A vertical launching device with horizontal docking function and launching method

Abstract

This invention provides a vertical launch device and method with horizontal docking capability. The device includes a base, a support tilting arm, a tail bracket, and multiple supports. The support tilting arm is rotatably mounted on the base and has a support surface for supporting the booster rocket and the payload vehicle. The tail bracket is detachably mounted at the tail end of the support tilting arm for connecting to the tail of the booster rocket. Multiple supports are sequentially arranged along the length of the support tilting arm on the support surface to support the booster rocket and the payload vehicle. At least some of the supports include a position adjustment mechanism for adjusting the relative position of the booster rocket and the payload vehicle when the support tilting arm is in a horizontal state, achieving coaxial docking. After docking, the assembly is erected as a whole to a vertical launch state via the support tilting arm. This invention achieves integrated horizontal docking and overall erection of the booster rocket and payload vehicle on the launch platform, avoiding the risk of damage to the lightweight vehicle structure during overall hoisting.

Description

Technical Field

[0001] This invention relates to the field of launching devices, and in particular to a vertical launching device and launching method with horizontal docking function. Background Technology

[0002] With the rapid development of near-space vehicle technology, the demonstration and development of new types of aircraft, such as near-space unmanned aerial vehicles (UAVs), hypersonic vehicles, rotating detonation engine demonstrator vehicles, and scramjet engine demonstrator vehicles, are becoming increasingly in-depth. These types of vehicles typically require a booster rocket to propel them to near-space altitudes. After the booster rocket separates from the payload vehicle, the payload vehicle flies autonomously according to its predetermined mission and returns to Earth after the mission is completed.

[0003] To address the aforementioned launch requirements, vertical launch has become the primary technical approach due to its ability to efficiently utilize rocket thrust.

[0004] With the widespread application of lightweight design in aircraft, the structural strength of the new generation of aircraft is insufficient to withstand the huge bending moment load generated during the overall hoisting process. Therefore, how to provide an integrated launch device that can achieve horizontal docking and vertical launch has become a technical problem that urgently needs to be solved in this field. Summary of the Invention

[0005] To address the aforementioned technical problems, the technical solution adopted by this invention is as follows: According to a first aspect of the present invention, a vertical launching device with horizontal docking function is provided, comprising: Base.

[0006] A load-bearing tilting arm is rotatably mounted on the base, and the load-bearing tilting arm has a load-bearing surface for supporting the booster rocket and the payload spacecraft.

[0007] A tail bracket is detachably mounted on the tail end of the bearing tilting arm for detachable connection with the tail of the booster rocket.

[0008] Multiple supports are sequentially arranged on the bearing surface along the length of the bearing tilting arm to support the booster rocket and the payload spacecraft.

[0009] Among them, at least part of the support includes a position adjustment mechanism for adjusting the support position, which is used to adjust the relative position of the booster rocket and the payload spacecraft when the load-bearing tilting arm is in a horizontal state, so as to achieve coaxial docking. After docking, the combined body is erected as a whole to the vertical launch state through the load-bearing tilting arm.

[0010] According to a second aspect of the present invention, a launching method based on the vertical launching device described in the first aspect is provided, comprising the following steps: The booster rocket was hoisted onto multiple supports on the rotating arm.

[0011] The tail support is connected to the tail of the booster rocket.

[0012] The payload aircraft is hoisted onto multiple supports on the load-bearing tilting arm.

[0013] By adjusting the position adjustment mechanism of at least part of the support, the payload spacecraft and the booster rocket (16) are coaxially docked in a horizontal state to form a combination.

[0014] The drive arm rotates relative to the base, raising the assembly from a horizontal to a vertical position.

[0015] Separate the load-bearing tilting arm from the assembly and return the load-bearing tilting arm to a horizontal position.

[0016] Ignition and launch of the booster rocket.

[0017] The vertical launch device provided by this invention achieves precise coaxial docking of the booster rocket and the payload spacecraft in a horizontal state by setting multiple supports with position adjustment mechanisms, solving the technical problem that lightweight spacecraft cannot withstand the bending moment of overall hoisting. After docking, it can be directly erected to a vertical launch state, optimizing the traditional double-crane tilting process and improving the safety and efficiency of launch preparation. Each support integrates multi-dimensional adjustment functions such as axial sliding, lifting, lateral movement and rolling, which can adapt to different models and specifications of spacecraft. The device adopts an integrated design, which simplifies the launch process, shortens the launch cycle, and has good versatility and economy.

[0018] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of the present invention, nor is it intended to limit the scope of the invention. Other features of the invention will become readily apparent from the following description. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the overall structure of a vertical launch device with horizontal docking function provided in an embodiment of the present invention.

[0021] Figure 2 for Figure 1 A schematic diagram of the internal equipment layout of the central control compartment in the device shown.

[0022] Figure 3 for Figure 1 The diagram shows the structure of the load-bearing tilting arm and its upper supports in the device shown.

[0023] Figure 4 A schematic diagram showing the horizontal docking of the booster rocket and the payload spacecraft on the load-bearing tilting arm.

[0024] Figure 5 for Figure 3 An exploded view of the rear booster support and the front booster support, wherein... Figure 5 View (a) is an exploded view of the rear booster support, and view (b) is an exploded view of the front booster support.

[0025] Figure 6 for Figure 3 An exploded structural diagram of the rear support under medium load and the front support under medium load, wherein, Figure 6 View (a) is an exploded view of the rear load support, and view (b) is an exploded view of the front booster support.

[0026] Figure 7 for Figure 1 An exploded view of the tail bracket in the device shown.

[0027] Figure 8 A schematic diagram showing the connection status of the combined structure consisting of the tilting arm, tail support, booster rocket, and payload spacecraft.

[0028] Figure 9 for Figure 1 An exploded view of the launch pad in the device shown.

[0029] Figure 10 This is a schematic diagram of the structure from the assembled unit to its vertical launch state.

[0030] Figure 11 for Figure 1 An exploded view of the connector separation mechanism in the device shown.

[0031] Figure 12 A schematic diagram of the combined module in its ignition and launch configuration.

[0032] (See attached image labels) 1-Load-bearing tilting arm; 1-1-Load-bearing tilting arm main body; 1-2-Auxiliary tensioning mechanism; 1-3-Climbing ladder fixing rod; 1-4-Landing guide seat; 1-5-Landing fixing seat; 1-6-Sliding guide rail; 1-7-Lifting block; 2-Tail bracket; 2-1-Tail bracket main body; 2-2-Auxiliary tensioning block; 2-3-Locking assembly; 2-4-Rotating component; 2-5-Rotating lifting ring; 2-6-Booster separation cable fixing seat; 3-Launch pad; 3-1-Launch pad main body; 3-2-Supporting platform; 3-3-Streamer; 3-4-Supporting column; 3-5-Tail bracket support seat; 4-Launch base; 5-Erecting frame; 6-Central control compartment; 7-Booster rear support seat; 7-1-Booster rear support seat support; 7 -2- Booster rear support transverse movement mechanism; 7-3- Booster rear support transverse movement seat; 7-4- Booster rear support lifting and rotating component; 7-5- Booster rear support base; 7-6- Booster rear support slider; 7-7- Booster rear support guide column; 7-8- Booster rear support fixing assembly; 8- Booster front support; 8-1- Booster front support radial clamping mechanism; 8-2- Booster front support support seat; 8-3- Booster front support transverse movement seat; 8-4- Booster front support transverse movement mechanism; 8-5- Booster front support lifting and rotating component; 8-6- Booster front support base; 8-7- Booster front support guide column; 8-8- Booster front support fixing assembly; 8-9- Booster front support slider; 9- Load rear support; 9-1- Load rear support support seat ; 9-2- Rear load support rolling support; 9-3- Rear load support rolling mechanism; 9-4- Rear load support lateral movement mechanism; 9-5- Rear load support lateral movement seat; 9-6- Rear load support lifting and rotating component; 9-7- Rear load support base; 9-8- Rear load support guide column; 9-9- Rear load support slider; 9-10- Rear load support fixing assembly; 10- Front load support; 10-1- Front load support support; 10-2- Front load support rolling support; 10-3- Front load support radial clamping mechanism; 10-4- Front load support lateral movement seat; 10-5- Front load support lateral movement mechanism; 10-6- Front load support lifting and rotating component; 10-7- Front load support base; 10-8 - Load front support guide column; 10-9- Load front support slider; 10-10- Load front support fixing assembly; 11- Connector separation mechanism; 11-1- Pull-out mechanism base; 11-2- Front stop; 11-3- Rear stop; 11-4- Lateral drive screw; 11-5- Linear drive mounting base; 11-6- Linear drive; 11-7- Adapter; 11-8- Adapter pull ring; 11-9- Traction ring; 11-10- Disconnect cable; 11-11- Sliding guide rail; 11-12- Sliding block; 11-13- Moving seat; 12- Erection cylinder; 13- Generator set; 14- Electrical control box; 15- Hydraulic pump station; 16- Boost rocket; 17- Load vehicle; 18- Assembly. Detailed Implementation

[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein in the description of this invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0035] It should be noted that some exemplary embodiments are described as processes or methods depicted as flowcharts. Although the flowcharts describe the steps as sequential processes, many of these steps can be performed in parallel, concurrently, or simultaneously. Furthermore, the order of the steps can be rearranged. A process can be terminated when its operation is complete, but it may also have additional steps not included in the figures. A process can correspond to a method, function, procedure, subroutine, subroutine, etc.

[0036] Currently, the following solutions mainly exist in the existing technology: One approach involves using a simplified launch pad combined with hoisting and tilting. This method transports the booster rocket and payload to the launch site horizontally, then uses two cranes to tilt them to a vertical position and place them on the simplified launch pad, finally securing them with steel cables. This approach is complex, the hoisting and tilting process poses significant safety risks, and the launch preparation period is lengthy.

