Universal liquid carrier rocket launching pad technology

Abstract

The invention discloses a universal liquid carrier rocket launching pad technology. A satellite general assembly test subsystem realizes recovery and detection of a satellite and forms a star cover assembly; the rocket horizontal final assembly test subsystem realizes subsystem test, matching test and total inspection test of a first-stage rocket body and a second-stage rocket body in a horizontal state, and the first-stage rocket body, the second-stage rocket body and a star cover combination body form a whole rocket in the horizontal state; the rocket horizontal transfer subsystem transfers the whole rocket to the fixed launching platform in a horizontal state; the rocket launching subsystem erects the whole rocket and achieves testing, filling and launching of the whole rocket. According to the universal liquid carrier rocket launching pad technology, by adopting a three-plane test launching mode of horizontal final assembly testing, horizontal transferring and vertical launching, the construction cost of a rocket launching site is effectively reduced, the operation process is simplified, the rocket launching efficiency and frequency are improved, and the requirement for rapid and batch launching is met.

Description

Technical Field

[0001] The present application relates to the field of carrier rocket launch technology, and in particular to a universal liquid carrier rocket launch platform technology. Background Art

[0002] As commercial space activities become more frequent, the market demand for launch vehicle services continues to grow. In order to adapt to this trend, improving the efficiency and frequency of rocket launches has become an important goal of space technology development. Currently, the industry is actively exploring new rocket launch technologies that can increase launch speed and reduce costs.

[0003] Existing rocket launch systems mostly adopt a vertical assembly and test mode, which requires the rocket to be assembled and tested in a vertical state, and then transported to the launch pad via a dedicated transfer track. This mode has some obvious disadvantages. It is necessary to build tall vertical plant buildings and service towers, which not only increases the construction cost, but also occupies a large area and has a greater impact on the surrounding environment. The vertical transfer and docking process in a vertical state are complicated, with high requirements for equipment, which increases the difficulty and risk of operation. The rocket occupies the launch area for a long time, which affects the utilization efficiency of the workstation. These factors limit the frequency and efficiency of rocket launches, making it difficult to meet the growing demand for rapid and mass launches. Summary of the invention

[0004] The purpose of this application is to provide a universal liquid carrier rocket launch platform technology, which effectively reduces the construction cost of the rocket launch site, simplifies the operating procedures, improves the efficiency and frequency of rocket launches, and meets the needs of rapid and batch launches by adopting a three-horizontal test and launch mode of horizontal assembly test, horizontal transfer and erection launch.

[0005] To achieve the above objectives, the present application provides a universal liquid carrier rocket launch platform technology, including:

[0006] A satellite assembly and testing subsystem, used to realize satellite recovery and detection, and to assemble the satellite and the fairing to form a satellite-cover assembly;

[0007] The rocket horizontal assembly test subsystem is used to implement subsystem testing, matching testing and general inspection testing of the first-stage rocket body and the second-stage rocket body in a horizontal state, and to assemble the first-stage rocket body, the second-stage rocket body, the star cover assembly and the star cover assembly in a horizontal state to form a rocket as a whole;

[0008] A rocket horizontal transfer subsystem, used to transfer the entire rocket in a horizontal state to a fixed launch platform;

[0009] The rocket launching subsystem is used to erect the entire rocket, as well as to test, refuel and launch the entire rocket.

[0010] In some embodiments, the satellite assembly and testing subsystem includes a satellite assembly and testing plant, the satellite and the fairing are transported to the satellite assembly and testing plant, and satellite status recovery and inspection, solar wing deployment and electrical testing, satellite performance testing, thermal control replenishment, satellite bracket pre-installation inspection, satellite-rocket docking health check, pre-fairing status confirmation, and fairing assembly work are completed in the satellite assembly and testing plant to form the satellite-fairing assembly.

[0011] In some embodiments, the rocket horizontal assembly and testing subsystem includes a rocket assembly and testing plant, and the first-stage rocket body and the second-stage rocket body are transported to the rocket assembly and testing plant, where the work of unpacking, rocket body recovery, horizontal lifting of the rocket body, assembly, gas inspection, electrical testing, instrument loading, subsystem function testing, matching inspection and general inspection and testing, filling and pyrotechnic installation are completed.

[0012] In some embodiments, the star-cover assembly is transported to the rocket assembly and testing plant, where the satellite-rocket joint operation and docking are completed to form the rocket as a whole.

[0013] In some embodiments, the rocket horizontal assembly and testing subsystem also includes a movable launch platform, which is integrally fixed to the rocket, and the movable launch platform is used to cooperate with the fixed launch platform after the rocket is erected.

[0014] In some embodiments, the rocket horizontal transfer subsystem includes a full-rocket transport vehicle, which is used to transport the entire rocket in a horizontal state to the fixed launch platform.

[0015] In some embodiments, the rocket horizontal transfer subsystem also includes an air-conditioning support vehicle and an erection frame. The air-conditioning support vehicle is transported with the full-rocket transport vehicle. The erection frame is installed on the full-rocket transport vehicle, and the rocket is fixed as a whole on the erection frame.

[0016] In some embodiments, the rocket horizontal transfer subsystem also includes an air-conditioning device, which is installed on the air-conditioning support vehicle. The air-conditioning device is connected to the interface of the fairing through a pipeline, and the temperature and humidity environmental conditions of the star-cover assembly during transfer and transportation are adjusted by the air-conditioning device.

