Modular application method of reconfigurable rocket launching platform

Abstract

The invention relates to the technical field of rocket launching platform design and application, in particular to a modular application method of a reconfigurable rocket launching platform, and solves the technical problem that existing launching work generally needs to carry out new launching platform design and demonstration according to rocket requirements. According to the method, a main control unit, a supporting unit, a filling unit and a testing unit framework of a launching platform are formed according to different rocket launching requirements; a plurality of units with different functions are stored in the launching site according to the number of stations, the requirements of rocket launching on a launching platform can be received, and the units with the functions are dispatched according to the actual requirements of a rocket under the dispatching of the main control unit; the unit for supporting the final assembly goes to a final assembly workshop to support rocket final assembly work; under the condition that part of the units do not need to participate in final assembly work, the parts of the units can directly go to a transmitting station for standby preparation; after the rocket is subjected to final assembly, the rocket is transported to a launching station through the units participating in final assembly work in a cooperative mode, and after launching is completed, all the units are withdrawn.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket launch platform design and application, and in particular to a modular application method of a reconfigurable rocket launch platform. Background Art

[0002] The rocket launch platform is an important infrastructure for rocket launches. It needs to have core functions such as supporting and fixing the rocket, adjusting the verticality of the rocket body, and cooperating with the test and launch process according to the requirements of the rocket test and launch mode;

[0003] Some models of launch platforms also have walking capabilities, test and refueling arrow-ground interfaces, integrated swing arm systems, etc.;

[0004] Current launch platforms generally adopt an integrated design and construction concept. The launch platform is an integral configuration with control mechanisms and pipelines set up in the internal space. It has the characteristics of large span, heavy weight, and large load, which is conducive to stable support of the rocket launch process. However, there are also problems in launch support, post-launch recovery, iterative updates, etc.

[0005] In terms of launch support, the existing launch platform does not have the reconfigurable feature because the configuration cannot be changed. As a result, the launch platform can only support the launch of specific types of rockets due to limitations in size, interfaces, etc. Even if other infrastructure at the launch site is highly universal, the types of rockets that can be launched will be limited by the launch platform. In addition, for newly developed rocket configurations or new launch stations at the launch site, new launch platform design demonstration and manufacturing work is generally required.

[0006] In terms of post-launch recovery, it is necessary to inspect and evaluate the damage to the launch platform and repair or replace damaged parts. Due to the limitations of the overall configuration, the disassembly and installation of parts and the testing after the repair are completed will take a long time;

[0007] In addition to the maintenance time, the launch platform unavailability will be extended due to reasons such as the ordering cycle for spare parts;

[0008] In terms of iterative updates, if the launch platform has reached its design life or usage limit, or if some functions or configurations need to be replaced as a whole after updates, re-ordering or design demonstration work will be required. The inability to replace or update on demand and accurately will also bring huge usage costs. Summary of the invention

[0009] In order to solve the technical problems existing in the above-mentioned prior art that generally require new launch platform design and demonstration, the purpose of the present invention is to provide a modular application method of a reconfigurable rocket launch platform.

[0010] To achieve the above-mentioned object of the invention, the present invention provides a modular application method of a reconfigurable rocket launch platform, comprising:

[0011] The launch site stores a number of application units 100 with different functions according to the number of workstations, and is capable of receiving the requirements of the launch platform for rocket launch, and dispatching the application units 100 with functions to form a launch platform according to the actual needs of the rocket under the dispatch of a main control unit 1;

[0012] Among them, the application unit 100 for supporting final assembly goes to the final assembly plant to support the final assembly of the rocket;

[0013] Some of the application units 100 can go directly to the launch station to stand by without participating in the final assembly work;

[0014] After the rocket is assembled, the application units 100 involved in the assembly work will be transported to the launch station in coordination, and after the launch, each unit will be withdrawn;

[0015] The allocation specifically includes the following steps:

[0016] Step S100, the launch site receives the demand for the rocket launch platform;

[0017] Determine the actual required quantity of different application units 100 according to the requirements of the launch platform for the rocket launch;