[0037] Another approach involves using a launch system with transport and erection capabilities. This type of system transports the booster rocket and payload vehicle assembly to the launch site, then uses an erection device to lift the assembly from a horizontal to a vertical position before ignition and launch. This method simplifies the launch process to some extent, but still requires the assembly to be docked before erection.

[0038] This invention aims to solve the aforementioned problems in the prior art by providing a vertical launch device and its launch method with horizontal docking capability. The invention integrates the launch pad at the rear end of the launch base, eliminating the need for auxiliary fixation during launch and simplifying the launch process. Along its length, the upper part of the load-bearing tilting arm is sequentially equipped with a booster rear support, a booster front support, a payload rear support, and a payload front support. Through the position adjustment mechanism of each support, coaxial docking of the booster rocket and the payload spacecraft is achieved when the load-bearing tilting arm is in a horizontal state. After docking, the assembly is erected to a vertical launch position via the load-bearing tilting arm. This invention optimizes the dual-crane tilting process, improves the safety of launch preparation, and allows for adaptation to spacecraft of different diameters and configurations by replacing the load-bearing tilting arm, demonstrating good compatibility.

[0039] First Embodiment like Figure 1 As shown, the first embodiment of the present invention provides a vertical launch device with horizontal docking function. This device is mainly used to realize the horizontal docking of the booster rocket 16 and the payload spacecraft 17 on the launch platform, and to raise the docked assembly 18 to a vertical launch state. The device includes: a launch base 4, a load-bearing tilting arm 1, a tail bracket 2, multiple supports, a centralized control cabin 6, a lifting cylinder 12, a launch pad 3, and a connector separation mechanism 11.

[0040] The launch base 4 serves as the mounting foundation for the entire device and is positioned at a predetermined location on the launch site. The support tilting arm 1 is rotatably mounted on the launch base 4, used to support the booster rocket 16 and the payload spacecraft 17 in a horizontal position and to lift them to an upright position. The tail bracket 2 is detachably mounted on the tail end of the support tilting arm 1, used to connect with the tail of the booster rocket 16 to achieve rigid fixation during the erection process. Multiple supports are sequentially arranged along the length of the support tilting arm 1 on its bearing surface, used to support the booster rocket 16 and the payload spacecraft 17 respectively, and their coaxial docking is achieved through a position adjustment mechanism. The multiple supports include: a rear booster support 7 for supporting the tail of the booster rocket 16; a front booster support 8 located in front of the rear booster support 7 for supporting the head of the booster rocket 16; a rear payload support 9 located in front of the front booster support 8 for supporting the tail of the payload vehicle 17; and a front payload support 10 located in front of the rear payload support 9 for supporting the head of the payload vehicle 17.

[0041] At least part of the support includes a position adjustment mechanism for adjusting the support position, which is used to adjust the relative position of the booster rocket 16 and the payload spacecraft 17 when the load-bearing tilting arm 1 is in a horizontal state, so as to achieve coaxial docking. After docking, the assembly is raised to a vertical launch state by the load-bearing tilting arm 1 and supported on the launch pad 3. Before ignition and launch, the load-bearing tilting arm 1 separates from the assembly 18 and returns to a horizontal position.

[0042] The centralized control cabin 6 is located at the front of the launch base 4, and integrates a generator set 13, an electrical control box 14, and a hydraulic pump station 15, providing power and control for the entire device. The two ends of the erection cylinder 12 are connected to the launch base 4 and the load-bearing tilting arm 1, respectively, to drive the load-bearing tilting arm 1 to rotate relative to the launch base 4. The launch platform 3 is located at the rear end of the launch base 4, used to support the assembly 18 after erection and to guide the gas flow during ignition. The connector separation mechanism 11 is located at the front of the load-bearing tilting arm 1, used to automatically disconnect the coupling connector of the payload aircraft 17 before launch.

[0043] The following is in conjunction with the appendix Figures 1 to 12 The present invention will provide a detailed description of the various components of the vertical launch device provided in the first embodiment of the invention and their connection relationships.

[0044] (a) Load-bearing tilting arm like Figure 1 and Figure 3 As shown, the load-bearing tilting arm 1 is rotatably mounted on the base 4, serving as the main support for the booster rocket 16 and the payload spacecraft 17 in a horizontal state, as well as the main force transmission component during their erection. The load-bearing tilting arm 1 has a bearing surface for supporting the booster rocket 16 and the payload spacecraft 17. This bearing surface is a machined flat surface to ensure the accuracy and stability of the installation of each support.

[0045] The main body 1-1 of the load-bearing tilting arm is a frame structure welded from high-strength metal materials. It has sufficient structural strength and rigidity to withstand the weight of the combined body 18 consisting of the booster rocket 16 and the payload spacecraft 17, as well as various loads generated during the erection process.

[0046] Two sets of auxiliary tensioning mechanisms 1-2 are provided at the front end of the main body 1-1 of the load-bearing tilting arm. Each auxiliary tensioning mechanism 1-2 includes a fixed base and a locking seat. The fixed base is fixedly connected to the main body 1-1 of the load-bearing tilting arm, and the locking seat is mounted on the fixed base and fixedly connected to it by bolts. The fixed base and locking seat adopt a split design, which facilitates the machining and heat treatment of each part, reduces manufacturing difficulty, and also facilitates later maintenance and replacement. The locking seat is preferably a triangular frame structure. The triangular structure has good geometric stability, which can effectively enhance the rigidity and strength of the connection parts, ensuring that it does not deform when subjected to large tensile forces during erection.

[0047] Two sets of auxiliary tensioning mechanisms 1-2 work in conjunction with two sets of auxiliary tensioning blocks 2-2 on the tail bracket 2, and are detachably connected by quick-release pins and other connecting parts. During the erection process, the auxiliary tensioning mechanisms 1-2 are connected to the auxiliary tensioning blocks 2-2, and the gravity load of the assembly 18 is transferred to the load-bearing tilting arm 1 through the auxiliary tensioning blocks 2-2, ensuring the stability and safety of the erection process.

[0048] The main body 1-1 of the load-bearing tilting arm is equipped with ladder fixing rods 1-3 on both sides for suspending the operating ladder. Operators can climb the ladder to the upper part of the load-bearing tilting arm 1 to facilitate the docking operation of the booster rocket 16 and the payload spacecraft 17, as well as the adjustment of each support.

[0049] Four sets of positioning guide seats 1-4 are provided at the four corners of the main body 1-1 of the load-bearing tilting arm 1 for guiding the load-bearing tilting arm 1 when it is docked with the lower erecting frame 5. The positioning guide seats 1-4 have guide ramps to guide the load-bearing tilting arm 1 to accurately land on the erecting frame 5 during the descent process. Four sets of positioning fixing seats 1-5 are installed at the end of the middle crossbeam of each side of the positioning guide seats 1-4 to reliably lock the load-bearing tilting arm 1 after docking with the erecting frame 5, preventing relative displacement during transportation or erection.

[0050] Sliding guide rails 1-6 are installed along the length of the upper part of the longitudinal beams on both sides of the main body of the rotating arm 1-1. The sliding guide rails 1-6 are precision-machined linear guide rails used to install and guide each support. The bottom of the booster rear support 7, booster front support 8, load rear support 9, and load front support 10 are respectively provided with sliders that cooperate with the sliding guide rails 1-6. Through the sliding cooperation between the sliders and the sliding guide rails 1-6, the position of each support can be freely adjusted along the length of the rotating arm 1 to accommodate booster rockets 16 and load vehicles 17 of different lengths.

[0051] Lifting blocks 1-7 are also provided at the four corners of the main body 1-1 of the tilting arm for lifting and transporting the entire tilting arm 1. Lifting blocks 1-7 are provided with lifting holes to facilitate connection with the hook of the lifting equipment, so as to realize the installation, disassembly and maintenance of the tilting arm 1.

[0052] (ii) Tail bracket like Figure 1 and Figure 7 As shown, the tail bracket 2 is detachably mounted on the tail end of the carrying tilting arm 1 and is used to detachably connect with the tail of the booster rocket 16. During the erection process, it transfers the gravity load of the assembly 18 to the carrying tilting arm 1 and, after being erected in place, carries the assembly 18 on the launch pad 3.

[0053] The tail support 2 is mainly composed of the tail support body 2-1, the auxiliary tensioning block 2-2, the locking assembly 2-3, the rotating part 2-4, the rotating lifting ring 2-5, and the booster rocket separation cable fixing seat 2-6.

[0054] The tail support body 2-1, serving as the main load-bearing structure, is a frame structure welded from high-strength metal materials, possessing sufficient structural strength and rigidity. The tail support body 2-1 consists of a square front end and an arc-shaped rear end. A circular opening is formed in the middle of the arc-shaped rear end, which is adapted to the tail port diameter of the booster rocket 16, facilitating the installation and repositioning of the booster rocket 16's tail nozzle. All mounting surfaces of the tail support body 2-1 are machined to ensure the accuracy and reliability of component installation.

[0055] The tail support 2 has two working states: transport state and erection preparation state. In the transport state, the tail support 2 is placed on the tail support base 3-5 of the launch pad 3 and reliably fixed to the launch pad 3 with fasteners, facilitating overall transportation. When it is necessary to erect the assembly, the tail support 2 is released from the launch pad 3, and the lifting equipment is connected by rotating the lifting ring 2-5 to flip the tail support 2 to the tail end face position of the booster rocket 16.

[0056] The left side of the tail support body 2-1 is fixedly connected to the rotating component 2-4 via a locking assembly 2-3. A pin hole is pre-drilled at the end of the rotating component 2-4, which is hinged to the rotating trunnion on the launch base 4, allowing the tail support 2 to rotate around the axis of the rotating trunnion of the launch base 4. Since the load-bearing tilting arm 1 also rotates around this rotating trunnion axis, the tail support 2 and the load-bearing tilting arm 1 can maintain synchronous rotation during erection, ensuring stable relative positions between them.