[0017] In some embodiments, the rocket launching subsystem includes a fixed launching platform, a hydraulic erecting device, a water spray noise reduction device and a guide groove. The hydraulic erecting device is used to erect the rocket as a whole on the fixed launching platform, the water spray noise reduction device is used to protect the fixed launching platform and the equipment on the rocket as a whole, and the guide groove is used to drain the flame ejected by the rocket as a whole.

[0018] In some embodiments, the fixed launch platform is provided with a receiving mechanism, and the receiving mechanism is used to receive the entire rocket after being erected at a preset height position, and place the entire rocket on the fixed launch platform after descending.

[0019] Compared with the above-mentioned background technology, the universal liquid carrier rocket launch platform technology provided in this application mainly includes a satellite assembly and test subsystem, a rocket horizontal assembly and test subsystem, a rocket horizontal transfer subsystem and a rocket launch subsystem. The satellite assembly and test subsystem is used to realize the recovery and detection of the satellite, and to assemble the satellite and the fairing to form a satellite-cover assembly; the rocket horizontal assembly and test subsystem is used to realize the subsystem test, matching test and general inspection test of the first-stage rocket body and the second-stage rocket body in a horizontal state, and to assemble the first-stage rocket body, the second-stage rocket body and the star-cover assembly in a horizontal state to form the rocket as a whole; the rocket horizontal transfer subsystem is used to transfer the rocket as a whole to a fixed launch platform in a horizontal state; the rocket launch subsystem is used to erect the rocket as a whole, and to realize the launch of the rocket as a whole.

[0020] In traditional rocket launch systems, rockets usually need to be assembled and tested in a vertical state, which requires the construction of tall vertical plants and service towers, which not only increases construction costs, but also occupies a large area and has a greater impact on the surrounding environment. In addition, the vertical transfer and docking process in a vertical state is complicated, with high requirements for equipment, which increases the difficulty and risk of operation. The long occupancy time of the rocket in the launch area affects the utilization efficiency of the workstation. These factors limit the frequency and efficiency of rocket launches, making it difficult to meet the needs of rapid and mass launches.

[0021] In response to these technical problems and defects, the universal liquid carrier rocket launch platform technology provided by this application adopts a new three-horizontal test and launch mode, namely horizontal assembly test, horizontal transportation and erection launch. This mode is first implemented in the satellite assembly and test subsystem, where the satellite completes recovery and detection, and is assembled with the fairing to form a satellite cover assembly. Then, the rocket horizontal assembly and test subsystem takes over, where the first-stage and second-stage rocket bodies undergo subsystem tests, matching tests and general inspection tests in a horizontal state, and are assembled in a horizontal state to form the entire rocket. This horizontal testing method reduces the requirements for the height of the plant and reduces construction costs.

[0022] Subsequently, the rocket horizontal transfer subsystem transports the entire rocket in a horizontal state to a fixed launch platform. This step avoids the need for a mobile platform and a tall service tower, further reducing construction costs and test and launch cycles. Finally, the rocket launch subsystem erects the entire rocket and performs rocket testing, refueling, and launch. This erection and launch method simplifies the operating process and improves the efficiency of the launch mission.

[0023] Through this three-level test and launch model, the construction cost of the rocket launch site is effectively reduced, because there is no need to build tall and complex vertical plants and service towers. The operation process is also simplified, because the final assembly, testing and transportation of the rocket are all carried out in a horizontal state, which reduces the demand for complex equipment and reduces the difficulty and risk of operation. In addition, the occupancy time of the rocket in the launch area is shortened, which improves the utilization efficiency of the workstation, thereby improving the efficiency and frequency of rocket launches. These improvements meet the needs of rapid and batch launches in commercial space activities, allowing rocket launch services to respond to market changes more flexibly and efficiently.

[0024] Combined with the above structure and process description, it can be seen that the universal liquid carrier rocket launch pad technology has at least the following beneficial effects: the universal liquid carrier rocket launch pad technology effectively reduces the construction cost of the rocket launch site, simplifies the operating procedures, improves the efficiency and frequency of rocket launches, and meets the needs of rapid and batch launches by adopting a three-horizontal test and launch mode of horizontal assembly test, horizontal transfer and erection launch. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.

[0026] FIG1 is a schematic diagram of a universal liquid carrier rocket launch platform technology provided in an embodiment of the present application;

[0027] FIG2 is a flow chart of a universal liquid carrier rocket launch platform technology provided in an embodiment of the present application;

[0028] FIG3 is a schematic diagram of a rocket horizontal test provided in an embodiment of the present application;

[0029] FIG4 is a schematic diagram of a full arrow transport vehicle provided in an embodiment of the present application;

[0030] FIG5 is a schematic diagram of rocket transport provided in an embodiment of the present application;

[0031] FIG6 is a schematic diagram of a fixed launch station and a movable launch station provided in an embodiment of the present application;

[0032] FIG7 is a schematic diagram of horizontal transfer of a rocket to a desired position provided by an embodiment of the present application;

[0033] FIG8 is a schematic diagram of a rocket in position vertically provided in an embodiment of the present application;

[0034] FIG. 9 is a rendering of the emission area provided in an embodiment of the present application.