[0018] The step S100 includes:

[0019] Step S110, performing launch platform combination configuration, setting the action route and specific module parameters of each unit according to the launch platform requirements and the number of specific units used, and loading them to the main control unit 1, and then the main control unit 1 distributes them to each application unit 100;

[0020] Step S120, movement of each application unit 100, under the monitoring of the main control unit 1, each application unit 100 moves to its respective target according to a preset action route;

[0021] The step S121 is also included, wherein the application units 100 necessary for final assembly are transferred to the final assembly plant;

[0022] The application unit 100 includes: a support unit 2;

[0023] The support unit 2 is a necessary unit for the vertical assembly and transportation of the rocket. The support unit 2 will move toward the assembly plant and form a combined configuration that supports the assembly and transportation of the rocket according to the configuration route;

[0024] Among them, the filling unit 3 and the test unit 4 are unnecessary units for final assembly and necessary units for launching, and the test unit can be directly transferred to the launching station;

[0025] After the rocket is transported to the right place, the pipeline and electrical connections of the filling unit 3 are connected, and the gas supply is filled; the test unit 4 is used to carry out the test work;

[0026] Step S130, the rocket is transferred to the launch station, the rocket is supported by the assembly necessary application unit 100, moves smoothly to the specific position of the launch station, and performs state conversion at the designated position and is fixed on the ground;

[0027] Step S140: the interfaces are connected, and before launching, the interfaces of the filling unit 3 and the testing unit 4 are connected with the interface on the arrow;

[0028] The filling unit 3 also needs to be connected to the ground pipeline;

[0029] S150, pre-launch filling and testing;

[0030] S160, rocket launch, executes the rocket launch process;

[0031] S170, each unit is withdrawn for maintenance.

[0032] Specifically, the units controlled by the main control unit 1 are divided based on functional modules, and the launch platform comprises at least: the support unit 2, the filling unit 3, and the test unit 4;

[0033] Wherein, the main control unit 1, the support unit 2, the filling unit 3, and the test unit 4 serve as a launch support unit;

[0034] Wherein, the launch support unit has independent use functions and independent physical configuration;

[0035] The application unit has stable movement and fixation capabilities, and has different functional interfaces on its outer surface for connecting the rocket and ground facilities.

[0036] Specifically, the main control unit 1 can inherit the centralized control function of the launch platform and be networked with each of the launch platform component units to send instructions and receive feedback, and set up an operation room.

[0037] Specifically, each of the support units 2 is provided with a rocket support interface;

[0038] Each of the support units 2 is equipped with a support and locking mechanism;

[0039] Multiple support units 2 are configured with the ability to work in coordination, which can ensure balanced force at the tail end in terms of vertical adjustment of the rocket, and can optionally be equipped with a configuration module with the ability to guide the rocket's tail flame according to the launch position and rocket configuration.

[0040] Specifically, the lower part of the filling unit 3 has an interface with the ground pipeline of the launch site, and the fuel and gas are transported to the rocket fuel or gas storage components through the operation of the internal valve.

[0041] Specifically, the test unit 4 is configured with several circuit interfaces for connecting to the rocket for functional testing;

[0042] The testing unit 4 also includes:

[0043] Test terminal, data transceiver module, networking module and motion status control module.

[0044] Compared with the prior art, the present invention has the following beneficial effects:

[0045] First, compared with the existing launch platform design scheme, the modular application method of the reconfigurable rocket launch platform can decouple the functions of each unit of the launch platform. In terms of launch support, it can be targeted at specific rocket models and combined with the use requirements of the launch platform to select different units for rapid reconfiguration and combination, supporting the launch function requirements of rockets of different configurations, which can greatly expand the versatility of the launch platform and thus improve the launch capability of the launch station;

[0046] Secondly, in terms of post-launch recovery, the volume of each unit is greatly reduced compared to the overall configuration, which is convenient for transportation, storage, and maintenance. The units are physically dispersed, which is more convenient for targeted inspection and evaluation. When the maintenance time limit is high, they can be directly replaced with the same type of stored units, shortening the post-launch recovery time and avoiding safety hazards caused by hasty maintenance.

