Aircraft launch pad and integrated transport and erect launch system

Abstract

This invention provides an aircraft launch pad and an integrated transport, erection, and launch system. The launch pad employs a modular design, enabling the transition between launch pad testing and launch states, and meeting the tensile and compressive load requirements of the testing conditions. Furthermore, through a rational layout and allocation of the launch pad's internal space, effective protection of the fueling and gas supply pipelines, and a modular design for the launch pad cover, the disassembly of the aircraft launch pad is facilitated, simplifying post-launch maintenance. The launch pad cover is electrically driven, while the docking device and the alignment and locking device with the erector carriage are hydraulically driven, significantly improving the automation level of the launch pad guide trough cover, docking device, and clamping device, saving manpower and increasing efficiency.

Description

Technical Field

[0001] This invention relates to the field of aerospace vehicle technology, and in particular to a launch pad and integrated transport, erection and launch system for a spacecraft. Background Technology

[0002] In recent years, with the development of aerospace technology, especially the rapid rise of various types of aircraft, particularly rockets propelled by the reaction force generated by the engine's propellant, my country is making every effort to advance the development of large-diameter aircraft to undertake the launch missions of large satellites. As the diameter of the aircraft increases, the size of the launch pad must also increase, as will the size of the guide channel. Furthermore, some reusable aircraft require launch, testing, and static ignition to be performed on the launch pad, resulting in longer ablation times and greater vibration levels. The launch pad must withstand not only significant compressive loads but also substantial tensile and vibration loads. Simultaneously, the overall structural layout and effective protection of the launch pad, as well as its coordination with the aircraft's erection and landing, must be considered.

[0003] Because the launch pad is large, the opening size is also large, the workload for personnel increases, and the preparation time for the aircraft before launch is longer.

[0004] Therefore, there is an urgent need to provide a transmitter system that can meet the requirements of high-frequency transmission. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention proposes an aircraft launch pad and an integrated transport, erection, and launch system, capable of flexibly switching between launch pad testing and launch states. Furthermore, the guide vane cover, docking, and clamping mechanisms are all automatically controlled, reducing manual operation, shortening pre-launch preparation time, and enabling high-frequency launches of the aircraft.

[0006] This invention provides an aircraft launch pad, comprising at least a platform body, a restraint and release device, an auxiliary support device, a flow guide trough cover, a positioning support device, and a clamping device. The platform body has a polygonal opening at its center, with the upper part of the opening for supporting the aircraft and the lower part for connecting to the flow guide trough. The restraint and release device and the auxiliary support device are alternately arranged around the opening for supporting and securing the aircraft. The positioning support device and the clamping device are located on one side of the platform body, wherein the positioning support device is used for positioning and supporting the aircraft launch pad during docking with a transport elevator, and the clamping device is used for docking the aircraft launch pad with the transport elevator. After the vertical vehicle is docked, the aircraft is locked and the aircraft is erected. The guide channel cover is set as a polygon matching the platform opening to cover the platform opening. The guide channel cover includes multiple triangular cover plates evenly divided by its angle bisector. The base of each triangular cover plate is rotatably set on the inner wall of the platform opening. The side of each triangular cover plate facing the inside of the platform opening is connected to the near-ground end of the platform body through an electric push rod. By controlling the electric push rod to retract, each triangular cover plate is pulled to rotate towards the ground to open the platform opening. By controlling the electric push rod to extend, each triangular cover plate is pushed to rotate away from the ground to the correct position to cover the platform opening.

[0007] In one embodiment, the platform includes a lower platform and an upper platform that are fixedly connected. The lower platform has at least a personnel passage, an equipment passage, a wiring passage, and a pipeline passage inside. The upper platform has at least a personnel operation through hole, a pipeline passage, and a wiring passage inside. One end of the restraint release device and the auxiliary support device are detachably mounted on the top of the lower platform through a conversion interface, and the other end extends beyond the top of the upper platform.

[0008] In one embodiment, the upper platform is provided with an upper platform plate on its top; the upper platform plate includes multiple platform plates of different sizes laid on the top plane of the upper platform; on the top plane of the upper platform, the platform plate closer to the platform opening is smaller than the platform plate farther away from the platform opening.

[0009] In one embodiment, the upper platform and the lower platform are square structures of the same shape; the restraint and release device is disposed on the axis of symmetry of the top plane of the lower platform, and the auxiliary support device is disposed on the angle bisector of the top plane of the lower platform.