[0035] in:

[0036] Satellite assembly and testing subsystem 100, rocket horizontal assembly and testing subsystem 200, rocket horizontal transfer subsystem 300, rocket launch subsystem 400,

[0037] First stage rocket body 01, second stage rocket body 02, star cover assembly 03, rocket body 04,

[0038] Satellite assembly and testing plant 1, mobile launch platform 2, rocket assembly and testing plant 3, full rocket transport vehicle 4, erection frame 5, air-conditioning device 6, pipeline 7, fixed launch platform 8, hydraulic erection device 9, air-conditioning support vehicle 10. DETAILED DESCRIPTION

[0039] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0040] In order to enable those skilled in the art to better understand the present application, the present application is further described in detail below in conjunction with the accompanying drawings and specific implementation methods.

[0041] Please refer to Figures 1 to 3, wherein Figure 1 is a schematic diagram of the universal liquid carrier rocket launch pad technology provided in an embodiment of the present application, Figure 2 is a flow chart of the universal liquid carrier rocket launch pad technology provided in an embodiment of the present application, and Figure 3 is a schematic diagram of the rocket horizontal test provided in an embodiment of the present application.

[0042] In the first specific implementation mode, the universal liquid carrier rocket launch pad technology provided in the implementation scheme of the present application mainly refers to a launch site system of a universal liquid carrier rocket three-horizontal test and launch mode, including a satellite assembly and test subsystem 100, a rocket horizontal assembly and test subsystem 200, a rocket horizontal transfer subsystem 300 and a rocket launch subsystem 400. The satellite assembly and test subsystem 100 is used to realize the recovery and detection of the satellite, and to assemble the satellite and the fairing to form a satellite cover assembly 03; the rocket horizontal assembly and test subsystem 200 is used to realize the subsystem test, matching test and general inspection test of the first-stage rocket body 01 and the second-stage rocket body 02 in a horizontal state, and to assemble the first-stage rocket body 01, the second-stage rocket body 02 and the star cover assembly 03 in a horizontal state to form a rocket body 04; the rocket horizontal transfer subsystem 300 is used to transfer the rocket body 04 in a horizontal state to a fixed launch platform 8; the rocket launch subsystem 400 is used to erect the rocket body 04, and to realize the testing, filling and launching of the rocket body 04.

[0043] In traditional rocket launch systems, rockets usually need to be assembled and tested in a vertical state, which requires the construction of tall vertical plants and service towers, which not only increases construction costs, but also occupies a large area and has a greater impact on the surrounding environment. In addition, the vertical transfer and docking process in a vertical state is complicated, with high requirements for equipment, which increases the difficulty and risk of operation. The long occupancy time of the rocket in the launch area affects the utilization efficiency of the workstation. These factors limit the frequency and efficiency of rocket launches, making it difficult to meet the needs of rapid and mass launches.

[0044] In response to these technical problems and defects, the universal liquid carrier rocket launch platform technology provided by the present application adopts a brand-new three-level test and launch mode, namely horizontal assembly test, horizontal transportation and erection launch. This mode is first implemented in the satellite assembly test subsystem 100, where the satellite completes recovery and detection, and is assembled with the fairing to form a star cover assembly 03. Then, the rocket horizontal assembly test subsystem 200 takes over, where the first-stage rocket body 01, the second-stage rocket body 02, and the star cover assembly 03 are subjected to subsystem testing, matching testing, and general inspection testing in a horizontal state, and are assembled in a horizontal state to form the rocket as a whole 04. This horizontal testing method reduces the requirements for the height of the plant and reduces construction costs.

[0045] Subsequently, the rocket horizontal transfer subsystem 300 transfers the rocket as a whole 04 to the fixed launch platform 8 in a horizontal state. This step avoids the need for a mobile platform and a tall service tower, further reducing the construction cost and the test and launch cycle. Finally, the rocket launch subsystem 400 erects the rocket as a whole 04 and implements the testing, filling, and launching of the rocket as a whole 04. This erection and launch method simplifies the operation process and improves the efficiency of the launch mission.

[0046] Through this three-level test and launch model, the construction cost of the rocket launch site is effectively reduced, because there is no need to build tall and complex vertical plants and service towers. The operation process is also simplified, because the final assembly, testing and transportation of the rocket are all carried out in a horizontal state, which reduces the demand for complex equipment and reduces the difficulty and risk of operation. In addition, the occupancy time of the rocket in the launch area is shortened, which improves the utilization efficiency of the workstation, thereby improving the efficiency and frequency of rocket launches. These improvements meet the needs of rapid and batch launches in commercial space activities, allowing rocket launch services to respond to market changes more flexibly and efficiently.

[0047] Combined with the above structure and process description, it can be seen that the universal liquid carrier rocket launch pad technology has at least the following beneficial effects: the universal liquid carrier rocket launch pad technology effectively reduces the construction cost of the rocket launch site, simplifies the operating procedures, improves the efficiency and frequency of rocket launches, and meets the needs of rapid and batch launches by adopting a three-horizontal test and launch mode of horizontal assembly test, horizontal transfer and erection launch.

[0048] In some embodiments, the satellite assembly and testing subsystem 100 includes a satellite assembly and testing plant 1. The satellite and the fairing are transported to the satellite assembly and testing plant 1. In the satellite assembly and testing plant 1, satellite status recovery and inspection, solar wing deployment and electrical testing, satellite performance testing, thermal control replenishment, satellite bracket pre-installation inspection, satellite-rocket docking health check, pre-fairing status confirmation, and fairing assembly work are completed to form a satellite-fairing assembly 03.