[0057] A set of auxiliary tensioning blocks 2-2 is provided on each of the left and right sides of the tail support body 2-1. The positions of the auxiliary tensioning blocks 2-2 correspond to the auxiliary tensioning mechanism 1-2 on the load-bearing tilting arm 1. When the tail support 2 is tilted to the tail end face of the booster rocket 16, the auxiliary tensioning blocks 2-2 are connected to the locking seats of the auxiliary tensioning mechanism 1-2 by quick-release pins, thereby achieving rigid fixation between the tail support 2 and the load-bearing tilting arm 1. At this time, the combination 18 consisting of the tail support 2, the load-bearing tilting arm 1, the booster rocket 16, and the payload spacecraft 17 forms a whole, ensuring structural stability during the erection process.

[0058] A rotating lifting ring 2-5 is installed on the right side of the tail support body 2-1, serving as a lifting interface for the state transition operation of the tail support 2. By connecting the lifting equipment through the rotating lifting ring 2-5, the tail support 2 can be easily flipped from the transport state above the launch pad 3 to the working state at the tail of the assembly, or the tail support 2 can be reset to the transport state after the work is completed.

[0059] A booster rocket separation cable fixing seat 2-6 is provided at the central circular opening of the arc-shaped rear end of the tail support body 2-1, for connecting the separation cable of the booster rocket 16. When the booster rocket 16 separates from the payload spacecraft 17, the separation cable transmits the separation force through this fixing seat, ensuring the reliable execution of the separation action.

[0060] The connection between the tail support 2 and the tail of the booster rocket 16 is as follows: After the tail support 2 is flipped to the tail end face of the booster rocket 16, multiple fasteners distributed around the arc-shaped rear end of the tail support body 2-1 are used to fix the tail flange of the booster rocket 16 to the tail support body 2-1, thus achieving a reliable connection between the booster rocket 16 and the tail support 2. Simultaneously, the arc-shaped rear end of the tail support body 2-1 is adapted to the shape of the tail of the booster rocket 16, providing radial positioning and support for the booster rocket 16.

[0061] Through the above structure, the tail support 2 forms a rigid connection with the load-bearing tilting arm 1 and the booster rocket 16 before erection, ensuring the stability of the erection process; after being erected in place, the tail support 2 transfers the weight of the assembly 18 to the launch pad 3, and disconnects from the load-bearing tilting arm 1 before ignition and launch, so that the load-bearing tilting arm 1 can return to its original position and complete the launch preparation.

[0062] (III) Launch Pad like Figure 1 and Figure 9 As shown, the launch pad 3 is located at the tail end of the base 4 and is used to support the tail support 2 and the booster rocket 16 and payload spacecraft 17 on the upper part of the tail support 2 after the combined body 18 is erected to a vertical state. It also guides and discharges the high-temperature and high-speed gas flow ejected from the tail when the booster rocket 16 is ignited and launched.

[0063] Launch platform 3, as a key load-bearing and functional component of the vertical launch device of this invention, mainly has the following functions: supporting the entire weight of the assembly 18 after erection; and rapidly guiding the exhaust gas flow from the tail of the booster rocket 16 to both sides of the device during the initial stage of ignition and launch, preventing backflow of exhaust gas from damaging the launch device and rocket body. To achieve the above functions, launch platform 3 mainly consists of launch platform body 3-1, support platform 3-2, flow guide 3-3, support column 3-4, and tail bracket support seat 3-5.

[0064] The launch pad body 3-1 is a frame structure welded from high-strength metal materials, serving as the installation foundation and main load-bearing component of the entire launch pad 3. The bottom of the launch pad body 3-1 is fixedly connected to the tail end of the base 4 with fasteners, which can effectively transfer the gravity load of the assembly 18 and the impact load generated during launch to the base 4, and then to the foundation. The top of the launch pad body 3-1 is provided with an installation interface for installing the support platform 3-2, and the surrounding area is provided with connection structures for installing the deflector 3-3.

[0065] The support platform 3-2 is located on top of the launch pad body 3-1 and is a square plate-like structure with a circular opening in the center. This circular opening corresponds to the position of the tail nozzle of the booster rocket 16, allowing the passage of exhaust gas. The bottom surface of the support platform 3-2 is fixedly connected to the launch pad body 3-1 by multiple support columns 3-4. The support columns 3-4 are vertically arranged between the support platform 3-2 and the launch pad body 3-1, distributed along the perimeter of the support platform 3-2, serving to support the support platform 3-2 and transfer the load on the support platform 3-2 to the launch pad body 3-1.

[0066] Tail support bases 3-5 are disposed on the upper surface of the support platform 3-2 to support the tail support 2 after it is erected. In this embodiment, four tail support bases 3-5 are provided, evenly distributed around the circular opening of the support platform 3-2. The positions of the four tail support bases 3-5 correspond to the support points at the bottom of the tail support 2. When the assembly 18 is erected to a vertical position, the lower surface of the tail support 2 rests precisely on the four tail support bases 3-5 and is reliably fixed by fasteners, ensuring the stability of the assembly 18 during launch.

[0067] The deflector 3-3 is located at the lower part of the launch pad body 3-1, directly below the circular opening of the support platform 3-2, and is used to guide and deflect the high-temperature, high-speed exhaust gas flow ejected during the initial ignition of the booster rocket 16. The deflector 3-3 adopts a double-sided symmetrical deflection structure, including a first deflector plate and a second deflector plate connected to each other. Both the first and second deflector plates are arc-shaped plate structures recessed towards the bottom of the launch pad body 3-1, forming a smooth guiding surface. The top of the first deflector plate is fixedly connected to one side of the bottom of the launch pad body 3-1, and the top of the second deflector plate is fixedly connected to the other side of the bottom of the launch pad body 3-1. Together, they form an inverted V-shaped or inverted U-shaped guiding channel below the bottom of the launch pad body 3-1. When the booster rocket 16 ignites, the high-temperature, high-speed gas flow ejected from the tail is sprayed downwards through the circular opening of the support platform 3-2 to the guide vane 3-3. After being guided by the arc-shaped surfaces of the first and second guide vanes, it is discharged horizontally to both sides of the launch device, effectively preventing the gas flow from causing recoil and thermal damage to the launch device body and the bottom of the rocket.

[0068] Through the above structure, the launch pad 3 provides a stable support foundation for the assembly 18 after it is erected, and effectively guides the gas flow during ignition and launch, ensuring the safety and reliability of the launch process.

[0069] (iv) Base like Figure 1 As shown, the base 4 serves as the overall mounting foundation for the vertical launch device of the present invention and is positioned at a predetermined location on the launch site. The base 4 is a frame structure welded from high-strength metal materials, possessing sufficient structural strength and rigidity to support the weight of the entire launch device and various loads generated during launch.

[0070] The base 4 has multiple mounting interfaces for mounting various upper-mount equipment. Specifically, the rear of the base 4 has a mounting seat for mounting the launch pad 3, which is fixedly connected to the base 4 by fasteners. The middle of the base 4 has two lower trunnion seats for hinged connection to one end of the erection cylinder 12. The tail end of the base 4 has a swivel trunnion for hinged connection to the tail end of the carrying tilting arm 1 and the swivel component 2-4 of the tail bracket 2, allowing the carrying tilting arm 1 and the tail bracket 2 to rotate in a vertical plane around the axis of the swivel trunnion. The front of the base 4 has a mounting interface for mounting the erector frame 5, which is fixedly mounted on the upper front end of the base 4 to support the front of the carrying tilting arm 1 in a horizontal position.

[0071] In addition, a central control cabin 6 is installed at the front of the base 4, and the central control cabin 6 is fixedly installed at the front end of the base 4. Figure 2 As shown, the central control cabin 6 integrates a generator set 13, an electrical control box 14, and a hydraulic pump station 15. These devices are all installed and fixed through interfaces reserved on the base 4. The bottom of the base 4 is also equipped with multiple anchor bolt mounting seats, which are used to reliably fix the entire vertical launch device to the foundation of the launch site through anchor bolts, ensuring stability during the launch process.

[0072] Multiple lifting rings are also provided around the base 4 for lifting, transporting and positioning the entire launch device.

[0073] (v) Central control cabin like Figure 1 and Figure 2 As shown, the central control cabin 6 is located at the front of the base 4, specifically mounted above the front end of the launch base 4. The central control cabin 6 serves as the integrated power and control unit for the vertical launch device of this invention, providing a good working environment for the various internal functional devices, while also providing a locking function during transport.

[0074] The centralized control compartment 6 adopts a box-type structure design, welded from metal plates, providing sufficient structural strength and sealing performance. The interior of the centralized control compartment 6 forms a closed installation space, effectively protecting the internal equipment from external environmental factors such as wind, sand, rain, snow, and temperature changes, ensuring reliable operation of the equipment under various climatic conditions.

[0075] The centralized control cabin 6 integrates a generator set 13, an electrical control box 14, and a hydraulic pump station 15. The generator set 13 serves as the power source for the entire launch device, providing electricity to all electrical equipment. The electrical control box 14 acts as the control core, housing the control system circuitry and interfaces to receive commands and control the actions of actuators such as the erecting cylinder 12, the radial clamping mechanism, and the connector separation mechanism 11. The hydraulic pump station 15 is connected to the erecting cylinder 12 via hydraulic lines, providing hydraulic power to drive the load-bearing tilting arm 1 to smoothly erect and return to its original position. These devices are rationally arranged within the centralized control cabin 6 for easy operation and maintenance.

[0076] The top of the central control cabin 6 is equipped with a travel locking seat, which corresponds to the position of the erector frame 5. During transport, the front of the erector frame 5 is securely connected to the travel locking seat via fasteners, ensuring reliable locking of the erector frame 5 during transport and preventing displacement or shaking due to vibrations and bumps, thus ensuring transport safety. Upon arrival at the launch site, the connection between the travel locking seat and the erector frame 5 is released, and the erector frame 5 can then enter operational status.