[0010] In one embodiment, the opening of the upper platform is an octagonal cylindrical structure, and the opening of the lower platform is an octagonal trumpet-shaped structure with the wide opening facing downwards; the guide channel cover is matched with the opening of the upper platform, specifically by dividing it into eight triangular cover plates by its angle bisector; each of the triangular cover plates is driven to rotate around its base by the electric push rod, thereby realizing the opening and closing of the platform.

[0011] In one embodiment, each of the eight inner sides of the lower platform is provided with an electric push rod mounting hole. One end of the electric push rod passes through the mounting hole and is connected to the lower platform through a lower hinge point, while the other end is connected to the side of the triangular cover plate facing the platform opening through an upper hinge point. A fire-blocking protrusion is provided around the electric push rod mounting hole, and a fire-blocking recess is provided at the position where the electric push rod is installed on the triangular cover plate, matching the fire-blocking protrusion. By driving the electric push rod, the triangular cover plate is opened into place, so that the fire-blocking protrusion and the fire-blocking recess are fastened together to prevent flames from entering the electric push rod mounting hole.

[0012] In one embodiment, a recessed platform is provided on one side of the upper platform, and the clamping device is disposed on the side wall of the recessed platform; the positioning support device includes a launch pad receiving surface disposed on the plane of the recessed platform, and a guide positioning pin disposed on the launch pad receiving surface; the guide positioning pin provides high-precision positioning for the erection vehicle, and the launch pad receiving surface provides support for the aircraft erection process.

[0013] In one embodiment, the top of the auxiliary support device is provided with an opening for the connector to extend out and a protective cover; after the aircraft takes off, the connector detaches from the aircraft and retracts into the auxiliary support device, while the protective cover closes to block the opening and protect the connector and internal pipelines located in the auxiliary support device.

[0014] In one embodiment, a filling pipeline is provided on one side of the upper platform, and a protective device is provided on the outside of the filling pipeline.

[0015] Another aspect of the present invention provides an integrated transport, erection, and launch system, which includes at least an aircraft transport and erection vehicle and an aircraft launch pad as described in any of the above embodiments; after the transport and erection vehicle is transported to its position, it is positioned and docked with the aircraft launch pad by the positioning support device, and the clamping device clamps the positioned transport and erection vehicle to cooperate with the aircraft for erection.

[0016] The aircraft launch pad and integrated transport, erection and launch system provided by this invention have at least one of the following beneficial effects: I. The aircraft launch pad and integrated transfer, erection and launch system of the present invention can flexibly complete the conversion between launch pad test and launch states, saving the cost of building another work station.

[0017] Second, the guide channel cover, docking and pressing mechanism of the present invention can all be automatically controlled, reducing manual operation and shortening the pre-launch process preparation time.

[0018] Third, the internal layout of the launch pad of the present invention is reasonable and clear, which facilitates inspection and maintenance, while taking into account the installation and protection of pipelines and cables, and is reasonably matched with the launch position.

[0019] Fourth, the launch pad of this invention adopts a modular design, which facilitates maintenance and replacement of the aircraft after launch.

[0020] Upon reading the detailed embodiments and examining the accompanying drawings, those skilled in the art will recognize additional features and advantages. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the 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.

[0022] Figure 1 This is a schematic diagram of the overall structure of the aircraft launch pad according to an embodiment of the present invention.

[0023] Figure 2 This is a three-dimensional structural diagram of the triangular cover plate according to an embodiment of the present invention.

[0024] Figure 3 This is a schematic diagram of the connection between the guide channel cover plate and the lower platform body in an embodiment of the present invention.

[0025] Figure 4 This is a schematic diagram of the flow channel cover plate being opened to the correct position according to an embodiment of the present invention.

[0026] Figure 5 This is a top view of the launch pad of the aircraft according to an embodiment of the present invention.

[0027] Figure 6 This is a top view of the lower platform of the aircraft launch pad according to an embodiment of the present invention.

[0028] Figure 7 This is a top view of the overall structure of the aircraft launch pad according to an embodiment of the invention.

[0029] Figure 8 This is a schematic diagram of how the triangular cover plates of an embodiment of the present invention are locked by mechanical locks.