[0049] In this embodiment, the satellite assembly and test subsystem 100 is a key component for preparing for satellite launch, and includes a dedicated satellite assembly and test plant 1. In this plant, the satellite and the fairing are transported here and a series of assembly and testing work is carried out. These works include the recovery and inspection of the satellite status, which is to ensure that the satellite is not damaged during transportation and that all systems are in working condition.

[0050] Next, the solar wing deployment and electrical testing is carried out to verify whether the deployment mechanism of the solar wing is normal and whether the solar wing can provide the required power for the satellite. Then there is the satellite performance test, which involves testing the various functions of the satellite to ensure that it can work properly during launch and orbital operation.

[0051] Thermal control replenishment is another important step that ensures the satellite can remain stable in extreme temperatures. The satellite bracket pre-installation inspection is an inspection of the bracket that supports the satellite to ensure that it can safely support the satellite and protect its sensitive components.

[0052] The satellite-rocket docking health check is performed before the satellite and rocket dock to ensure that the connection between the two is safe. The pre-shroud status confirmation is the final check before the satellite is placed in the fairing to ensure that all systems are ready for final packaging. The fairing assembly work is to package the satellite and the fairing together to form a satellite-shroud assembly 03. This assembly will be transported to the rocket assembly and test plant, where it will dock with the rest of the rocket to complete the overall assembly of the rocket.

[0053] In some embodiments, the rocket horizontal assembly and testing subsystem 200 includes a rocket assembly and testing building 3, and the first-stage rocket body 01 and the second-stage rocket body 02 are transported to the rocket assembly and testing building 3, where the work of unpacking, rocket body recovery, horizontal lifting of the rocket body, assembly, gas inspection, electrical testing, instrument loading, subsystem function testing, matching inspection and general inspection and testing, filling and pyrotechnic installation are completed.

[0054] In this embodiment, the rocket horizontal assembly and testing subsystem 200 is a key link for rocket assembly and testing, and it includes a special rocket assembly and testing plant 3. In this plant, the first stage rocket body 01 and the second stage rocket body 02 are transported here to undergo a series of assembly and testing processes.

[0055] The first step is unpacking and rocket body recovery, which involves taking the various components of the rocket out of the transport box and restoring them to a state where they can be operated later. Then, the rocket body horizontal hoisting hoists these components to the appropriate position in a horizontal state in preparation for final assembly.

[0056] Final assembly is the process of assembling the various components of a rocket into a complete rocket structure. Gas and electrical testing is the process of checking the air tightness of the rocket and whether the electrical system is working properly. Instrument loading is the process of installing various measuring and control instruments on the rocket, which are essential for monitoring the status of the rocket and performing flight missions.

[0057] The subsystem function test is a separate test of the rocket's subsystems to ensure that they can work properly. The matching check is to ensure that the subsystems can work in coordination, and the general inspection test is a comprehensive test of the entire rocket to verify the overall performance of the rocket.

[0058] Filling refers to injecting propellant into the rocket's fuel tank, while pyrotechnic installation involves installing various explosive devices used in rocket launch and flight, such as separation devices and ignition devices. These steps are completed in Rocket Assembly and Test Building 3 to ensure that the rocket completes all necessary assembly and testing work in a horizontal state, ready for subsequent horizontal transportation and erection launch.

[0059] In some embodiments, the star cover assembly 03 is transported to the rocket assembly and testing plant 3, where the satellite-rocket joint operation and docking are completed to form the rocket as a whole 04.

[0060] In this embodiment, the transportation and docking process of the satellite cover assembly 03 is a key step in rocket assembly. The satellite cover assembly 03, that is, the assembly including the satellite and the fairing, is previously transported to the rocket assembly and test plant 3 after completing all necessary tests and preparations in the satellite assembly and test plant 1.

[0061] In the rocket assembly and test building 3, the star cover assembly 03 will be operated and docked with the first stage rocket body 01 and the second stage rocket body 02. This process involves a precise docking mechanism to ensure that the star cover assembly 03 can be correctly combined with the other parts of the rocket to form a complete rocket body 04. This docking process is very critical because it ensures the mechanical connection between the satellite and the rocket, as well as the docking of the electrical and fluid systems, which are necessary conditions for the successful launch of the rocket and the delivery of the satellite into the predetermined orbit.

[0062] After completing the joint operation and docking of the rocket and the satellite, the rocket 04 is ready for the next step of horizontal transfer. This step reflects the efficiency of the three-level test and launch mode, because the rocket remains in a horizontal state throughout the process, which reduces the dependence on vertical facilities, simplifies the operation process, and also reduces the launch cost. In this way, the rocket 04 can be transferred to the launch area in a horizontal state for the final erection and launch preparation.

[0063] In some cases, as shown in Figure 2, the three-level test and launch mode process includes the final assembly plant, the wharf, the technical area and the launch area, and the satellite final assembly and test plant 1 and the rocket final assembly and test plant 3 are located in the technical area.

[0064] In this embodiment, the three-level test and launch mode process designs an efficient workflow, covering four main areas: the final assembly plant, the dock, the technical area, and the launch area, each of which has specific functions and tasks.

[0065] The final assembly plant is the starting point for rocket and satellite assembly, where all components and segments are assembled into a complete rocket structure. This area is usually equipped with the necessary facilities and equipment to support complex assembly work.

[0066] The terminal is responsible for receiving transported parts, including satellite and rocket parts arriving by sea or land. It provides the necessary logistics support for the final assembly plant, ensuring that all necessary components arrive at the final assembly plant in a timely manner.