[0047] Third, in terms of updates and iterations, specific new units can be designed and produced or existing units can be modified according to the new requirements of the launch platform for functions and performance of the new rocket, avoiding the design and manufacture of overall large configurations, saving time and economic costs brought by the launch platform update;

[0048] To summarize, this technical solution proposes a modular application method for a reconfigurable rocket launch platform to address the characteristics of the launch platform, such as limited rocket compatibility, shortened maintenance cycle, and low overall life due to the non-reconfigurability of the launch platform. It can significantly improve the launch support, post-launch recovery, and update and iteration capabilities of the launch platform. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0050] Figure 1 To schematically illustrate the architecture of the main control unit of the present invention;

[0051] Figure 2 To schematically illustrate the structure of the support unit of the present invention;

[0052] Figure 3 To schematically illustrate the architecture of the filling unit of the present invention;

[0053] Figure 4 To schematically illustrate the architecture of the test unit of the present invention;

[0054] Figure 5 To schematically illustrate an application example of the combined launch platform of the present invention;

[0055] Figure 6 The following is a schematic diagram of the application flow chart of the combined launch platform of the present invention;

[0056] Figure 7 To schematically illustrate an example of deployment of a rocket combination launch platform according to the present invention.

[0057] Reference numerals

[0058] 100.Unit; 1. Main control unit; 2. Support unit; 3. Filling unit; 4. Test unit; A. Storage place; B. Final assembly plant; C. Launch room station. DETAILED DESCRIPTION

[0059] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0060] In the new era of development with the growing demand for space launches, the rocket launch capability must be continuously improved, and the versatility of the launch platform is the key link in determining the launch capability. In view of the limited rocket compatibility, shortened maintenance cycle, and low overall life span caused by the non-reconfigurability of the launch platform, the present invention proposes a modular application method for a reconfigurable rocket launch platform, which embodies the design features of reconfigurability and combination, and can significantly improve the launch support, post-launch recovery, and update and iteration capabilities of the launch platform.

[0061] Adopting the modular design concept, the architecture design of the main control unit 1, the support unit 2, the filling unit 3, and the test unit 4 is proposed. The specific content involves a design scheme and modular application method of a reconfigurable rocket launch platform, specifically:

[0062] The launch site stores a number of application units 100 with different functions according to the number of workstations, and is capable of receiving the requirements of the launch platform for rocket launches, and dispatching the application units 100 with functions to form a launch platform according to the actual needs of the rocket under the dispatch of a main control unit 1;

[0063] Among them, the application unit 100 for supporting final assembly goes to the final assembly plant to support the final assembly of the rocket;

[0064] Some application units 100 can go directly to the launch station to stand by and prepare without participating in the final assembly work;

[0065] After the rocket is assembled, the application units 100 involved in the assembly work will be transported to the launch station in coordination, and the units will be withdrawn after the launch.

[0066] The allocation specifically includes the following steps:

[0067] Step S100, the launch site receives the demand for the rocket launch platform;

[0068] Determine the actual required quantity of different application units 100 according to the requirements of the launch platform for rocket launch;

[0069] Step S100 includes:

[0070] Step S110, configure the launch platform combination, set the action route and specific module parameters of each unit according to the launch platform requirements and the number of specific units used, and load them to the main control unit 1, which is then distributed to each application unit 100 by the main control unit 1;

[0071] Step S120, the movement of each application unit 100, under the monitoring of the main control unit 1, each application unit 100 moves to its own target according to a preset action route;

[0072] The step S121 is also included, wherein the application units 100 necessary for final assembly are transferred to the final assembly plant;

[0073] The application unit 100 includes: a support unit 2;

[0074] Support unit 2 is a necessary unit for the vertical assembly and transportation of rockets. Support unit 2 will move toward the assembly plant and form a combined configuration to support the assembly and transportation of rockets according to the configuration route;

