship-rocket inspection; SD6: refueling and launching of the launch vehicle; S432: Take the manned conventional rescue launch mission process project set Φ CR-1 , design the draft mission process CRP for conventional rescue launch; S433: Based on the CRP draft of the mission process for conventional rescue launch, the conflicts among disposal resources, time and technical process items, a set of conventional rescue technical process items is formed; The setting of emergency rescue technical process project set includes: S441: Get the manned emergency rescue launch mission process project set ΦER-1: MD1: Duty personnel assemble; SD4: The duty status of the manned spacecraft on duty is lifted and the state is changed to the flight spacecraft state; SD 4-1 : Refueling of manned spacecraft; SD 4-2 : Manned spacecraft buckle cover; SD5: Manned spacecraft transfer launch area; RD4: The duty status of the on-duty launch vehicle is lifted and the status is changed to the flight launch vehicle status; RD5: Launch vehicle transfer area; SR 1-2 : Ship-rocket launching area docking; SR3: Joint ship-rocket inspection; SD6: refueling and launching of the launch vehicle; S442: Get the manned emergency rescue launch mission process project set Φ ER-1 , design the mission process draft ERP for emergency rescue launch; S443: Based on the draft ERP of the emergency rescue launch mission process, the conflicts among disposal resources, time and technical process items, form an emergency rescue technical process item set; The launch condition acquisition module is used to obtain the current launch conditions, which include initial launch conditions, rolling launch conditions, conventional rescue launch conditions, and emergency rescue launch conditions; The launch execution module is used to determine the launch conditions. If the emergency rescue launch conditions are met, the launch is carried out in accordance with the emergency rescue technical process item set. If there are no manned spacecraft and carrier rockets on duty at the launch site, the on-duty launch enters the initial launch mode. If the conventional rescue launch conditions are met, the launch is carried out in accordance with the conventional rescue technical process item set. If there are no manned spacecraft and carrier rockets on duty at the launch site, the on-duty launch enters the initial launch mode. During the implementation of the initial launch, rolling launch or conventional rescue, at the safety recovery point, if the emergency rescue launch conditions are met, the current program is suspended and the launch is carried out in accordance with the emergency rescue technical process item set. During the implementation of the initial launch and rolling launch, at the safety recovery point, if the conventional rescue launch conditions are met, the current program is suspended and the launch is carried out in accordance with the conventional rescue technical process items. Repeat the judgment of the launch conditions and the mode conversion until the launch is completed.

6. 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 data processing method for manned space launch according to any one of claims 1 to 4.

7. A computer-readable medium having a computer program stored thereon, characterized in that: When the program is executed by a processor, the data processing method for manned space launch according to any one of claims 1 to 4 is implemented.

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