[0067] The technical area is the core area of ​​the entire process, where both the satellite assembly and test plant 1 and the rocket assembly and test plant 3 are located. The satellite assembly and test plant 1 is responsible for the final assembly and testing of the satellite, including key steps such as satellite recovery, inspection, solar wing deployment, and electrical testing, until it is combined with the fairing to form a satellite cover assembly 03. The rocket assembly and test plant 3 is responsible for the final assembly and testing of the rocket, including the assembly of the first-stage rocket body 01 and the second-stage rocket body 02, airtightness inspection, electrical testing, instrument installation, matching testing between systems, and joint operation and docking of the satellite cover assembly 03 with the first-stage rocket body 01 and the second-stage rocket body 02.

[0068] The launch area is the final location for rocket launch, and is equipped with a rocket launch subsystem 400, including a fixed launch platform 8 and a hydraulic erection device 9. In the launch area, the rocket is erected from a horizontal state, completes the final inspection and preparation, and then is launched.

[0069] Through this area division, the entire three-level test and launch mode process achieves efficient assembly, testing and launch of rockets and satellites, reduces costs, and improves launch efficiency and frequency.

[0070] Please refer to FIG. 6 , which is a schematic diagram of a fixed launching platform and a movable launching platform provided in an embodiment of the present application.

[0071] In some embodiments, the rocket horizontal assembly and testing subsystem 200 also includes a movable launch platform 2, which is fixed to the rocket as a whole 04, and the movable launch platform 2 is used to cooperate with the fixed launch platform 8 after the rocket is erected.

[0072] In this embodiment, the rocket horizontal assembly and testing subsystem 200 includes not only the rocket assembly and testing plant 3, but also the mobile launch platform 2. The mobile launch platform 2 is a key component that plays an important role in the assembly and launch process of the rocket.

[0073] The mobile launch platform 2 is mainly used to fix the rocket as a whole 04 before the rocket is erected. After arriving at the launch area, the mobile launch platform 2 will be used in conjunction with the fixed launch platform 8. The fixed launch platform 8 is a permanent structure in the launch area, designed to provide support during the launch of the rocket. After the rocket is erected, the mobile launch platform 2 will dock with the fixed launch platform 8 to ensure that the rocket can be accurately placed in the launch position.

[0074] This design allows the rocket to be assembled and tested in a horizontal state, and then transported to the launch area through the mobile launch platform 2, where it is erected to a vertical position in preparation for launch. This method not only improves the efficiency of rocket launches, but also reduces dependence on complex vertical launch facilities, thereby reducing launch costs and increasing launch flexibility. Through the use of the mobile launch platform 2, the rocket as a whole 04 can remain in a well-assembled state before launch, reducing the operations required in the launch area and improving the safety and reliability of the launch.

[0075] Please refer to Figure 4, which is a schematic diagram of the full-arrow transport vehicle provided in an embodiment of the present application.

[0076] In some embodiments, the rocket horizontal transfer subsystem 300 includes a full-rocket transport vehicle 4, which is used to transport the rocket as a whole 04 in a horizontal state to a fixed launch platform 8.

[0077] In this embodiment, the rocket horizontal transfer subsystem 300 is a key component responsible for transferring the assembled rocket 04 from the final assembly and test building 3 to the launch area. The core of this subsystem is the full rocket transporter 4, which is designed to carry and transport the entire rocket in a horizontal state.

[0078] The full rocket transporter not only needs to have sufficient structural strength to support the weight of the entire rocket, but also needs to have precise movement control capabilities to ensure that the rocket remains stable during transportation and avoid any violent vibrations or unexpected movements that may damage the rocket. Such transporters are usually equipped with multiple axles and hydraulic suspension systems to disperse the load and provide smooth driving performance.

[0079] During the transfer process, the rocket transporter 4 transports the entire rocket 04 from the rocket assembly and test building 3 in the technical area to the fixed launch platform 8 in the launch area. This transfer process is completed while the rocket remains in a horizontal state, which helps reduce the need for vertical transfer facilities, simplifies transfer operations, and reduces the complexity and risk of launch preparations.

[0080] In some embodiments, the rocket horizontal transfer subsystem 300 also includes an air-conditioning support vehicle 10 and an erection frame 5. The air-conditioning support vehicle 10 is transported with the full-rocket transport vehicle 4. The erection frame 5 is arranged on the full-rocket transport vehicle 4, and the rocket as a whole 04 is fixed on the erection frame 5.

[0081] In this embodiment, the design of the rocket horizontal transport subsystem 300 includes a vertical erection frame 5, which is a crucial component and is installed on the full-rocket transport vehicle 4. The function of the vertical erection frame 5 is to transform the rocket from a horizontal state to a vertical state after the rocket as a whole 04 arrives at the launch area, so as to facilitate the launch.

[0082] The erection frame 5 is designed to bear the weight and size of the rocket body 04, while providing a stable support structure to ensure that the rocket maintains a precise and safe posture during the erection process. The rocket body 04 is fixed to the erection frame 5, and this fixing process needs to ensure that the rocket does not move or rotate during the erection process to avoid damage to the rocket.

[0083] By integrating the erection frame 5 on the full rocket transporter 4, the rocket horizontal transport subsystem 300 achieves a seamless transition from horizontal transportation to vertical erection. This integrated design simplifies pre-launch preparations, reduces the operations required for the rocket in the launch area, improves launch efficiency, and reduces launch costs. In addition, this design also improves the safety and reliability of rocket launches because it reduces the need for multiple operations on the rocket in the launch area, thereby reducing the risk of errors.