[0075] Among them, the filling unit 3 and the test unit 4 are unnecessary units for final assembly and necessary units for launching, and the test unit can be directly transferred to the launching station;

[0076] After the rocket is transported to the right place, the pipeline and electrical connections of the filling unit 3 are connected, and the gas supply is filled; the test unit 4 is used to carry out the test work;

[0077] Step S130, the rocket is transferred to the launch station, the rocket is supported by the assembly necessary application unit 100, moves smoothly to the specific position of the launch station, and performs state conversion at the designated position and is fixed on the ground;

[0078] Step S140: the interfaces are connected, and the interfaces of the filling unit 3 and the testing unit 4 are connected to the interface on the arrow before launching;

[0079] Among them, the filling unit 3 also needs to be connected to the ground pipeline;

[0080] S150, pre-launch filling and testing;

[0081] S160, rocket launch, executes the rocket launch process;

[0082] S170, each unit is withdrawn for maintenance.

[0083] Specifically, the units controlled by the main control unit 1 are divided based on functional modules, and the launch platform is composed of at least: a support unit 2, a filling unit 3, and a test unit 4;

[0084] Among them, the main control unit 1, the support unit 2, the filling unit 3, and the test unit 4 serve as the launch support unit;

[0085] Among them, the launch support unit has independent usage functions and independent physical configuration;

[0086] The application unit has stable movement and fixation capabilities, and has different functional interfaces on the outer surface for connecting the rocket and ground facilities.

[0087] Specifically, the main control unit 1 can inherit the centralized control function of the launch platform and be networked with each launch platform component unit to send instructions and receive feedback, and set up an operation room.

[0088] Specifically, each support unit 2 is provided with a rocket support interface;

[0089] Each support unit 2 is equipped with a support and locking mechanism;

[0090] Multiple support units 2 are configured with the ability to work in coordination, which can ensure balanced force at the tail end in terms of vertical adjustment of the rocket, and can optionally be equipped with a configuration module with the ability to guide the rocket's tail flame according to the launch position and rocket configuration.

[0091] Specifically, the lower part of the filling unit 3 has an interface with the ground pipeline of the launch site, and the fuel and gas are transported to the rocket fuel or gas storage components through the operation of the internal valves.

[0092] Specifically, the test unit 4 is configured with several circuit interfaces for connecting to the rocket for functional testing;

[0093] Test Unit 4 also includes:

[0094] Test terminal, data transceiver module, networking module and motion status control module.

[0095] The launch platform combination deployment process is shown as follows Figure 5 As shown, the solid arrow is an indication of the direction of movement, and the dotted line is an indication of the network connection; first, the launch platform is assembled and configured according to the rocket requirements, and each unit is called to move from storage A to the final assembly building B or the launch station C. After the final assembly is completed, the rocket is transported to the launch station C.

[0096] Each launch support unit has stable movement and fixation capabilities, different functional interfaces on the outer surface for connecting the rocket and ground facilities, and a dedicated functional system inside.

[0097] The main control unit 1 can inherit the centralized control function of the launch platform and be networked with each launch platform component unit to send instructions and receive feedback, and set up an operation room.

[0098] The main control unit 1 inherits the centralized control capability of the traditional launch platform, networks with the various components of the launch platform, sends commands and receives feedback, sets up the operation room, has a graphical human-machine operation interface, and can control the coordinated movement of each unit. The configuration architecture is as shown in the attached Figure 1 as shown in .

[0099] Details are as attached Figure 1 Among them, the motion state control module includes but is not limited to physical and software components such as motion mechanism, motion state sensor, motion control instruction generation, etc., and performs motion control and motion function execution of the main control unit 1 itself according to the established action strategy; the information processing module includes but is not limited to software and hardware components such as sensors, information processing calculations, etc., and performs coordinated motion target control of each support unit 2, filling unit 3, and test unit 4 required for launch support; the networking module includes software and hardware components for organizing the networking strategy of each support unit 2, filling unit 3, and test unit 4 required for launch support, and performs networking of each support unit 2, filling unit 3, and test unit 4 required for launch support; the data transceiver module includes software and hardware components required for communication with each support unit 2, filling unit 3, and test unit 4 required for launch support, and performs data transmission and reception between each unit. There is a data communication relationship between each module.