[0077] The central control cabin 6 is also equipped with operating doors and inspection ports on its sides, facilitating equipment operation and routine maintenance by operators. The bottom of the central control cabin 6 is fixedly connected to the base 4 with fasteners to ensure the stability and reliability of the overall structure.

[0078] Through the above structure, the centralized control cabin 6 integrates the power source, control core and execution power source into one unit, realizing a highly integrated design of the launch device, simplifying on-site wiring and workflow, and improving the efficiency and reliability of launch preparation.

[0079] (vi) Assisting rear support like Figure 3 and Figure 5 As shown, the booster rear support 7 is located at the rearmost part of the bearing surface of the bearing tilting arm 1, and is used to provide support for the tail of the booster rocket 16 during horizontal docking with the payload spacecraft 17 and after docking.

[0080] The booster rear support 7 mainly includes a booster rear support base 7-5, a booster rear support slider 7-6, a booster rear support lifting and rotating component 7-4, a screw lift, a booster rear support guide column 7-7, a booster rear support transverse sliding seat 7-3, a booster rear support transverse sliding mechanism 7-2, a booster rear support support 7-1, and a booster rear support fixing assembly 7-8. Through these structures, the booster rear support 7 integrates an axial sliding mechanism, a lifting mechanism, and a transverse sliding mechanism, enabling multi-dimensional position adjustment of the booster rocket 16's tail section in a horizontal state.

[0081] (1) Axial sliding mechanism The booster rear support base 7-5 serves as the mounting foundation for the booster rear support 7, with two sets of booster rear support sliders 7-6 installed on each of its bottom left and right sides. The booster rear support sliders 7-6 slide in conjunction with the sliding guide rails 1-6 on the upper longitudinal beams of the supporting tilting arm 1, forming an axial sliding mechanism. Through this axial sliding mechanism, the booster rear support 7 can be axially adjusted along the length of the supporting tilting arm 1 to accommodate booster rockets 16 of different lengths. Once the axial position is adjusted, the booster rear support base 7-5 is fixed and locked to the supporting tilting arm 1 by the booster rear support fixing assembly 7-8, preventing accidental displacement during subsequent docking and erection operations, ensuring positioning accuracy and operational safety.

[0082] (2) Lifting mechanism A screw jack is fixedly installed on each of the left and right sides of the upper part of the booster rear support base 7-5, with the two screw jacks arranged symmetrically. The booster rear support lifting rotating component 7-4 is a drive shaft that runs horizontally through the two screw jacks. One end of the shaft is rotatably connected to the booster rear support base 7-5 via a bearing seat or fixed seat, and the other end is drively connected to the input end of the two screw jacks. The end of the booster rear support lifting rotating component 7-4 is provided with a drive interface, which can be connected to a manual crank or a power drive device. When the booster rear support lifting rotating component 7-4 is rotated, the two screw jacks move synchronously, converting their rotational motion into linear motion of the lifting end, thus forming the lifting mechanism.

[0083] The lifting end of the spiral lifter is fixedly connected to the booster rear support transverse shift seat 7-3. By driving the lifting rotating component to rotate, the booster rear support transverse shift seat 7-3 and its upper components can move smoothly up and down in a direction perpendicular to the bearing surface of the bearing tilting arm 1, thereby precisely adjusting the support height of the tail of the booster rocket 16.

[0084] Two guide columns 7-7 are also provided on the booster rear support base 7-5, spaced apart between the two screw jacks. Each guide column 7-7 is arranged vertically, with its lower end fixedly connected to the booster rear support base 7-5, and its upper end passing through the corresponding guide hole on the booster rear support transverse sliding seat 7-3, and can slide within the guide hole. The cooperation between the booster rear support guide column 7-7 and the guide hole plays a guiding role during the lifting process, ensuring the smoothness and directional accuracy of the lifting movement, and preventing the transverse sliding seat from deflecting. At the same time, after the supporting tilting arm 1 is raised to a vertical position, the booster rear support guide column 7-7 can enhance the overall rigidity of the booster rear support 7, share the bending moment load on the screw of the screw jack, and prevent the screw jack from being damaged due to excessive bending moment.

[0085] (3) Transverse movement mechanism Two sets of transverse guide rails are provided on the upper part of the booster rear support transverse shifter 7-3 along both sides perpendicular to the length direction of the bearing tilting arm 1. Four sets of sliders are installed at the bottom of the booster rear support support 7-1. These sliders slide in cooperation with the transverse guide rails on the upper part of the booster rear support transverse shifter 7-3, forming a transverse shifting mechanism. The booster rear support transverse shifting mechanism 7-2 is mounted on the booster rear support transverse shifter 7-3 and is drively connected to the booster rear support support 7-1. By manually or power-driven rotation of the booster rear support transverse shifting mechanism 7-2, the booster rear support support 7-1 can be driven to move laterally in the horizontal direction perpendicular to the length direction of the bearing tilting arm 1, thereby adjusting the transverse support position of the tail of the booster rocket 16 and achieving transverse alignment with the payload spacecraft 17.

[0086] The upper part of the booster rear support support 7-1 has an arc-shaped support surface that is adapted to the shape of the tail of the booster rocket 16. The surface of the arc-shaped support surface is covered with flexible materials such as felt to protect the surface of the rocket body from damage when supporting the booster rocket 16.

[0087] Through the above structure, the booster rear support 7 integrates a position adjustment mechanism with three dimensions: axial sliding, lifting and lateral movement. This provides a comprehensive means of adjustment for the precise positioning of the tail of the booster rocket 16 in a horizontal state, ensuring that the booster rocket 16 and the payload spacecraft 17 can achieve high-precision coaxial docking.

[0088] (vii) Assisting the front support seat like Figure 3 and Figure 5 As shown, the front booster support 8 is located at the front of the rear booster support 7 and is used to provide support and radial restraint for the head of the booster rocket 16 during horizontal docking with the payload spacecraft 17 and after docking.

[0089] The structure of the front booster support 8 is basically similar to that of the rear booster support 7, mainly including the front booster support base 8-6, the front booster support slider 8-9, the front booster support lifting and rotating component 8-5, the screw lift, the front booster support guide column 8-7, the front booster support transverse sliding seat 8-3, the front booster support transverse sliding mechanism 8-4, the front booster support support seat 8-2, the front booster support fixing assembly 8-8, and the front booster support radial clamping mechanism 8-1. Through these structures, the front booster support 8 integrates the axial sliding mechanism, the lifting mechanism, the transverse sliding mechanism, and the radial clamping mechanism, enabling multi-dimensional position adjustment and reliable fixation of the booster rocket 16 head in a horizontal state.

[0090] (1) Axial sliding mechanism An axial sliding mechanism is used to drive the corresponding support to slide along the length of the load-bearing tilting arm 1. Specifically, the booster front support base 8-6 serves as the mounting base for the booster front support 8, and two sets of booster front support sliders 8-9 are installed on each of the left and right sides of the bottom of the booster front support base 8-6. The booster front support sliders 8-9 slide in cooperation with the sliding guide rails 1-6 provided on the upper two longitudinal beams of the load-bearing tilting arm 1, forming an axial sliding mechanism. Through this axial sliding mechanism, the booster front support 8 as a whole can be axially adjusted along the length of the load-bearing tilting arm 1 to accommodate booster rockets 16 of different lengths. After the axial position is adjusted to the correct position, the booster front support base 8-6 is fixed and locked to the load-bearing tilting arm 1 by the booster front support fixing assembly 8-8 to prevent accidental displacement during subsequent docking and erection operations.

[0091] (2) Lifting mechanism A screw jack is fixedly installed on each of the left and right sides of the upper part of the booster front support base 8-6, with the two screw jacks arranged symmetrically. The booster front support lifting rotating component 8-5 is a drive shaft that runs horizontally through the two screw jacks. One end of the shaft is rotatably connected to the booster front support base 8-6 via a bearing seat or fixed seat, and the other end is drively connected to the input end of the two screw jacks. The end of the booster front support lifting rotating component 8-5 is provided with a drive interface, which can be connected to a manual crank or a power drive device. When the booster front support lifting rotating component 8-5 is rotated, the two screw jacks move synchronously, converting their rotational motion into linear motion of the lifting end, thus forming the lifting mechanism.

[0092] The lifting end of the spiral lift is fixedly connected to the front booster support transverse shift seat 8-3. By driving the lifting mechanism to rotate, the front booster support transverse shift seat 8-3 and its upper components can move smoothly up and down in a direction perpendicular to the bearing surface of the bearing tilting arm 1, thereby precisely adjusting the support height of the booster rocket 16 head.

[0093] Two guide columns 8-7 are also provided on the front support base 8-6, spaced apart between the two screw jacks. Each guide column 8-7 is arranged vertically, with its lower end fixedly connected to the front support base 8-6, and its upper end passing through the corresponding guide hole on the front support transverse sliding seat 8-3, and can slide within the guide hole. The cooperation between the guide column 8-7 and the guide hole plays a guiding role during the lifting process, ensuring the smoothness and directional accuracy of the lifting movement. At the same time, after the rotating arm 1 is raised to the vertical position, it enhances the overall rigidity of the front support 8 and shares the bending moment load on the screw of the screw jack.

[0094] (3) Transverse movement mechanism Two sets of transverse guide rails are provided on the upper part of the booster front support transverse sliding seat 8-3 along both sides perpendicular to the length direction of the bearing tilting arm 1. Four sets of sliders are installed at the bottom of the booster front support support 8-2. These sliders slide in engagement with the transverse guide rails on the upper part of the booster front support transverse sliding seat 8-3, forming a transverse sliding mechanism. The booster front support transverse sliding mechanism 8-4 is mounted on the booster front support transverse sliding seat 8-3 and is drively connected to the booster front support support 8-2. By manually or power-driven rotation of the booster front support transverse sliding mechanism 8-4, the booster front support support 8-2 can be driven to move laterally in the horizontal direction perpendicular to the length direction of the bearing tilting arm 1, thereby adjusting the transverse support position of the booster rocket 16's nose section.