[0084] Please refer to Figure 5, which is a schematic diagram of rocket transportation provided in an embodiment of the present application.

[0085] In some embodiments, the rocket horizontal transfer subsystem 300 also includes an air-conditioning device 6, which is installed in the air-conditioning support vehicle 10. The air-conditioning device 6 is connected to the interface of the fairing through a pipeline 7, and the temperature and humidity environmental conditions of the star-cover assembly 03 during the transfer and transportation process are adjusted through the air-conditioning device 6.

[0086] In this embodiment, the air conditioning support vehicle 10 of the rocket horizontal transport subsystem 300 is also specially equipped with an air conditioning device 6. The function of this air conditioning device 6 is to adjust the temperature and humidity environment conditions of the satellite cover assembly 03 during the transportation process, ensuring that the satellite and the fairing are kept in a suitable environment during the transportation to the launch area.

[0087] Since satellites and other sensitive equipment have specific requirements for environmental conditions, the air conditioning device 6 is connected to the interface of the fairing through the pipeline 7, which can accurately control the internal environment and prevent damage to the satellite due to fluctuations in temperature and humidity. This is especially important for protecting the satellite's electronic systems and precision instruments, as these components are very sensitive to environmental changes.

[0088] The setting of the air conditioning device 6 ensures that the star cover assembly 03 is maintained in a stable and controlled environment during the entire transportation process from the technical area to the launch area. This is essential for maintaining the performance and readiness of the satellite, especially in extreme weather conditions or long-distance transportation.

[0089] By integrating the air conditioning device 6 on the air conditioning support vehicle 10, the rocket horizontal transport subsystem 300 not only provides physical transportation functions, but also provides environmental control, thereby providing additional protection and assurance for the overall transportation and pre-launch preparation of the rocket. This design takes into account every detail of the satellite launch process, ensuring the high efficiency and high success rate of the entire launch process.

[0090] Please refer to Figures 7 to 9, wherein Figure 7 is a schematic diagram of the horizontal transfer of the rocket into position provided in an embodiment of the present application, Figure 8 is a schematic diagram of the vertical position of the rocket provided in an embodiment of the present application, and Figure 9 is a rendering of the launch area provided in an embodiment of the present application.

[0091] In some embodiments, the rocket launching subsystem 400 includes a fixed launching platform 8, a hydraulic erecting device 9, a water spray noise reduction device and a guide groove. The hydraulic erecting device 9 is used to erect the rocket as a whole 04 on the fixed launching platform 8, the water spray noise reduction device is used to protect the fixed launching platform and the equipment on the rocket as a whole, and the guide groove is used to drain the flames ejected by the rocket as a whole.

[0092] In the present embodiment, the rocket launch subsystem 400 is a key component for realizing the rocket from the horizontal state to the vertical launch state. This subsystem includes a fixed launch platform 8 and a hydraulic erection device 9, which work together to ensure that the rocket body 04 can be erected from the horizontal position to the vertical position safely and accurately.

[0093] The fixed launch platform 8 is a permanent structure in the launch area that provides a stable base for the rocket. The platform is designed with specific interfaces and structures to support the rocket and withstand the huge forces generated during launch. The fixed launch platform 8 is usually equipped with various pipelines and cables to provide fuel, oxidizer, power and data connections to the rocket before launch.

[0094] The hydraulic erection device 9 is a mechanical system connected to the fixed launch platform 8, which is responsible for lifting the rocket 04 from a horizontal state to a vertical state. This device uses hydraulic power to operate, which can smoothly and accurately control the erection process, ensuring the stability and safety of the rocket during the erection process. The design of the hydraulic erection device 9 takes into account the weight and size of the rocket, ensuring that the erection task can be reliably completed even in strong winds or unstable weather conditions.

[0095] When the rocket 04 is transported to the launch area by the full-rocket transport vehicle 4 and parked on the fixed launch platform 8, the hydraulic erection device 9 starts to work and slowly erects the rocket to a vertical position. Once the rocket is erected in place, it will be locked on the fixed launch platform 8, the rocket-ground connection is completed, and the final inspection and preparation work are carried out to wait for the launch order.

[0096] In addition, the rocket launch subsystem 400 also includes a water spray noise reduction device and a guide groove. The water spray noise reduction device is used to protect the fixed launch platform 8 and the rocket as a whole 04 on-arrow equipment, and the guide groove is used to guide the flames ejected by the rocket as a whole. These components together ensure the safety and effectiveness of the launch process.

[0097] Through this design, the rocket launch subsystem 400 not only improves the efficiency and safety of the rocket erection process, but also reduces the need for complex vertical launch towers, thereby reducing launch costs and simplifying the launch process. The application of this system makes rocket launches more flexible and can respond to launch plans more quickly, meeting the needs of the commercial aerospace industry for fast and efficient launches.

[0098] In some embodiments, the fixed launch platform 8 is provided with a receiving mechanism, which is used to receive the rocket assembly 04 after being erected at a preset height position, and place the rocket assembly 04 on the fixed launch platform 8 after descending.

[0099] In this embodiment, the design of the fixed launch platform 8 takes into account the entire process of erecting and placing the rocket body 04. The fixed launch platform 8 is equipped with a receiving mechanism, which is used to receive the rocket body 04 after it is erected to a preset height, and to stably place the rocket body 04 on the fixed launch platform 8 after the erection device descends.