[0100] The data transceiver modules of the support unit 2, the filling unit 3 and the test unit 4 communicate data with each other; the networking modules of the support unit 2, the filling unit 3 and the test unit 4 configure network parameters according to the networking strategy of the main control unit 1; the motion state control modules of the support unit 2, the filling unit 3 and the test unit 4 have the same composition and function as the motion state control module of the main control unit 1, and control their own motion according to the received motion target.

[0101] For specific architecture configuration, please refer to the attached Figure 2 As shown in , each support unit 2 is provided with a rocket support interface;

[0102] Each support unit 2 is equipped with a rocket support and locking mechanism;

[0103] Multiple support units 2 are configured with the ability to work together, ensuring balanced force at the tail end in terms of rocket vertical adjustment, and can be equipped with configuration modules with rocket tail flame diversion capabilities according to the launch position and rocket configuration;

[0104] For specific architecture configuration, please refer to the attached Figure 3 As shown in the figure, the lower part of the filling unit 3 has an interface with the ground pipeline of the launch site, and under the control of the valve control module, the fuel and gas are transported to the rocket fuel or gas storage component through the internal valve operation.

[0105] For specific architecture configuration, please refer to the attached Figure 4 As shown in , the test unit 4 is equipped with several circuit interfaces for connecting to the rocket for functional testing;

[0106] Test Unit 4 also includes:

[0107] Test terminal, data transceiver module, networking module and motion status control module.

[0108] Compared with the existing launch platform design scheme, the modular application method of the reconfigurable rocket launch platform proposed in the present invention can decouple the existing launch platform functions and physics. In terms of launch support, it can be oriented towards specific rocket models and combined with the use requirements of the launch platform to select different units for rapid reconstructive combination, support the launch function requirements of rockets of different configurations, and greatly expand the versatility of the launch platform, thereby improving the launch capability of the launch station.

[0109] That is, the main control unit 1, the support unit 2, the filling unit 3, and the test unit 4 have the same purpose and execute the respective unit function module group, and the module group includes:

[0110] Networking module, used for configuring network parameters through networking strategies;

[0111] A data transceiver module, used for data communication between the data transceiver modules;

[0112] Motion state control module, used for motion control and motion function execution.

[0113] In terms of post-fire recovery, the volume of each unit is greatly reduced compared to the overall configuration, which is convenient for transportation, storage, and maintenance. The units are physically dispersed, which makes it more convenient for targeted inspection and evaluation. When the maintenance time limit requirements are high, they can be directly replaced with stored units of the same type, shortening the post-fire recovery time and avoiding safety hazards caused by hasty maintenance.

[0114] In terms of updates and iterations, specific new units can be designed and produced or existing units can be modified based on the new requirements of the launch platform's functions and performance by the new rocket, avoiding the design and manufacturing of large-scale overall configurations and saving time and economic costs brought about by launch pad updates.

[0115] In addition, it should be noted that the present invention can be provided as a method, an apparatus or a computer program product. Therefore, the embodiments of the present invention can take the form of a complete hardware embodiment, a complete software embodiment or an embodiment combining software and hardware. Moreover, the embodiments of the present invention can take the form of a computer program product implemented on one or more computer-usable storage media containing computer-usable program code.

[0116] It should also be noted that, in this article, the terms "include", "comprises" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or terminal device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or terminal device. In the absence of further restrictions, the elements defined by the sentence "comprises a ..." do not exclude the existence of other identical elements in the process, method, article or terminal device including the elements.