[0030] Explanation of reference numerals in the attached figures: 1. Platform body; 11. Upper platform body; 12. Lower platform body; 2. Traction release device; 3. Auxiliary support device; 31. Protective cover; 4. Guide channel cover plate; 41. Triangular cover plate; 411. Rotary hinge lug; 412. Equalizing hole; 413. Mechanical locking pin hole; 414. Mechanical locking pin; 5. Positioning support device; 51. Launch pad receiving surface; 52. Guide positioning pin; 6. Clamping device; 71. Electric push rod; 72. Fireproof raised edge; 73. Fireproof recessed edge; 74. Electric push rod installation. 80. Hole; 81. Basic adapter; 82. Mobile ladder; 83. Fixed ladder; 84. Guardrail; 85. Conversion interface; 86. Upper platform; 87. Mechanical limit switch; 88. Surface protection plate; 89. Locking hook; 90. Camera; 91. Methane pipeline; 92. Filling pipeline protection plate; 93. Gas supply pipeline; 94. Gas pipeline protection cover; 95. Oxygen filling pipeline; 96. Filling hose; 97. Cable tray; 98. Hydraulic pipeline; 99. Hydraulic pump station; 100. Personnel passage. Detailed Implementation

[0031] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and to exemplify the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of the present invention.

[0032] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0033] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0034] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., and should not be considered limiting. Similar terms are used throughout the description to refer to similar elements.

[0035] It will be apparent to those skilled in the art that the present invention can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.

[0036] See Figure 1 The present invention provides a square-shaped launch pad for an aircraft, comprising at least: a launch pad body 1, and a restraint and release device 2, an auxiliary support device 3, a guide channel cover plate 4, a positioning support device 5, and a clamping device 6, all mounted on the launch pad body 1. A polygonal opening is located at the center of the launch pad body 1, meaning the opening is polygonal when viewed from above. The area above the opening is used to support the aircraft, and the area below the opening is used to connect to the guide channel. The guide channel cover plate 4 is used to cover the opening. During launch or test firing of the aircraft, the guide channel cover plate 4 must be opened in advance to ensure that the flame ejected from the aircraft's tail enters the guide channel through the opening. The restraint and release device 2 and the auxiliary support device 3 are alternately arranged around the opening to support and secure the aircraft. The positioning support device 5 and the clamping device 6 are located on one side of the launch pad body. The positioning support device 5 is used to position and support the launch pad during docking with the transport and erection vehicle, while the clamping device 6 is used to lock the aircraft after docking with the transport and erection vehicle and to assist in the aircraft's erection.

[0037] Rockets are among the most common spacecraft in the aerospace field, widely used in satellite launches, deep space exploration, and manned spaceflight missions due to their powerful thrust systems and efficient propulsion methods. The launch pad of this invention is specifically described using rocket launches as an example: (See also...) Figure 1 , Figure 2 , Figure 3 , Figure 4 and Figure 5 : To cope with frequent rocket test and launch missions, and to save manpower costs, the guide channel cover 4 in this embodiment can be designed as a modular assembly structure, and each section can be automatically driven by a drive mechanism to significantly reduce manual operation costs and improve operational safety and reliability. Specifically, the shape of the guide channel cover 4 matching the platform opening is set as polygonal to facilitate installation on the inner wall of the platform opening. For example, the guide channel cover 4 includes multiple triangular cover plates 41 evenly divided by their angle bisectors. Each triangular cover plate 41 is rotatably connected to the inner wall of the platform opening through its base, and the drive mechanism controls the opening or closing of each triangular cover plate 41. It should be noted that each triangular cover plate 41 is an isosceles triangle structure. When the guide channel cover 4 is blocking the platform opening, the apex angles of each triangular cover plate 41 are in close contact with each other. The side of the triangular cover plate 41 opposite to the apex angle is the base, and its base is connected to the inner wall of the platform opening through a rotary hinge 411. Under the action of the drive mechanism, each triangular cover plate can rotate around its hinge point, and its maximum opening angle is 95 degrees.

[0038] The base of the triangular cover plate in this application can also be a location near the base, that is, a solid structure close to the base of the cover plate, and not merely a base in a geometric sense. Describing it as a base in this application is merely for indirect description and should not be interpreted restrictively. It is also inappropriate to intentionally interpret the base as a geometric base and then offset it upwards in the project, moving it a certain distance away from the base and connecting it to the platform, and interpret this as outside the scope of protection of this application.

[0039] In the above embodiments, the drive mechanism is located inside the launch pad and is specifically one of an electric push rod (electric cylinder), a hydraulic cylinder, and a pneumatic cylinder. In this embodiment, the rocket launch pad selects an electric push rod 71 as the drive mechanism for the triangular cover plate 41. The side of each triangular cover plate 41 facing inwards from the launch pad is connected to the near-ground end of the launch pad 1 via the electric push rod 71. The electric push rod 71 is equipped with an upper limit proximity switch and a lower limit proximity switch. The upper limit proximity switch is used to identify when the triangular cover plate 41 is closed, and the lower limit proximity switch is used to identify when the triangular cover plate 41 is open. When both proximity switches detect the electric push rod moving to its designated position, the electric push rod will automatically stop moving.

