Multiplexed liquid rocket integrated horizontal transfer erect-launch system

Abstract

The application discloses a multiplex liquid rocket integrated horizontal transfer and erecting launching system, which comprises a mobile vehicle, a detachable support frame, a locking device and a launching platform, wherein the mobile vehicle is located at the lower part of the support frame and is used for driving the support frame to move horizontally; the upper part of the support frame is provided with a horizontally placed multiplex liquid rocket, and the support frame is further used for adjusting the erecting of the horizontally placed multiplex liquid rocket; the locking device is located on the support frame and is used for axially and radially fixing the multiplex liquid rocket to prevent displacement movement of the multiplex liquid rocket on the support frame; and the launching platform is fixed at one end of the support frame and is used for supporting the whole rocket body after the multiplex liquid rocket is erected. The system is suitable for rockets of various sizes, has high compatibility, can accurately dock the launching platform, improves work efficiency, reduces cost, and improves the reliability of the erecting system.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to an integrated horizontal transport, erection, and launch system for reusable liquid rockets. Background Technology

[0002] With the rapid development of the aerospace industry, various technologies involved in the rocket field have also made great strides.

[0003] The global aerospace industry is transforming towards higher frequency, lower cost, and faster response, with the launch demand for large and medium-sized liquid-fueled launch vehicles growing rapidly. Rocket launch and testing modes are undergoing a profound transformation from traditional to commercial models.

[0004] The traditional vertical assembly-vertical testing-vertical transfer-vertical launch mode relies on ultra-high clearance assembly plants, dedicated transfer roads, and complex ground facilities. It has a long launch preparation cycle and high infrastructure and maintenance costs, making it difficult to meet the needs of high-density missions such as commercial satellite constellation networking and emergency launches.

[0005] Currently, some aerospace companies adopt the "three horizontal and one vertical" launch mode, which is a launch mode of horizontal assembly, horizontal transportation, horizontal testing, and vertical launch. This mode reliably supports and carries the rocket body during the rocket loading, transportation, and erection process, so that the rocket body is not subjected to additional forces other than its own gravity. It also avoids multiple loading and transportation, and reduces the risk of collisions to the rocket. This is particularly important and crucial. With its advantages such as decoupling the final assembly and testing process from the launch site, flexible transfer, and low infrastructure costs, it has become the core technology development direction for high-density launches in commercial aerospace.

[0006] However, in the "three horizontal and one vertical" launch and test mode, existing transport and erection systems are mostly customized designs for a single launch position, with inconsistent interface sizes and load-bearing specifications. Performing missions across launch sites requires the customization of adaptable tooling and structural components, doubling research and manufacturing costs and lengthening deployment cycles, making them unsuitable for the flexible scheduling needs of commercial aerospace across multiple launch sites. Furthermore, after erection, the launch pad needs precise docking with the ground launch platform. The entire docking process involves a large workload and a long cycle; a single interface failure can delay the entire launch cycle. During horizontal transport, displacement of the rocket body frequently occurs, severely impacting the reliability of the erection system.

[0007] There is an urgent need to provide an integrated horizontal transport, erection, and launch system for reusable liquid rockets that is suitable for rockets of various sizes, has high compatibility, can accurately dock with the launch pad, improves work efficiency, reduces costs, and also reduces the risk of rocket displacement during horizontal transport, thereby improving the reliability of the erection system. This is the problem that needs to be solved. Summary of the Invention

[0008] The purpose of this invention is to provide an integrated horizontal transport, erection, and launch system for reusable liquid rockets, which is applicable to rockets of various sizes, has high compatibility, can accurately dock with the launch pad, improves work efficiency, and is universally compatible with multiple launch sites. This reduces costs and also reduces the risk of rocket displacement during horizontal transport, thereby improving the reliability of the erection system.

[0009] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0010] One aspect of the present invention provides an integrated horizontal transport, erection, and launch system for reusable liquid rockets, comprising a mobile vehicle, a detachable support frame, a locking device, and a launch pad, wherein...

[0011] The mobile vehicle is located at the lower part of the support frame and is used to drive the support frame to move horizontally;

[0012] The upper part of the support frame is provided with a horizontally placed reusable liquid rocket, and the support frame is also used to adjust the horizontally placed reusable liquid rocket to stand upright.

[0013] The locking device is located on the support frame and is used to fix the reusable liquid rocket axially and radially to prevent the reusable liquid rocket from shifting on the support frame.

[0014] The launch pad is fixed to one end of the support frame and is used to support the entire rocket body after the reusable liquid rocket is erected.

[0015] Furthermore, the support frame is a frame structure and includes at least a detachable first frame body, a second frame body, and a third frame body, wherein the second frame body is located between the first frame body and the third frame body, and its two ends are fixedly connected to the first frame body and the third frame body, respectively.

[0016] The upper part of the frame structure is provided with an auxiliary support bracket for supporting the body of the reusable liquid rocket. The auxiliary support bracket is respectively set on the first frame body and the second frame body. The interior of the frame structure is provided with a pipeline system for supplying liquid and gas to the reusable liquid rocket and a hydraulic cylinder structure. One end of the hydraulic cylinder structure is fixedly connected to the internal crossbeam of the support frame through a rotating shaft, and the other end is used to fix it to the ground.