[0095] The booster front support 8-2 is a plate-shaped structure with an arc-shaped support in the middle that matches the shape of the head of the booster rocket 16. The surface of the arc-shaped support is covered with flexible materials such as felt to protect the surface of the rocket body from damage when supporting the booster rocket 16.

[0096] (4) Radial clamping mechanism The radial clamping mechanism 8-1 of the booster front support is set on both sides of the arc-shaped support bracket of the booster front support 8-2. It is used to clamp the side wall of the booster rocket 16 after the booster rocket 16 is hoisted into place, so as to achieve radial limit.

[0097] The radial clamping mechanism 8-1 for the booster front support includes a mounting base, a clamping drive motor, a transmission mechanism, and a clamping arm. The mounting base is located at the end of the booster front support base 8-2, and the clamping drive motor and transmission mechanism are mounted on the mounting base. The transmission mechanism employs a drive shaft structure, which is rotatably connected to the upper middle part of the clamping arm.

[0098] The clamping arms of the two radial clamping mechanisms 8-1 for the booster front support are positioned opposite each other on both sides of the arc-shaped support. The bottom of the clamping arms is rotatably connected to the booster front support base 8-2. This rotatable connection is located between the connection point between the mounting base and the booster front support base 8-2 and the arc-shaped support, but closer to the arc-shaped support. The clamping arms are curved, and the two clamping arms together form an arc-shaped clamping space that conforms to the shape of the side wall of the booster rocket 16. Each clamping arm has an arc-shaped clamping block at its end, the curvature of which conforms to the shape of the side wall of the booster rocket 16.

[0099] The drive shaft is connected to the upper middle part of the clamping arm in an inclined manner. The advantages of this connection method are: by setting the drive point in the upper middle part of the clamping arm, a larger clamping force can be obtained with a small drive stroke by utilizing the lever principle, thereby improving clamping efficiency; at the same time, the inclined drive allows the clamping arm to generate a downward component force during rotation, enhancing the stability of the connection point between the clamping arm and the support bracket, making the clamping arm more stable in the clamping state; in addition, the arrangement of the bottom rotation connection point of the clamping arm close to the arc-shaped support bracket shortens the distance from the clamping point to the fulcrum, further improving the clamping rigidity and ensuring that the booster rocket 16 will not undergo radial displacement during erection and launch preparation.

[0100] Driven by the clamping drive motor, the two clamping arms rotate relative to each other around their bottom pivot axis, causing the arc-shaped clamping block to move closer to and clamp the side wall of booster rocket 16 until the arc-shaped clamping block is tightly fitted to the side wall of booster rocket 16, achieving reliable radial limiting. When it is necessary to release the limiting, the clamping drive motor reverses to drive the clamping arms to open, releasing booster rocket 16.

[0101] Through the above structure, the booster front support 8 integrates a position adjustment mechanism with three dimensions of axial sliding, lifting, and lateral movement, as well as a radial clamping mechanism, providing comprehensive adjustment means for the precise positioning and reliable fixation of the booster rocket 16 in a horizontal state, ensuring that the booster rocket 16 and the payload spacecraft 17 can achieve high-precision coaxial docking.

[0102] (ix) Load rear support like Figure 3 and Figure 6 As shown, the rear load support 9 is located at the front of the front booster support 8. It is used to provide support for the tail of the load vehicle 17 during horizontal docking of the booster rocket 16 and the load vehicle 17 and after docking is completed. It also has the function of adjusting the roll attitude.

[0103] The structure of the rear payload support 9 is basically similar to that of the rear booster support 7 and the front booster support 8, but a roll mechanism is added to achieve roll attitude adjustment of the payload vehicle 17. The rear payload support 9 mainly includes a rear payload support base 9-7, a rear payload support slider 9-9, a rear payload support lifting and rotating component 9-6, a spiral lift, a rear payload support guide column 9-8, a rear payload support lateral shift seat 9-5, a rear payload support lateral shift mechanism 9-4, a rear payload support roll support seat 9-2, a rear payload support roll mechanism 9-3, a rear payload support support 9-1, and a rear payload support fixing assembly 9-10. Through these structures, the rear payload support 9 integrates an axial sliding mechanism, a lifting mechanism, a lateral shift mechanism, and a roll mechanism, enabling multi-dimensional position adjustment and roll attitude adjustment of the tail of the payload vehicle 17 in a horizontal state.

[0104] (1) Axial sliding mechanism The load rear support base 9-7 serves as the mounting foundation for the load rear support 9, with a set of load rear support sliders 9-9 installed on each of its bottom left and right sides. The load rear support sliders 9-9 slide in conjunction with the sliding guide rails 1-6 on the upper longitudinal beams of the load-bearing tilting arm 1, forming an axial sliding mechanism. Through this axial sliding mechanism, the load rear support 9 can be axially adjusted along the length of the load-bearing tilting arm 1 to accommodate payload aircraft 17 of different lengths. Once the axial position is adjusted, the load rear support base 9-7 is fixed and locked to the load-bearing tilting arm 1 by the load rear support fixing assembly 9-10 to prevent accidental displacement during subsequent docking and erection operations.

[0105] (2) Lifting mechanism A screw jack is fixedly installed on each of the left and right sides of the upper part of the load rear support base 9-7, with the two screw jacks arranged symmetrically. The load rear support lifting rotating component 9-6 is a drive shaft that runs horizontally through the two screw jacks. One end of the drive shaft is rotatably connected to the load rear support base 9-7 via a bearing seat or fixed seat, and the other end is drively connected to the input end of the two screw jacks. The end of the load rear support lifting rotating component 9-6 is provided with a drive interface, which can be connected to a manual crank or a power drive device. When the load rear support lifting rotating component 9-6 is rotated, the two screw jacks move synchronously, converting their rotational motion into linear motion of the lifting end, thus forming a lifting mechanism.

[0106] The lifting end of the spiral lift is fixedly connected to the load rear support transverse shift seat 9-5. By driving the lifting mechanism to rotate, the load rear support transverse shift seat 9-5 and its upper components can be driven to move smoothly up and down in a direction perpendicular to the bearing surface of the load-bearing tilting arm 1, thereby precisely adjusting the support height of the tail of the load aircraft 17.

[0107] Two load rear support guide columns 9-8 are also provided on the load rear support base 9-7, spaced apart between the two screw jacks. Each load rear support guide column 9-8 is arranged vertically, with its lower end fixedly connected to the load rear support base 9-7, and its upper end passing through the corresponding guide hole on the load rear support transverse sliding seat 9-5, and can slide within the guide hole. The cooperation between the load rear support guide column 9-8 and the guide hole plays a guiding role during the lifting process, ensuring the smoothness and directional accuracy of the lifting movement. At the same time, after the load-bearing tilting arm 1 is raised to the vertical position, it enhances the overall rigidity of the load rear support 9 and shares the bending moment load on the screw of the screw jack.

[0108] (3) Transverse movement mechanism Two sets of transverse guide rails are provided on the upper part of the load rear support transverse shift seat 9-5 along both sides perpendicular to the length direction of the load-bearing tilting arm 1. Four sets of sliders are installed at the bottom of the load rear support rolling support seat 9-2. These sliders slide in cooperation with the transverse guide rails on the upper part of the load rear support transverse shift seat 9-5, forming a transverse shifting mechanism. The load rear support transverse shifting mechanism 9-4 is mounted on the load rear support transverse shift seat 9-5 and is connected to the load rear support rolling support seat 9-2 via a transmission connection. By manually or electrically driving the load rear support transverse shifting mechanism 9-4 to rotate, the load rear support rolling support seat 9-2 and its upper components can be driven to move laterally in the horizontal direction perpendicular to the length direction of the load-bearing tilting arm 1, thereby adjusting the transverse support position of the tail of the load aircraft 17.

[0109] (4) Rolling mechanism The rear load support roll support 9-2 has a frame structure with an installation space in its middle. The rear load support support 9-1 has an arc-shaped structure and is located in the middle installation space of the rear load support roll support 9-2, and is used to support the tail of the load aircraft 17.

[0110] The load rear support roll mechanism 9-3 is a horizontally arranged rotating shaft. One end of this shaft is inserted into the load rear support roll support 9-2 and rotatably connected to the bottom of the load rear support support 9-1. The other end protrudes from the outside of the load rear support roll support 9-2, forming a drive interface. The load rear support support 9-1 is supported and installed inside the load rear support roll support 9-2 by the load rear support roll mechanism 9-3, and can rotate relative to the load rear support roll support 9-2 about the axis of the load rear support roll mechanism 9-3. By manually or electrically driving the rotation of the protruding end of the load rear support roll mechanism 9-3, the load rear support support 9-1 can roll in the vertical plane, thereby adjusting the roll attitude of the tail of the payload spacecraft 17 and ensuring precise alignment with the booster rocket 16.

[0111] The load rear support lateral movement mechanism 9-4 is another horizontally arranged rotating shaft, which is independent of and not connected to the load rear support rolling mechanism 9-3. The load rear support lateral movement mechanism 9-4 includes a fixed base and a rotating shaft. The fixed base is fixedly connected to the end of the load rear support lateral movement seat 9-5. One end of the rotating shaft is rotatably connected to the fixed base, and the other end is rotatably connected to the load rear support rolling support seat 9-2. By manually or electrically driving the load rear support lateral movement mechanism 9-4 to rotate, the load rear support rolling support seat 9-2 and its internal load rear support support 9-1 can be driven to slide along the transverse guide rail, achieving lateral movement and thus adjusting the lateral support position of the tail of the load vehicle 17.