[0040] Specifically, before rocket testing or launch, the electric push rod 71 is retracted, pulling each triangular cover plate 41 to rotate closer to the ground. The lower limit proximity switch detects that the platform opening is in place (e.g., ...). Figure 4(As shown in the diagram), the electric push rod is controlled to stop retracting. Traditional guide channel covers often need to be manually moved before rocket erection. In this embodiment, the guide channel cover can automatically open after rocket erection and before ignition. During the rocket static ignition test or after rocket takeoff, the electric push rod 71 is extended, pushing each triangular cover 41 to rotate away from the ground until the platform opening is completely blocked. Once the upper limit switch detects that the platform opening is closed, the electric push rod 71 stops extending.

[0041] See also Figure 1 , Figure 5 and Figure 6 Furthermore, the platform 1 includes an upper platform 11 and a lower platform 12 fixedly connected, which can be fixed together by bolts. The lower platform 12 has at least a personnel passage, equipment passage, wiring passage, and pipe passage inside, while the upper platform 11 has at least a personnel operation through-hole, pipe passage, and wiring passage inside. The platform 1 has a movable ladder 81 and a fixed ladder 82 on its outer perimeter. The movable ladder 81 facilitates personnel movement and work between the upper and lower platforms, while the fixed ladder 82 is used for emergency work and evacuation in case the movable ladder 81 is removed. Additionally, to ensure the safety of workers, a removable guardrail 83 made of aluminum alloy can be installed around the top plane of the upper platform, facilitating disassembly and installation and protecting personnel safety.

[0042] In any of the above embodiments, the opening of the upper platform 11 is an octagonal cylindrical structure, and the opening of the lower platform 12 is an octagonal trumpet-shaped structure with the wider opening facing downwards. The opening of the lower platform 12 gradually expands outwards from top to bottom, forming a cone angle of 5° to 8°. This special octagonal trumpet shape effectively accommodates the high-temperature, high-speed flame emissions generated after rocket engine ignition, ensuring the stability of the flame jet channel while also providing directional guidance and pressure buffering for the gas flow through the gradually expanding structure.

[0043] The guide channel cover is precisely matched with the opening of the upper platform 11. Specifically, it is divided into eight triangular cover plates 41 by its angle bisector. Each triangular cover plate 41 is driven by an electric push rod 71 to rotate around its base, thus opening and closing the platform. In other words, the guide channel cover and the opening of the upper platform 11 are precisely matched, with the specific structure designed to divide the platform into eight identical isosceles triangular cover plates 41 by the angle bisector. Before launch, the electric push rods are synchronously controlled to retract, pulling each triangular cover plate 41 to rotate flexibly around its base (the side hinged to the platform). When all triangular cover plates 41 simultaneously unfold inward and press against the inner wall of the lower platform 12's platform opening, the platform is fully open (e.g., when all triangular cover plates 41 simultaneously unfold inward and press against the inner wall of the platform opening of the lower platform 12). Figure 4(as shown in the diagram) to facilitate the normal use and maintenance of the guide channel. When the electric push rod 71 is driven in the reverse direction to cause each triangular cover plate 41 to close tightly to each other, a complete platform closure surface is formed (as shown in the diagram). Figure 5 As shown in the figure, the entire opening and closing process is stable, reliable, and highly precise.

[0044] See Figure 2 Furthermore, in this embodiment, each triangular cover plate 41 has multiple pressure equalization holes 412 evenly distributed on its surface. This effectively reduces the scouring force of the gas flow on the platform, preventing scouring and ablation damage to the guide channel cover plate. The pressure equalization holes 412 are through holes. These precisely designed vents effectively balance the pressure difference on both sides of the guide channel cover plate at the moment of launch, effectively reducing the scouring force of the gas flow on the platform. By setting a reasonably distributed pressure equalization hole structure on the guide channel cover plate, not only is it ensured that the pressure on both sides remains dynamically balanced during the emission of high-temperature and high-pressure gas, but it also effectively reduces the mechanical stress generated by the internal and external pressure difference of the cover plate, thereby improving the safety and stability of the launch platform.