[0117] Finally, it should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, for those skilled in the art, once the basic creative concept of the present invention is known, several improvements and modifications can be made without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. A modular application method for a reconfigurable rocket launch platform, characterized in that: include: The launch site stores a number of application units (100) with different functions according to the number of workstations, and is capable of receiving the demand for a launch platform for rocket launch, and dispatching the application units (100) with functions to form a launch platform according to the actual needs of the rocket under the dispatch of a main control unit (1); Among them, the application unit (100) for supporting final assembly goes to the final assembly plant to support the final assembly of the rocket; Some of the application units (100) can directly go to the launch station to wait for orders without participating in the final assembly work; After the rocket is assembled, the application units (100) participating in the assembly work are cooperatively transported to the launch station, and after the launch is completed, each unit is withdrawn; The allocation specifically includes the following steps: Step S100, the launch site receives the demand for the rocket launch platform; Determining the actual required number of different application units (100) according to the requirements of the launch platform for the rocket launch; The step S100 includes: Step S110, performing launch platform combination configuration, setting the action route and specific module parameters of each unit according to the launch platform requirements and the number of specific units used, and loading them into the main control unit (1), and then distributing them to each application unit (100) by the main control unit (1); Step S120, movement of each application unit (100), under the monitoring of the main control unit (1), each application unit (100) moves toward its respective target according to a preset action route; The step S121 is also included, wherein the application units (100) necessary for final assembly are transferred to the final assembly plant; The application unit (100) comprises: a support unit (2); The support unit (2) is a necessary unit for the vertical assembly and transportation of the rocket. The support unit (2) will move toward the assembly plant and form a combined configuration that supports the assembly and transportation of the rocket according to the configuration route. Among them, the filling unit (3) and the test unit (4) are unnecessary units for final assembly and necessary units for launching, and the test unit can be directly transferred to the launching station; After the rocket is transported to the right place, the pipeline and electrical connections of the filling unit (3) are connected, and the gas supply is filled; and the test unit (4) is used to carry out the test work; Step S130, the rocket is transferred to the launch station, the rocket is supported by the necessary application unit (100) for final assembly, moves smoothly to the specific position of the launch station, and performs state conversion at the designated position and is fixed on the ground; Step S140: the interfaces are connected, and before launching, the interfaces of the filling unit (3) and the testing unit (4) are connected to the interface on the arrow; The filling unit (3) also needs to be connected to a ground pipeline; S150, pre-launch filling and testing; S160, rocket launch, executes the rocket launch process; S170, each unit is withdrawn for maintenance.

2. The modular application method of the reconfigurable rocket launch platform according to claim 1, characterized in that: The units controlled by the main control unit (1) are divided based on functional modules, and the launch platform comprises at least: the support unit (2), the filling unit (3), and the test unit (4); Wherein, the main control unit (1), the support unit (2), the filling unit (3), and the test unit (4) serve as a launch support unit; Wherein, the launch support unit has independent use functions and independent physical configuration; The application unit has stable movement and fixation capabilities, and has different functional interfaces on its outer surface for connecting the rocket and ground facilities.

3. The modular application method of the reconfigurable rocket launch platform according to claim 2, characterized in that: The main control unit (1) can inherit the centralized control function of the launch platform and be networked with each of the launch platform component units to send instructions and receive feedback, and set up an operation room.

4. The modular application method of the reconfigurable rocket launch platform according to claim 3 is characterized in that: Each of the support units (2) is provided with a rocket support interface; Each of the support units (2) is equipped with a support and locking mechanism; The multiple support units (2) are configured with the ability to work in coordination, which can ensure balanced force on the tail end in terms of rocket vertical adjustment, and can be equipped with a configuration module with rocket tail flame diversion capability according to the launch station and rocket configuration.

5. The modular application method of the reconfigurable rocket launch platform according to claim 4, characterized in that: The lower part of the filling unit (3) has an interface with the ground pipeline of the launch site, and the fuel and gas are transported to the rocket fuel or gas storage component through the operation of the internal valve.

6. The modular application method of the reconfigurable rocket launch platform according to claim 5, characterized in that: The test unit (4) is equipped with a plurality of circuit interfaces for connecting to the rocket to perform functional testing; The testing unit (4) further comprises: Test terminal, data transceiver module, networking module and motion status control module.

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