[0112] Through the above structure, the payload rear support 9 integrates a position adjustment mechanism with four dimensions: axial sliding, lifting, lateral movement and rolling. The lateral movement and rolling are controlled by independent drive shafts, providing a comprehensive means of adjustment for the precise positioning and rolling attitude adjustment of the tail of the payload spacecraft 17 in a horizontal state, ensuring that the payload spacecraft 17 and the booster rocket 16 can achieve high-precision coaxial docking.

[0113] (x) Load front support like Figure 3 and Figure 6 As shown, the front load support 10 is located at the front of the rear load support 9, and is used to provide support and radial restraint for the head of the load vehicle 17 during horizontal docking of the booster rocket 16 and the load vehicle 17 and after docking is completed.

[0114] The structure of the payload front support 10 is basically similar to that of the booster front support 8, mainly including a payload front support base 10-7, a payload front support slider 10-9, a payload front support lifting and rotating component 10-6, a spiral lift, a payload front support guide column 10-8, a payload front support transverse sliding seat 10-4, a payload front support transverse sliding mechanism 10-5, a payload front support rolling support seat 10-2, a payload front support support 10-1, a payload front support fixing assembly 10-10, and a payload front support radial clamping mechanism 10-3. Through these structures, the payload front support 10 integrates an axial sliding mechanism, a lifting mechanism, a transverse sliding mechanism, and a radial clamping mechanism, enabling multi-dimensional position adjustment and reliable fixation of the payload spacecraft 17's head in a horizontal state.

[0115] (1) Axial sliding mechanism The load front support base 10-7 serves as the mounting foundation for the load front support 10, with two sets of load front support sliders 10-9 mounted on each of its bottom left and right sides. The load front support sliders 10-9 slide in conjunction with the sliding guide rails 1-6 on the upper longitudinal beams of the load-bearing tilting arm 1, forming an axial sliding mechanism. Through this axial sliding mechanism, the load front support 10 can be axially adjusted along the length of the load-bearing tilting arm 1 to accommodate payloads 17 of different lengths. Once the axial position is adjusted, the load front support base 10-7 is fixed and locked to the load-bearing tilting arm 1 by the load front support fixing assembly 10-10 to prevent accidental displacement during subsequent docking and erection operations.

[0116] (2) Lifting mechanism A screw jack is fixedly installed on each of the left and right sides of the upper part of the load front support base 10-7, with the two screw jacks arranged symmetrically. The load front support lifting rotating component 10-6 is a drive shaft that runs horizontally through both screw jacks. One end of the drive shaft is rotatably connected to the load front support base 10-7 via a bearing seat or fixed seat, and the other end is drively connected to the input end of the two screw jacks. The end of the load front support lifting rotating component 10-6 is provided with a drive interface, which can be connected to a manual crank or a power drive device. When the load front support lifting rotating component 10-6 is rotated, the two screw jacks move synchronously, converting their rotational motion into linear motion of the lifting end, thus forming a lifting mechanism.

[0117] The lifting end of the spiral jack is fixedly connected to the load front support transverse shift seat 10-4. By driving the lifting mechanism to rotate, the load front support transverse shift seat 10-4 and its upper components can be driven to move smoothly up and down in a direction perpendicular to the bearing surface of the load-bearing tilting arm 1, thereby precisely adjusting the support height of the head of the load aircraft 17.

[0118] Two load front support guide columns 10-8 are also provided on the load front support base 10-7, spaced apart between the two screw jacks. Each load front support guide column 10-8 is arranged vertically, with its lower end fixedly connected to the load front support base 10-7, and its upper end passing through the corresponding guide hole on the load front support transverse sliding seat 10-4, and can slide within the guide hole. The cooperation between the load front support guide column 10-8 and the guide hole plays a guiding role during the lifting process, ensuring the smoothness and directional accuracy of the lifting movement. At the same time, after the load tilting arm 1 is raised to the vertical position, it enhances the overall rigidity of the load front support 10 and shares the bending moment load on the screw of the screw jack.

[0119] (3) Transverse movement mechanism Two sets of transverse guide rails are provided on the upper part of the load front support transverse shift seat 10-4 along both sides perpendicular to the length direction of the load-bearing tilting arm 1. Four sets of sliders are installed at the bottom of the load front support rolling support seat 10-2. These sliders slide in cooperation with the transverse guide rails on the upper part of the load front support transverse shift seat 10-4 to form a transverse shifting mechanism. The load front support transverse shifting mechanism 10-5 is set on the load front support transverse shift seat 10-4 and is drivenly connected to the load front support rolling support seat 10-2. By manually or power-drivenly rotating the load front support transverse shifting mechanism 10-5, the load front support rolling support seat 10-2 and its upper components can be driven to move laterally in the horizontal direction perpendicular to the length direction of the load-bearing tilting arm 1, thereby adjusting the transverse support position of the head of the load aircraft 17.

[0120] (4) Rolling structure The load front support roll support 10-2 is a frame structure with an installation space in its middle. The load front support support 10-1 is an arc-shaped structure, located in the middle installation space of the load front support roll support 10-2, and is used to support the nose of the load aircraft 17.

[0121] The front load support 10-1 is installed inside the front load roll support 10-2 in the same manner as the rear load roll mechanism 9-3. Specifically, the rear load roll mechanism 9-3 is a horizontally arranged rotating shaft. One end of the shaft is inserted into the front load roll support 10-2 and rotatably connected to the bottom of the front load support 10-1, while the other end protrudes from the outside of the front load roll support 10-2. The rolling motion of the front load support 10-1 on the upper part of the front load roll support 10-2 is driven by the rear load roll mechanism 9-3. By manually or electrically driving the rotation of the protruding end of the rear load roll mechanism 9-3, the front load support 10-1 can roll in the vertical plane, thereby adjusting the rolling attitude of the head of the payload spacecraft 17 and ensuring precise alignment with the booster rocket 16.

[0122] The upper part of the load front support support 10-1 has an arc-shaped support surface that is adapted to the shape of the head of the load vehicle 17. The surface of the arc-shaped support surface is covered with flexible materials such as felt to protect the surface of the rocket body from damage when supporting the load vehicle 17.

[0123] (5) Radial clamping mechanism The radial clamping mechanism 10-3 of the load front support is set on both sides of the arc-shaped support surface of the load front support support 10-1, and is used to clamp the side wall of the load aircraft 17 after the load aircraft 17 is hoisted into place to achieve radial limit.

[0124] The radial clamping mechanism 10-3 for the load front support includes a mounting base, a clamping drive motor, a transmission mechanism, and a clamping arm. The mounting base is located at the end of the load front support 10-1, and the clamping drive motor and transmission mechanism are mounted on the mounting base. The transmission mechanism uses a drive shaft structure, which is rotatably connected to the upper middle part of the clamping arm.

[0125] The clamping arms of the two radial clamping mechanisms 10-3 for the front load supports are positioned opposite each other on both sides of the arc-shaped support surface. The bottom of the clamping arms is rotatably connected to the front load support support 10-1, with this rotatable connection located between the connection point between the mounting base and the front load support support 10-1 and the arc-shaped support surface, but closer to the arc-shaped support surface. The clamping arms are curved, and the two clamping arms together form an arc-shaped clamping space that conforms to the shape of the side wall of the load vehicle 17. Each clamping arm has an arc-shaped clamping block at its end, the curvature of which conforms to the shape of the side wall of the load vehicle 17.

[0126] The drive shaft is connected to the upper middle part of the clamping arm in an inclined manner. The advantages of this connection method are: by setting the drive point in the upper middle part of the clamping arm, a larger clamping force can be obtained with a small drive stroke by utilizing the lever principle, thereby improving clamping efficiency; at the same time, the inclined drive allows the clamping arm to generate a downward component force during rotation, enhancing the stability of the connection point between the clamping arm and the support bracket, making the clamping arm more stable in the clamping state; in addition, the arrangement of the bottom rotation connection point of the clamping arm close to the arc-shaped support surface shortens the distance from the clamping point to the fulcrum, further improving the clamping rigidity and ensuring that the payload spacecraft 17 will not undergo radial displacement during erection and launch preparation.

[0127] Driven by the clamping drive motor, the two clamping arms rotate relative to each other around their bottom pivot axis, causing the arc-shaped clamping block to move closer to and clamp the side wall of the payload aircraft 17 until the arc-shaped clamping block is tightly fitted to the side wall of the payload aircraft 17, achieving reliable radial limiting. When it is necessary to release the limiting, the clamping drive motor reverses to drive the clamping arms to open, releasing the payload aircraft 17.

[0128] Through the above structure, the front load support 10 integrates a position adjustment mechanism with three dimensions of axial sliding, lifting and lateral movement, as well as a radial clamping mechanism. At the same time, its rolling motion is driven by the rear load support rolling mechanism 9-3, providing a comprehensive adjustment means for the precise positioning and reliable fixation of the head of the payload spacecraft 17 in a horizontal state, ensuring that the payload spacecraft 17 and the booster rocket 16 can achieve high-precision coaxial docking.

[0129] It should be noted that the fixing components of each bracket include two symmetrically arranged locking parts, which are used to reliably fix the bracket base to the load-bearing tilting arm after the axial position of the bracket is adjusted to the correct position, ensuring that the locking force is evenly distributed and preventing displacement during subsequent operations.

[0130] (xi) Connector separation mechanism like Figure 1 and Figure 11 As shown, the connector separation mechanism 11 is located at the center of the front of the bearing flip arm 1 and in front of the load front support 10. It is used to automatically pull out the disconnect connector of the load vehicle 17 from the socket before the booster rocket 16 is ignited and launched, so as to realize the electrical separation of the load vehicle 17 from the ground test system.