[0045] In addition, the eight inner sides of the 12 prongs of the lower platform are all welded with heat-protective reinforcing ribs and coated with heat-protective coating. This design can significantly reduce the impact of high-temperature environment on platform structure. The dual protection design ensures the stability and safety of the prong area under extreme working conditions.

[0046] See Figure 1 , Figure 2 and Figure 3 In one embodiment, each of the eight inner sides of the lower platform 12's opening is provided with an electric push rod mounting hole 74. One end of the electric push rod 71 passes through the electric push rod mounting hole 74 and is connected to the lower platform 12 via a lower hinge point, while the other end is connected to the side of the triangular cover plate 41 facing the opening via an upper hinge point. A fire-blocking protrusion 72 is provided around the electric push rod mounting hole 74, and a fire-blocking recess 73 matching the fire-blocking protrusion 72 is provided at the position where the electric push rod is mounted on each triangular cover plate 41. When the triangular cover plate 41 is opened to its full position by synchronously driving each electric push rod 71, the fire-blocking protrusion 72 and the fire-blocking recess 73 engage and lock together to prevent flames from entering the launch pad through the electric push rod mounting hole 74 in the middle of the fire-blocking protrusion 72, thus avoiding damage to internal instruments and equipment.

[0047] In the above embodiment, each of the eight inner sides of the lower platform is provided with precisely positioned electric push rod mounting holes 74. These mounting holes are evenly arranged according to a preset mechanical distribution law to ensure balanced force distribution.

[0048] See Figure 2 , Figure 5 and Figure 8 Furthermore, in the closed state of the guide channel cover (e.g.) Figure 5(As shown in the diagram), the front end of each triangular cover plate 41 is locked by a mechanical lock pin, thereby connecting the eight triangular cover plates 41 into one unit and preventing danger due to the failure of a single electric push rod. Specifically, each triangular cover plate 41 has a mechanical lock pin hole 413 at the apex corresponding to its base edge. When the eight triangular cover plates 41 completely cover the platform opening, the mechanical lock pin 414 passes through the mechanical lock pin hole 413 at each apex and locks the plate. It should be noted that, see [reference needed] Figure 8 In this embodiment, the mechanical locking pin 414 comprises eight pins connected as a single unit. After each pin of the mechanical locking pin 414 passes through its corresponding pin hole, the eight triangular cover plates 41 form a robust overall structure through this mechanical connection. Even if one of the electric push rods fails due to a malfunction, the other cover plates can still maintain a stable connection due to the locking effect of the mechanical lock, effectively preventing dangerous situations such as accidental opening or displacement of the cover plates caused by the failure of a single electric push rod, thereby significantly improving safety.

[0049] See Figure 1 and Figure 5 In any of the above embodiments, to enable the rocket launch pad of this embodiment to support both rocket launches and rocket testing and static ignition tests, the restraint release device 2 and the auxiliary support device 3 can be detachably mounted on the launch pad 1. Specifically, one end of the restraint release device 2 and the auxiliary support device 3 can be detachably mounted on the top of the lower launch pad 12 via a conversion interface 84, and the other end can extend beyond the top of the upper launch pad 11. Since both the upper launch pad 11 and the lower launch pad 12 are identical square structures, the restraint release device 2 can be positioned on the axis of symmetry of the top plane of the lower launch pad 12, while the auxiliary support device 3 can be positioned on the angle bisector of the top plane of the lower launch pad 12. This achieves a uniform and alternating distribution of the restraint release device 2 and the auxiliary support device 3, further enhancing the stability and anti-displacement capability of the launch pad. The two devices can work together to optimize the overall performance of the device.

[0050] When a static ignition test is required using the rocket launch pad of this embodiment, the restraint release device 2 and auxiliary support device 3 can be removed first, replaced with the test stand fixture, and connected via the conversion interface 84. This setup not only improves the stability of the restraint release device and auxiliary support device but also increases the applicability and functionality of the rocket launch pad of this embodiment.

[0051] Furthermore, in any of the above embodiments, the top of the auxiliary support device 3 is provided with an opening for the connector to extend and a protective cover 31. After the rocket takes off, the connector detaches from the rocket and retracts into the auxiliary support device, while the protective cover 31 closes to block the opening of the auxiliary support device, protecting the connector and internal pipelines located within the auxiliary support device. In this embodiment, the auxiliary support device is specially designed with an opening for the connector to extend at its top and is equipped with an openable and closable protective cover 31. During rocket launch, the connector remains extended and docked with external equipment. When the rocket successfully takes off and reaches a certain altitude, the connector automatically detaches from the rocket and separates from it, then smoothly retracts into the internal space of the auxiliary support device through a built-in recovery mechanism. At the same time, the protective cover 31 closes quickly under its own gravity, tightly blocking the opening of the auxiliary support device, forming an effective physical barrier to protect the retracted connector, electrical connector, and internal pipelines from the influence of the external environment (such as high-speed airflow, dust, temperature changes, etc.), so as to allow for multiple uses and reduce rocket launch costs.