[0100] The receiving mechanism is usually an adjustable mechanical structure that can move in the vertical direction to adapt to the height and erection requirements of different types of rockets. When the rocket is erected to a certain height, the receiving mechanism will move to the position corresponding to the bottom of the rocket, and then lock or fix the rocket to ensure its stability during the erection process.

[0101] When the hydraulic erection device 9 completes its erection action and erects the rocket 04 in a vertical position, the receiving mechanism will slowly descend so that the rocket 04 is stably placed on the fixed launch platform 8. This process requires precise control to ensure that the rocket will not be damaged during the erection and placement process, and also ensure the alignment accuracy of the rocket.

[0102] The design of the receiving mechanism enables the rocket to be quickly and safely transferred to the fixed launch platform 8 after erection, which not only improves the efficiency of launch preparation, but also reduces the manual operations performed in the launch area, thereby reducing operational risks. In addition, this design also allows the rocket to be finally inspected and prepared on the fixed launch platform 8, providing more flexibility and safety for launch.

[0103] By fixing the receiving mechanism on the launch platform 8, the rocket launch subsystem 400 realizes the seamless connection from horizontal transportation to vertical erection and then to final placement of the rocket, which optimizes the entire launch process and improves the efficiency and reliability of the launch.

[0104] In a specific implementation, the main process flow of the launch vehicle at the launch site system is as follows:

[0105] After the processes at the final assembly plant and the dock, the rocket sub-stages are transported by road to the technical area of ​​the launch site, and the satellites are transported to the site by road or air;

[0106] The satellite is assembled, tested, refueled and fairing-assembled in Satellite Assembly and Test Building 1;

[0107] The first and second stages of the rocket were unloaded and transferred in the rocket assembly and test plant 3. The subsystem test and system matching test were completed in a horizontal state. The overall inspection of the rocket was completed, and the first and second stages were docked.

[0108] Complete the installation of pyrotechnics and the filling of attitude control propellants;

[0109] The fairing assembly 03 was transferred to the rocket assembly and test plant 3, hoisted and docked, and the satellite-rocket interface inspection was completed;

[0110] The rocket-satellite assembly 04 is transported to the launch station by the rocket transport vehicle 4, docked and locked with the launch platform 8 (or the launch platform base) fixed at the guide slot, and the rocket is connected to the ground, and the rocket is erected as a whole;

[0111] Fueling signal coordination, kerosene (or methane) filling, liquid oxygen filling, pre-launch inspection, ignition and launch, and rocket take-off.

[0112] Step 1: The rocket conducts horizontal assembly testing in the technical area.

[0113] Specifically, the rocket packaging boxes are unloaded at the dock and transported by road to the rocket assembly and testing plant 3 to complete tasks such as unpacking, rocket body recovery, horizontal lifting of the rocket body, final assembly, gas inspection, electrical testing, instrument loading, subsystem function testing, matching inspection and general inspection and testing, DT-3 filling and pyrotechnic installation.

[0114] The satellite is transported by road to the satellite assembly and test plant 1, where satellite status recovery and inspection, solar wing deployment and electrical testing, satellite performance testing, thermal control supplementation, satellite bracket pre-installation inspection, satellite-rocket docking health inspection, pre-cover status confirmation, and fairing assembly work are completed to form the satellite cover assembly 03. The satellite cover assembly 03 is transferred from the cover assembly platform to the full rocket transport vehicle 4 and transported to the rocket assembly and test plant 3. After the satellite-rocket joint operation and docking are completed in the rocket assembly and test plant 3, the rocket body 04 (including the satellite cover assembly 03) is formed, and the rocket body 04 is fixed to the mobile launch platform 2. The full rocket transport vehicle 4 enters the assembly and test plant, and the rocket body 04 (including the mobile launch platform 2) is horizontally hoisted onto the transport vehicle's erection frame 5 through the plant's crane equipment, and the fairing air conditioning support and other interfaces are connected and fixed.

[0115] Step 2: The rocket as a whole 04 is horizontally transferred to the launch station.

[0116] Specifically, the whole rocket transport vehicle 4 is transported from the final assembly and testing plant in the technical area to the designated location on the launch station field via the transfer road. The air-conditioning device 6 is installed on the transport vehicle to ensure the temperature and humidity environmental conditions of the star cover assembly 03 during the transfer and transportation process.

[0117] Step 3, the rocket body 04 and the erection frame 5 are erected as a whole.

[0118] The erection process includes five parts: docking, erection, lowering, connection and falling back.

[0119] Specifically, the transport vehicle uses magnetic navigation to dock and adjust its posture. After the transport vehicle is in place, the chassis descends, and the positioning pin on the erection frame 5 falls along the V-shaped guide opening, and finally falls to the bottom of the V-shaped guide opening to complete the landing. The hydraulic erection device 9 motor controls the pin to extend, and completes the connection between the erection frame 5 and the fixed platform pin. After the posture of the erection cylinder is adjusted, the motor drives the pin to realize the connection between the fulcrum on the erection cylinder and the erection frame 5. The hydraulic erection device 9 drives the combination of the rocket body 04, the erection frame 5 and the movable launch platform 2, and rotates around the hinge axis of the erection frame 5 and the fixed launch platform 8 to complete the erection of the rocket. The erection frame 5 drives the movable launch platform 2 to rotate and erect in place (the receiving mechanism is retracted inside the fixed launch platform 8), drives the launch platform to slowly fall on the fixed launch platform 8, and is fastened with bolts.

[0120] Step 4: Rocket testing and refueling.