[0131] The connector separation mechanism 11 mainly includes a pull-out mechanism base 11-1, a sliding guide rail 11-11, a sliding block 11-12, a moving seat 11-13, a front stop 11-2, a rear stop 11-3, a transverse drive screw 11-4, a linear drive mounting seat 11-5, a linear drive 11-6, an adapter seat 11-7, an adapter pull ring 11-8, a traction ring 11-9, and a disconnect cable 11-10.

[0132] The base 11-1 of the pull-out mechanism serves as the mounting base for the connector separation mechanism 11 and is fixedly mounted on the front of the bearing flip arm 1. A sliding guide rail 11-11 is provided on the upper part of the base 11-1 along the length of the bearing flip arm 1. The sliding guide rail 11-11 is a linear guide rail structure used to guide the sliding of the moving seat 11-13.

[0133] The movable seat 11-13 is slidably mounted on the sliding guide rail 11-11 via the sliding block 11-12. The sliding block 11-12 and the sliding guide rail 11-11 are slidably engaged, allowing the movable seat 11-13 to slide smoothly along the length of the carrying tilting arm 1.

[0134] The movable seats 11-13 are used to install and support components connected to the disconnect connector, and their position can be adjusted axially to accommodate the disconnect connector position of different types of payload aircraft 17.

[0135] The transverse drive screw 11-4 is arranged along the length of the bearing tilting arm 1. One end of it is rotatably connected to the base 11-1 of the release mechanism, and the other end is provided with a drive interface for connecting a manual crank. The transverse drive screw 11-4 is threadedly connected to the moving seat 11-13. When the transverse drive screw 11-4 is manually rotated, the moving seat 11-13 is driven to move axially along the sliding guide rail 11-11 via the threaded drive, thereby adjusting the moving seat 11-13 to a position directly below the release connector of the payload aircraft 17. After adjustment, the moving seat 11-13 can be fixed by the locking mechanism.

[0136] The front stop 11-2 and rear stop 11-3 are respectively located at the front and rear ends of the base 11-1 of the extraction mechanism, cooperating with the movable seat 11-13 to limit the axial sliding range of the movable seat 11-13, thus acting as a front and rear limiter to prevent the movable seat 11-13 from exceeding its safe stroke due to operational errors or unexpected situations, ensuring the safe operation of the mechanism. The linear drive mounting seat 11-5 is fixedly mounted on the movable seat 11-13 for mounting the linear drive 11-6. The linear drive 11-6 is an electric push rod, its drive end of which is fixedly connected to the adapter 11-7. The linear drive 11-6 can receive remote control commands to perform extension or retraction actions.

[0137] The adapter 11-7 is fixedly connected to the drive end of the linear drive 11-6. One end of the adapter pull ring 11-8 is fixedly connected to the adapter 11-7, and the other end is connected to the traction ring 11-9. The traction ring 11-9 is a ring structure and can adopt various shapes such as O-type, U-type, or C-type, and is used to connect to the steel wire rope on the de-plug connector of the payload spacecraft 17. The de-plug cable 11-10 is electrically connected to the de-plug connector of the payload spacecraft 17 and is used to transmit electrical signals during the ground testing and preparation phase before launch.

[0138] In the connector separation mechanism 11, the connecting parts that connect to the disconnect connector include an adapter 11-7, an adapter pull ring 11-8, and a traction ring 11-9. The traction ring 11-9 is an actuating component that directly connects to the wire rope of the disconnect connector. The adapter pull ring 11-8 connects the traction ring 11-9 to the adapter 11-7, and the adapter 11-7 is fixedly connected to the drive end of the linear push rod 11-6.

[0139] The working principle of the connector separation mechanism 11 is as follows: First, after the booster rocket 16 and the payload spacecraft 17 are docked, manually rotate the transverse drive screw 11-4 to drive the moving seat 11-13 to move axially, adjust it to the position directly below the disconnector of the payload spacecraft 17, and lock it in place.

[0140] Then, the linear drive 11-6 is extended remotely, and the drive end of the linear drive 11-6 drives the adapter 11-7, the adapter pull ring 11-8, and the traction ring 11-9 to extend upwards simultaneously. When the position sensor detects that the traction ring 11-9 has extended to the correct position, the operator connects the traction ring 11-9 to the wire rope on the disconnect connector.

[0141] When a disengagement operation is required (usually at T0-1 minute before launch), the remote control system issues a disengagement command. The linear drive component 11-6 retracts, simultaneously retracting the adapter 11-7, adapter pull ring 11-8, and traction ring 11-9 downwards. The traction ring 11-9 pulls the disengagement connector via a steel cable, smoothly pulling it out of the socket on the payload spacecraft 17, achieving electrical separation. After disengagement, the positioning sensor sends a retraction signal to the control system for confirmation. T0 is the reference time for rocket ignition and liftoff; T0-1 minute represents one minute before launch.

[0142] Through the above structure, the connector separation mechanism 11 realizes remote automatic disconnection and disconnection of the payload spacecraft 17 connector, avoiding the safety risks of manual disconnection operation and improving the automation and reliability of launch preparation.

[0143] The improvement of this invention is as follows: (1) Integrated horizontal docking and overall erection design: Through the coordinated work of the booster rear support 7, booster front support 8, payload rear support 9 and payload front support 10, each support integrates multi-dimensional position adjustment mechanisms such as axial sliding, lifting, lateral movement and rolling. When the load-bearing tilting arm 1 is in a horizontal state, the relative position of the booster rocket 16 and the payload spacecraft 17 can be precisely adjusted to achieve coaxial docking of the two. After docking, it can be directly erected to the vertical launch state. This design solves the problem in the existing technology that lightweight spacecraft cannot withstand the bending moment of overall hoisting, avoids the complicated process of overall transportation or hoisting to the launch pad after docking in the factory in the traditional solution, and significantly improves the safety of launch preparation work.

[0144] (2) Adjustable support and auxiliary tensioning co-fixing structure: An auxiliary tensioning mechanism 1-2 is provided at the front end of the load-bearing tilting arm 1, which works in conjunction with the auxiliary tensioning block 2-2 on the tail bracket 2 to rigidly connect the assembly 18 to the load-bearing tilting arm 1 during the erection process. The multi-dimensional adjustment mechanism of each support and the auxiliary tensioning mechanism work together to ensure both the position adjustment accuracy during docking and the structural stability during the erection process. Compared with the existing fixed support scheme which is only used for limiting position, the adjustable support structure of the present invention realizes the dual functions of docking adjustment and erection fixation.

[0145] (3) Modular compatibility design: Adopting a modular design approach, based on the different diameters of the booster rocket 16 and the special configuration of the payload vehicle 17, different specifications of the load-bearing tilting arm 1 and tail bracket 2 can be replaced to quickly adapt to various flight mission requirements. The load-bearing tilting arm 1 and tail bracket 2 are independent replaceable modules, integrating mounting interfaces and auxiliary tensioning interfaces compatible with various models. They can be quickly switched without changing the main structure of the base 4, centralized control cabin 6, etc., which significantly improves the versatility of the launch device and the mission response speed.

[0146] Through the above structural design, this invention achieves the integrated horizontal docking and overall erection of the booster rocket 16 and the payload spacecraft 17 on the launch platform, avoiding the risk of damage to the lightweight spacecraft structure caused by the bending moment load generated by the overall hoisting in the traditional scheme; the multi-dimensional position adjustment mechanism of each support provides a precise adjustment means for the docking process, significantly improving docking accuracy and efficiency; the integrated centralized control cabin design and automated erection control system simplify the launch preparation process and shorten the launch cycle; the compatibility design allows the same launch platform to be adapted to multiple types of booster rockets and payload spacecraft, reducing equipment costs and improving the flexibility and economy of launch missions.

[0147] Second Embodiment This embodiment provides a launching method based on the vertical launching device described in the first embodiment above, specifically including the following steps: Step 1: Hoist the booster rocket 16 onto multiple supports on the load-bearing tilting arm 1.

[0148] The generator set 13 is started to supply power to the device, and the electrical control box 14 is activated to open the radial clamping mechanism 8-1 of the front booster support 8 to the designated position. The booster rocket 16 is then hoisted onto the supporting tilting arm 1 using hoisting equipment and slowly lowered so that the tail of the booster rocket 16 lands on the support support 7-1 of the rear booster support 7, and the nose lands on the support support 8-2 of the front booster support 8. The surfaces of the support supports of the rear booster support 7 and the front booster support 8 are covered with flexible materials such as felt to protect the surface of the booster rocket 16.

[0149] Step two: Connect the tail support 2 to the tail of the booster rocket 16.

[0150] By connecting the lifting equipment via rotating lifting ring 2-5, the tail support 2 is flipped from its transport position on the upper part of the launch pad 3 to the tail end face of the booster rocket 16. The position of the tail support 2 is adjusted to align it with the tail flange of the booster rocket 16, and fasteners are used to reliably connect the tail support 2 to the tail of the booster rocket 16. At the same time, the auxiliary tensioning mechanism 1-2 at the front end of the carrying tilting arm 1 is connected to the auxiliary tensioning block 2-2 on the tail support 2 via quick-release pins, forming a rigid connection between the carrying tilting arm 1, the tail support 2, and the booster rocket 16, ensuring the stability of the subsequent erection process.

[0151] Step 3: Hoist the payload aircraft 17 onto multiple supports on the load-bearing tilting arm 1.

[0152] Open the radial clamping mechanism 10-3 of the front load support 10 to the designated position. Using hoisting equipment, lift the load vehicle 17 above the load-bearing tilting arm 1 and slowly lower it so that the tail of the load vehicle 17 lands on the support bracket 9-1 of the rear load support 9, and the head lands on the support bracket 10-1 of the front load support 10. The surfaces of the support brackets of both the rear load support 9 and the front load support 10 are also covered with flexible materials such as felt to protect the shell surface of the load vehicle 17.