[0052] See Figure 1 and Figure 7 In one embodiment, a flat upper platform plate 85 is installed on the top of the upper platform 11. The upper platform plate 85 and the upper platform 11 are connected by a stable structure to ensure the stability and load-bearing capacity of the overall structure, while providing a flat and reliable working platform for subsequent equipment installation or operation. Considering that the gas flow that the upper platform plate 85 needs to withstand is related to its distance from the platform opening, the upper platform plate 85 can be set as a modular unit. For example, the upper platform plate 85 includes multiple plates of different sizes laid on the top plane of the upper platform. Since the surface pressure of the gas flow is greater near the platform opening, smaller plates are laid near the platform opening, while larger plates are laid further away from the platform opening due to the lower surface pressure. The plates of different sizes are laid together on the entire plane area of ​​the top of the upper platform except for the platform opening, and are bound together with wire.

[0053] To enhance the load-bearing and compressive strength of the upper platform, reinforcing ribs can be installed on each upper platform. In this embodiment, the reinforcing ribs are integrally molded from high-strength materials, which not only significantly improves the overall compressive strength of the upper platform and effectively disperses and bears external load pressure, but also enhances the bonding strength with the thermal protection material through its special surface structure design, greatly improving the adhesion of the thermal protection material and ensuring that the thermal protection layer is not easily detached in high-temperature environments, thereby providing more reliable thermal protection for the equipment.

[0054] In one embodiment, a recessed platform is provided on one side of the upper platform 11, where the clamping device and positioning support device are located. It should be noted that the recessed platform is designed with vertical sidewalls on only three sides, with the open side intentionally designed to be without sidewalls. The main function of this special structure is that the side without sidewalls is used for precise docking with the transport and erection vehicle, ensuring smooth connection and ease of operation. Meanwhile, the other three locations with sidewalls are specifically planned as installation areas for the clamping device. These sidewalls provide a stable support foundation and accurate positioning reference for the clamping device, enabling it to effectively perform its fixing and clamping functions.

[0055] Furthermore, the positioning support device 5 includes a launch pad receiving surface 51 disposed on the plane of the recessed platform, and a guide positioning pin 52 disposed on the launch pad receiving surface 51. The guide positioning pin 52 provides high-precision positioning for the erection vehicle, and the launch pad receiving surface 51 provides the main support for the rocket erection process. In addition, the side wall of the upper platform 11, which is opposite to the open side of the recessed platform, has an inclined transition with the top of the upper platform. Two mechanical limiters 86 are provided on the inclined surface to protect the position during the rocket erection process and prevent damage to the rocket body due to excessive erection angle.

[0056] In the above embodiment, the launch pad receiving surface has three parallel locations, with guide positioning pins 52 positioned in the middle of the two side launch pad receiving surfaces 51. Each side of the launch pad receiving surface 51 and guide positioning pins 52 has an openable and closable receiving surface protective plate 87 at its top. The receiving surface protective plate 87 is installed on the upper platform 11 to protect the launch pad receiving surface 51 and guide positioning pins 52 when not in use, preventing dust from entering and causing contamination and damage. Additionally, the lower platform 12 has a locking hook 88 on its side wall for docking with the transport and erection vehicle, used for locking the position during docking of the transport and erection vehicle with the launch pad. All locking devices in this embodiment are hydraulically driven, stable and reliable, and work with lead screws to achieve self-locking.

[0057] See Figure 5In one embodiment, a refueling pipeline is provided on one side of the upper platform 11, and a protective device is provided on the outside of the refueling pipeline. Specifically, a methane pipeline 91 and a gas supply pipeline 93 are provided on the side of the upper platform (excluding the side used for docking with the transport and erection vehicle). A refueling pipeline protective plate 92 is provided on the outside of the methane pipeline 91, and a gas path protective cover 94 is provided on the part of the gas supply pipeline 93 located on the outside of the upper platform, which can effectively protect the methane pipeline 91 and the gas supply pipeline 93 from direct ablation by the high-temperature flames during rocket launch. In addition, the gas supply pipeline 93, oxygen refueling pipeline 95, and refueling hose 96 are arranged in the internal space of the upper platform, and a rational layout is achieved through a scientific layered design. All critical pipeline systems are fully protected under the upper platform plate. This arrangement can effectively resist the strong heat radiation and flame ablation generated during rocket launch, and can also provide sufficient maintenance environment for personnel through the easily openable cover structure when maintenance is required, ensuring the smooth conduct of daily inspections and emergency maintenance work.