[0121] Specifically, after the rocket is erected and docked with the launch station, the rocket-ground pipelines and cables are connected, and the power system rocket-ground airtightness inspection, electrical system function inspection, and general inspection test are started. The rocket general inspection test includes vacuum system test, measurement system function inspection, power system ground pipeline and gas distribution platform He replacement, gas seal, blowdown, ejection test, ground pressurization test, engine vacuum test, filling valve opening and closing test, and connector detachment test. Then the rocket completes the tank replacement through the gas supply pipeline, and the propellant is filled, and it enters the pre-launch preparation.

[0122] Step 5, rocket launch.

[0123] Specifically, the hydraulic erecting device 9 controls the erecting frame 5 to smoothly fall back to the target position according to the predetermined fallback strategy (pre-fallback and 0-second fallback). The rocket is launched by the ground test and launch control system.

[0124] It should be noted that many of the components mentioned in this application are universal standard parts or components known to those skilled in the art, and their structures and principles can be learned by those skilled in the art through technical manuals or through conventional experimental methods.

[0125] It should be noted that, in this specification, relational terms such as first and second are merely used to distinguish one entity from other entities, but do not necessarily require or imply any actual relationship or order between these entities.

[0126] The above is a detailed introduction to the universal liquid carrier rocket launch pad technology provided by the present application. Specific examples are used herein to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method and core idea of ​​the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the principles of the present application, several improvements and modifications can be made to the present application, and these improvements and modifications also fall within the scope of protection of the claims of the present application.

Claims

1. A universal liquid carrier rocket launch platform technology, characterized in that: include: A satellite assembly and testing subsystem, used to realize satellite recovery and detection, and to assemble the satellite and the fairing to form a satellite-cover assembly; The rocket horizontal assembly test subsystem is used to implement subsystem testing, matching testing and general inspection testing of the first-stage rocket body and the second-stage rocket body in a horizontal state, and to assemble the first-stage rocket body, the second-stage rocket body and the star cover assembly in a horizontal state to form the entire rocket; A rocket horizontal transfer subsystem, used to transfer the entire rocket in a horizontal state to a fixed launch platform; The rocket launching subsystem is used to erect the entire rocket, as well as to test, refuel and launch the entire rocket.

2. The universal liquid carrier rocket launch platform technology according to claim 1 is characterized in that: The satellite assembly and testing subsystem includes a satellite assembly and testing plant. The satellite and the fairing are transported to the satellite assembly and testing plant. Satellite status recovery and inspection, solar wing deployment and electrical testing, satellite performance testing, thermal control replenishment, satellite bracket pre-installation inspection, satellite-rocket docking health check, pre-fairing status confirmation, and fairing assembly work are completed in the satellite assembly and testing plant to form the satellite-fairing assembly.

3. The universal liquid carrier rocket launch platform technology according to claim 1 is characterized in that: The rocket horizontal assembly and testing subsystem includes a rocket assembly and testing plant. The first-stage rocket body and the second-stage rocket body are transported to the rocket assembly and testing plant, and the work of unpacking, rocket body recovery, horizontal lifting of the rocket body, assembly, gas inspection, electrical testing, instrument loading, subsystem function testing, matching inspection and general inspection and testing, filling and pyrotechnic installation are completed in the rocket assembly and testing plant.

4. The universal liquid carrier rocket launch platform technology according to claim 3 is characterized in that: The star cover assembly is transported to the rocket assembly and testing plant, where the satellite-rocket joint operation and docking are completed to form the rocket as a whole.

5. The universal liquid carrier rocket launch platform technology according to claim 4 is characterized in that: The rocket horizontal assembly and testing subsystem also includes a movable launch platform, which is integrally fixed to the rocket and is used to cooperate with the fixed launch platform after the rocket is erected.

6. The universal liquid carrier rocket launch platform technology according to claim 1, characterized in that: The rocket horizontal transfer subsystem includes a full-rocket transport vehicle, which is used to transport the entire rocket in a horizontal state to the fixed launch platform.

7. The universal liquid carrier rocket launch platform technology according to claim 6 is characterized in that: The rocket horizontal transfer subsystem also includes an air-conditioning support vehicle and an erection frame. The air-conditioning support vehicle is transported along with the full-rocket transport vehicle. The erection frame is installed on the full-rocket transport vehicle, and the rocket is fixed as a whole on the erection frame.

8. The universal liquid carrier rocket launch platform technology according to claim 6 is characterized in that: The rocket horizontal transfer subsystem also includes an air-conditioning device, which is installed on the air-conditioning support vehicle. The air-conditioning device is connected to the interface of the fairing through a pipeline, and the temperature and humidity environmental conditions of the star-cover assembly during transfer and transportation are adjusted by the air-conditioning device.

9. The universal liquid carrier rocket launch platform technology according to claim 1, characterized in that: The rocket launching subsystem includes a fixed launching platform, a hydraulic erecting device, a water spray noise reduction device and a guide groove. The hydraulic erecting device is used to erect the rocket as a whole on the fixed launching platform. The water spray noise reduction device is used to protect the fixed launching platform and the equipment on the rocket as a whole. The guide groove is used to drain the flame ejected by the rocket as a whole.

10. The universal liquid carrier rocket launch platform technology according to claim 9, characterized in that: The fixed launch platform is provided with a receiving mechanism, which is used to receive the entire rocket after being erected at a preset height position, and place the entire rocket on the fixed launch platform after being lowered.

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