[0153] Step four: By adjusting the position adjustment mechanism of at least part of the support, the payload spacecraft 17 and the booster rocket 16 are coaxially docked in a horizontal state to form a combined body 18.

[0154] The radial clamping mechanism 10-3 of the drive payload front support 10 clamps the head of the payload spacecraft 17 into place. The payload spacecraft 17 is then pushed towards the booster rocket 16, gradually bringing the two closer together. Based on the actual situation during the docking process, the position adjustment mechanisms of the payload rear support 9 and the payload front support 10 are adjusted respectively. By rotating the rear load support lifting mechanism 9-6 and the front load support lifting mechanism 10-6, the support height of the load vehicle 17 is adjusted so that it is aligned with the axis height of the booster rocket 16. By rotating the load rear support transverse movement mechanism 9-4 and the load front support transverse movement mechanism 10-5, the lateral position of the load spacecraft 17 is adjusted to achieve lateral alignment with the booster rocket 16. By rotating the load rear support rolling mechanism 9-3, the rolling attitude of the load vehicle 17 is adjusted to ensure its circumferential alignment with the booster rocket 16.

[0155] like Figure 4 As shown, after the docking surfaces of the payload spacecraft 17 and the booster rocket 16 are fully aligned, coaxial docking is completed, forming the assembly 18. After docking, the transverse drive screw 11-4 of the drive connector separation mechanism 11 adjusts the moving seat 11-13 to a position directly below the disconnect connector of the payload spacecraft 17 and locks it. The remote-controlled linear push rod 11-6 extends, causing the traction ring 11-9 to extend upward, connecting the traction ring 11-9 to the steel wire rope on the disconnect connector.

[0156] Step 5: Drive the load-bearing tilting arm 1 to rotate relative to the base 4, so that the assembly 18 is raised from the horizontal state to the vertical state.

[0157] The erection program of the electrical control box 14 is initiated. Upon receiving the erection signal, the erection cylinder 12 extends its piston rod, pushing the load-bearing tilting arm 1 to rotate smoothly around the trunnion on the base 4. The load-bearing tilting arm 1 drives the assembly 18 on it to gradually rise from a horizontal state to a vertical state. During the erection process, the auxiliary tensioning mechanism 1-2 and the auxiliary tensioning block 2-2 remain connected to ensure that the relative position of the assembly 18 and the load-bearing tilting arm 1 is fixed.

[0158] like Figure 10 As shown, when the assembly 18 reaches the vertical position, the lower surface of the tail support 2 is attached to the tail support base 3-5 of the launch pad 3, and the tail support 2 and the launch pad 3 are reliably locked together using fasteners. The tilt sensor on the erection cylinder 12 monitors the erection angle in real time to ensure that the angle between the assembly 18 and the horizontal plane reaches 90°.

[0159] Step six: Separate the load-bearing tilting arm 1 from the assembly 18 and return the load-bearing tilting arm 1 to a horizontal position.

[0160] Thirty minutes before launch, disconnect the auxiliary tensioning mechanism 1-2 from the tail support 2, and release the rigid connection between the load-bearing tilting arm 1 and the assembly 18. Open the radial clamping mechanism 8-1 of the booster front support 8 to release the booster rocket 16. One minute before launch, remotely control the linear push rod 11-6 to retract, causing the traction ring 11-9 to move downwards, smoothly pulling the disconnect connector out of the socket on the payload spacecraft 17 via a steel cable, and the positioning sensor provides feedback on the retraction position signal. Remotely control the radial clamping mechanism 10-3 of the payload front support 10 to open, releasing the payload spacecraft 17. After confirming that all radial clamping mechanisms are open, remotely control the erection cylinder 12 to retract, smoothly lowering the load-bearing tilting arm 1 back to a horizontal position.

[0161] Step 7: Ignite and launch booster rocket 16.

[0162] like Figure 12 As shown, after all launch preparations are completed, the operators evacuate to a safe area. The ground control system issues an ignition command, booster rocket 16's engine ignites, and the combined rocket assembly 18 takes off vertically under thrust. During launch, the deflector 3-3 on launch pad 3 guides the high-temperature exhaust gas ejected from the tail of booster rocket 16 through a double-sided deflector structure to both sides of the device, preventing backflow of exhaust gas from damaging the launch device and rocket body. Booster rocket 16 propels payload spacecraft 17 into the air, where it performs its flight mission according to the predetermined flight profile.

[0163] Through the above steps, this embodiment realizes the horizontal docking, overall erection and automated launch preparation of the booster rocket 16 and the payload spacecraft 17 on the launch platform. It effectively avoids the risk of damage to the lightweight spacecraft structure caused by the bending moment load generated by the overall hoisting in the traditional scheme, simplifies the launch process and improves the safety and efficiency of the launch preparation work.

[0164] It should be understood that the various forms of processes shown above can be used to reorder, add, or delete steps. For example, the steps described in this invention can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution disclosed in this invention can be achieved, and this is not limited herein.

[0165] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A vertical launching device with horizontal docking function, characterized in that, include: Base (4); The load-bearing tilting arm (1) is rotatably mounted on the base (4), and the load-bearing tilting arm (1) has a load-bearing surface for supporting the booster rocket (16) and the payload spacecraft (17); Tail bracket (2) is detachably mounted on the tail end of the bearing tilting arm (1) for detachable connection with the tail of the booster rocket (16); Multiple supports are arranged sequentially on the bearing surface along the length direction of the bearing tilting arm (1) to support the booster rocket (16) and the payload spacecraft (17). Among them, at least part of the support includes a position adjustment mechanism for adjusting the support position, for adjusting the relative position of the booster rocket (16) and the payload spacecraft (17) when the load-bearing flip arm (1) is in a horizontal state, so as to achieve coaxial docking, and the docked assembly is raised to a vertical launch state by the load-bearing flip arm (1).

2. The vertical launching device according to claim 1, characterized in that, The plurality of supports include: The booster rear support (7) is used to support the tail of the booster rocket 16; The front booster support (8) is located in front of the rear booster support (7) and is used to support the head of the booster rocket (16); The rear load support (9) is located in front of the front booster support (8) and is used to support the tail of the load vehicle (17). The front load support (10) is located in front of the rear load support (9) and is used to support the head of the load aircraft (17).

3. The vertical launching device according to claim 2, characterized in that, The booster front support (8) and / or the load front support (10) include a radial clamping mechanism for clamping the sidewall of the booster rocket (16) or the load vehicle (17) to achieve radial limiting.

4. The vertical launching device according to claim 2, characterized in that, The position adjustment mechanism includes at least one of the following: A lifting mechanism is used to drive the corresponding support to move up and down in a direction perpendicular to the bearing surface; A lateral movement mechanism is used to drive the corresponding support to move laterally in a horizontal direction perpendicular to the length of the bearing flipping arm (1); An axial sliding mechanism is used to drive the corresponding support to slide along the length direction of the bearing tilting arm (1); A rolling mechanism is used to drive the corresponding support to rotate around the length direction of the load-bearing flip arm (1) in order to adjust the rolling attitude of the load aircraft (17).

5. The vertical launching device according to claim 1, characterized in that, It also includes an auxiliary tensioning mechanism (1-2), which is mounted on the bearing tilting arm (1), and the tail bracket (2) is provided with an auxiliary tensioning block (2-2) corresponding to the auxiliary tensioning mechanism (1-2). The auxiliary tensioning mechanism (1-2) is detachably connected to the auxiliary tensioning block (2-2) and is used to fix the assembly (18) consisting of the booster rocket (16) and the payload vehicle (17) to the load-bearing tilting arm (1) during the erection process.

6. The vertical launching device according to claim 1, characterized in that, It also includes a connector separation mechanism (11), which is located at the front of the load-bearing flip arm (1) for connecting to the disconnect connector of the payload aircraft (17) and performing a disconnection operation before launch.

7. The vertical launching device according to claim 6, characterized in that, The connector separation mechanism (11) includes: Linear drive components (11-6); The movable seat (11-13) is slidably disposed on the base (11-1) of the connector separation mechanism (11) and connected to the drive end of the linear drive (11-6); A connector, disposed on the movable base (11-13), is used to connect with the disconnect connector; The linear drive (11-6) drives the movable base (11-13) to move, thereby causing the connector to pull the disconnector out of the socket.

8. The vertical launching device according to claim 1, characterized in that, Also includes: Launch pad (3) is located at the tail end of the base (4) and is used to support the combination (18) consisting of the tail bracket (2), the booster rocket (16) and the payload vehicle (17) after it is erected. A flow deflector (3-3) is installed on the launch pad (3) to deflect the hot flow ejected from the tail of the booster rocket (16) during launch.

9. The vertical launching device according to claim 1, characterized in that, Also includes: A centralized control cabin (6) is located at the front of the base (4). The centralized control cabin (6) integrates at least one of a generator set (13), an electrical control box (14), and a hydraulic pump station (15). The lifting cylinder (12) is connected to the base (4) and the bearing tilting arm (1) respectively, and is used to drive the bearing tilting arm (1) to rotate relative to the base (4).

10. A launching method based on the vertical launching device according to any one of claims 1-9, characterized in that, Includes the following steps: The booster rocket (16) is hoisted onto multiple supports on the load-bearing tilting arm (1); Connect the tail bracket (2) to the tail of the booster rocket (16); The payload aircraft (17) is hoisted onto multiple supports on the load-bearing tilting arm (1); By adjusting the position adjustment mechanism of at least part of the support, the payload spacecraft (17) and the booster rocket (16) are coaxially docked in a horizontal state to form a combination (18). Drive the load-bearing tilting arm (1) to rotate relative to the base (4), and raise the assembly (18) from the horizontal state to the vertical state; Separate the load-bearing tilting arm (1) from the assembly (18) and return the load-bearing tilting arm (1) to a horizontal position; Ignition launches booster rocket (16).

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