[0058] See also Figure 1 and Figure 7 In one embodiment, cameras 89 are arranged diagonally on the upper platform 11 to facilitate real-time monitoring of the connectors and protective covers of the auxiliary support device 3. The lower platform 12 has a cable outlet on its side for docking with the transport and erection vehicle, allowing cables to be removed for easy connection to the vehicle. In addition, besides the side for docking with the transport and erection vehicle, the other three sides of the lower platform 1 are equipped with fireproof doors for easy personnel access and exhaust vents. These vents are kept open during testing and launch to increase airflow and prevent the accumulation of toxic and harmful gases within the platform.

[0059] See Figure 6 In any of the above embodiments, the outer ring inside the lower platform 12 serves as a personnel passage 100, with a passage platform laid underneath for easy personnel access and maintenance. The inner ring inside the lower platform 12 is mainly used to arrange cable trays 97 and hydraulic pipelines 98, arranged in layers. The cable trays 97 are located at the top, with strong and weak current cables arranged separately within the trays. The hydraulic pipelines 98 are located at the bottom for easy connection to the hydraulic pump station 99. The cable inlet is close to the outlet of the underground pipeline, and all cables are under the gas circuit protection cover 94 to prevent flame erosion. The lower platform 1 is connected to the foundation via a foundation adapter 80. The foundation adapter 80 can be leveled with high precision and welded to the pre-embedded steel plate of the foundation. The lower platform 1 and the foundation adapter 80 are quickly connected by bolts, making assembly convenient.

[0060] This invention employs an independent upper and lower platform structure, with strictly separate and independent internal personnel passages and cable conduits. This physical isolation design effectively reduces mutual interference between systems and forms a comprehensive protective barrier for critical components such as conduits, connectors, and disconnect / reconnection mechanisms, significantly improving the reliability and safety of the launch pad in complex environments. The launch pad's guide vane cover, rocket receiving device, and clamping device utilize automated control technology, reducing labor costs. The launch pad surface cover adopts a standardized modular unit design, with modules fixed by quick-connect mechanisms. This facilitates targeted disassembly and replacement after launch based on wear or mission requirements, significantly shortening maintenance cycles and reducing operational complexity. The aforementioned systematic design scheme, encompassing independent layout, automated control, lightweight assembly and disassembly, and modular maintenance, falls within the core protection scope of this invention. In addition, other technical solutions that adopt an 8-point support arrangement and are substantially similar to this invention in terms of overall design concept (such as functional zoning isolation, protection of key components, process automation, lightweight disassembly and assembly of structure, etc.) and layout (such as upper and lower platform separation architecture, automatic control logic of guide channel cover plate, modular combination of platform cover plate, etc.) should all be included in the protection scope of this invention.

[0061] The above embodiments can be combined with each other and have corresponding technical effects.

[0062] This invention also provides an integrated transport, erection, and launch system, comprising at least the rocket launch pad and rocket transport and erection vehicle as described in any of the above embodiments. After transporting the rocket to its designated position, the transport and erection vehicle is positioned and docked with the rocket launch pad via a positioning support device. A clamping device then clamps the positioned transport and erection vehicle to facilitate rocket erection. The rocket launch pad's restraint and release device integrates a rocket receiving mechanism, which actively receives the rocket after erection, lowers it onto the launch pad for support, and clamps the rocket's arrow feet. An auxiliary support device on the rocket launch pad supports the remaining four arrow feet after the rocket has landed on the launch pad.

[0063] The aircraft launch pad and integrated transport, erection, and launch system of this invention can flexibly complete the transition between launch pad testing and launch states. In addition, the guide vane cover, docking, and clamping mechanisms can all be automatically controlled, reducing manual operation and shortening the pre-launch preparation time.

[0064] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A launch pad for an aircraft, characterized in that, At least including: Platform body, restraint and release device, auxiliary support device, guide channel cover plate, positioning support device and clamping device; The platform has a polygonal opening at its center, with the upper part of the opening used to support the aircraft and the lower part used to connect to the flow guide channel. The restraint release device and the auxiliary support device are alternately arranged around the opening to support and fix the aircraft. The positioning support device and the clamping device are arranged on one side of the platform. The positioning support device is used to position and support the aircraft launch pad when it is docked with the transport and erection vehicle, and the clamping device is used to lock the aircraft after the aircraft launch pad is docked with the transport and erection vehicle and to assist in the aircraft's erection. The guide channel cover is configured as a polygon matching the platform opening to cover the platform opening; the guide channel cover includes a plurality of triangular cover plates evenly divided by its angle bisector, the base of each triangular cover plate is rotatably disposed on the inner wall of the platform opening, and the side of each triangular cover plate facing the inside of the platform opening is connected to the near-ground end of the platform body through an electric push rod. By controlling the retraction of the electric push rod, each of the triangular cover plates is pulled to rotate towards the ground to open the platform opening; By controlling the extension of the electric push rod, each of the triangular cover plates is pushed to rotate into position away from the ground, thereby blocking the platform opening; The platform includes a lower platform and an upper platform that are fixedly connected. The inner side of the lower platform opening is provided with an electric push rod mounting hole. One end of the electric push rod passes through the mounting hole and is connected to the lower platform through the lower hinge point, and the other end is connected to the side of the triangular cover plate facing the inside of the platform opening through the upper hinge point. The electric push rod mounting hole is surrounded by a fire-blocking protrusion, and the triangular cover plate is provided with a fire-blocking recess at the position where the electric push rod is installed, which matches the fire-blocking protrusion. By driving the electric push rod, the triangular cover plate is opened into place, so that the fire-blocking protrusion and the fire-blocking concave edge are fastened together to prevent flames from entering the electric push rod mounting hole.

2. The aircraft launch pad according to claim 1, characterized in that, The lower platform is provided with at least a personnel passage, an equipment passage, a wiring passage, and a pipeline passage; the upper platform is provided with at least a personnel operation through hole, a pipeline passage, and a wiring passage. The restraint and release device and the auxiliary support device are detachably mounted on the top of the lower platform through a conversion interface at one end, and the other end extends beyond the top of the upper platform.

3. The aircraft launch pad according to claim 2, characterized in that, The top of the upper platform is provided with an upper platform plate; The upper platform includes multiple platforms of different sizes laid on the top plane of the upper platform, wherein the platform closer to the platform opening is smaller than the platform further away from the platform opening.

4. The aircraft launch pad according to claim 2, characterized in that, The upper platform and the lower platform are square structures of the same shape; The restraint and release device is located on the axis of symmetry of the top plane of the lower platform, and the auxiliary support device is located on the angle bisector of the top plane of the lower platform.

5. The aircraft launch pad according to any one of claims 2 to 4, characterized in that, The upper platform has an octagonal cylindrical structure at its opening, and the lower platform has an octagonal trumpet-shaped structure with its wide opening facing downwards. The guide channel cover is matched with the platform opening of the upper platform, specifically by dividing it into eight triangular cover plates by its angle bisector; the electric push rod drives each of the triangular cover plates to rotate around its base, thereby realizing the opening and closing of the platform opening.

6. The aircraft launch pad according to claim 1, characterized in that, A recessed platform is provided on one side of the upper platform, and the pressing device is disposed on the side wall of the recessed platform; The positioning support device includes a launch pad receiving surface disposed on the plane of the recessed platform, and a guide positioning pin disposed on the launch pad receiving surface; the guide positioning pin provides high-precision positioning for the erection vehicle, and the launch pad receiving surface provides support for the aircraft erection process.

7. The aircraft launch pad according to claim 1, characterized in that, The top of the auxiliary support device is provided with an opening for the connector to extend out and a protective cover; after the aircraft takes off, the connector detaches from the aircraft and retracts into the auxiliary support device, and at the same time the protective cover closes to cover the opening and protect the connector and internal pipelines installed in the auxiliary support device.

8. The aircraft launch pad according to claim 1, characterized in that, A filling pipeline is provided on one side of the upper platform, and a protective device is provided on the outside of the filling pipeline.

9. An integrated transport, erection, and launch system, characterized in that, It includes at least an aircraft transport and erection vehicle and an aircraft launch pad as described in any one of claims 1 to 8; after the transport and erection vehicle is transported to its position, it is positioned and docked with the aircraft launch pad through the positioning support device, and the clamping device clamps the positioned transport and erection vehicle to cooperate with the aircraft for erection.

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