[0017] Furthermore, the auxiliary support bracket includes a crossbeam base, a lifting assembly, an anti-tilt limiting cylinder assembly, a lifting support seat, and an arrow body support bracket, wherein...

[0018] Both the lifting platform assembly and the anti-tilt limiting cylinder assembly are located between the crossbeam base and the lifting support seat, with the anti-tilt limiting cylinder assemblies symmetrically arranged on both sides of the lifting platform assembly.

[0019] The lower end of the crossbeam base is connected to the support frame, and the upper end of the crossbeam base is connected to the lower ends of the lifting assembly and the anti-tilt limiting cylinder assembly respectively. The upper ends of the lifting assembly and the anti-tilt limiting cylinder assembly are connected to the lower ends of the lifting support seat respectively. The upper end face of the lifting support seat is fixedly connected to the lower end face of the arrow body support bracket, and the upper end face of the arrow body support bracket is used to fit against the surface of the arrow body.

[0020] Furthermore, the locking device includes a first locking mechanism and a second locking mechanism, wherein the first locking mechanism is used to radially fix the rocket body end near the fairing end, and the second locking mechanism is used to fix the rocket body near the rocket engine end to limit the axial movement of the reusable liquid rocket.

[0021] Furthermore, the first locking mechanism includes at least two sets of symmetrically arranged clamping devices, a first adjusting device, and a first fixing device, with each end of the first adjusting device connected to the corresponding clamping device and the first fixing device respectively.

[0022] The clamping device is used to fit against the corresponding arrow body surface;

[0023] The first adjusting device is used to adjust the distance between the clamping device and the surface of the arrow body;

[0024] The first fixing device is used to fix the first adjusting device so that the first locking mechanism is fixed on the support frame.

[0025] Furthermore, the clamping device is roughly triangular in shape, and the end face of the clamping device near the surface of the arrow body is a curved end face.

[0026] The first adjustment device includes an upper adjustment bracket, a lower adjustment bracket, and a first electric lever. The upper end of the upper adjustment bracket, near the arrow body, is connected to the clamping device via a first rotating shaft. The lower end of the upper adjustment bracket, near the arrow body, is connected to the lower adjustment bracket, near the arrow body, via a second rotating shaft. The upper end of the first electric lever is connected to the upper end of the upper adjustment bracket, away from the arrow body, via a third rotating shaft. The lower end of the first electric lever is connected to the lower adjustment bracket, away from the arrow body, via a fourth rotating shaft.

[0027] The first fixing device includes an upper support, a lower support, and a second electric lever. The upper end of the upper support is connected to the lower end of the lowering bracket and the end near the arrow body via a fifth rotating shaft. The lower end of the upper support is fixed to the upper longitudinal beam on the side of the support frame near the arrow body. The upper end of the lower support is connected to the lower end of the second electric lever via a sixth rotating shaft. The lower end of the lower support is fixed to the lower longitudinal beam on the side of the support frame near the arrow body. The upper end of the second electric lever is connected to the lower end of the lowering bracket and the end away from the arrow body via a seventh rotating shaft.

[0028] Both the upper support and the lower support are triangular prism structures with a hollow center.

[0029] Furthermore, the second locking mechanism includes at least two sets of symmetrically arranged docking devices, a second adjusting device, and a second fixing device.

[0030] One side of the docking device is used to be fixedly connected to the docking panel on the outside of the arrow body, and the other side is connected to the upper end of the second adjustment device. The lower end of the second adjustment device is fixedly connected to the upper end of the support frame. The upper end of the second fixing device is fixed to the side of the second adjustment device away from the arrow body, and the lower end of the second fixing device is fixed to the inner frame sidewall of the support frame.

[0031] Furthermore, the second adjustment device includes a fixed base, a triangular arm, a lifting mechanism, and a telescopic mechanism, wherein...

[0032] The lower end of the fixed base is fixed to the support frame. The upper end of the fixed base is connected to the lower end of the triangular arm through the eighth rotating shaft. The upper end of the triangular arm, on the side closer to the arrow body, is connected to the lower end of the lifting mechanism through the ninth rotating shaft. The upper end of the lifting mechanism is connected to the docking device. The upper end of the triangular arm, on the side farther from the arrow body, is connected to the fixed end of the telescopic mechanism through the tenth rotating shaft. The telescopic end of the telescopic mechanism is connected to the outer wall of the lifting mechanism through the eleventh rotating shaft.

[0033] The space enclosed by the triangular arm, the lifting mechanism, and the telescopic mechanism forms a triangular structure.

[0034] Furthermore, the lifting mechanism is an electric cylinder structure, and the output end of the electric cylinder structure is also provided with a plate and a locking block. The upper part of the plate is provided with a slot with two ends communicating. One side surface of the locking block is in close contact with the slot sidewall on the plate, and the locking block is fixed to the plate by locking bolts.

[0035] A scale mark is provided on the surface of the lifting mechanism along its axial direction and located at the output end;

[0036] The lifting mechanism is also equipped with an anti-tilt device on the side near the arrow body. One end of the anti-tilt device is connected to the outer wall of the lifting mechanism, and the other end is fixed to the crossbeam on the support frame.

[0037] Furthermore, the docking device includes a docking plate, a rotating shaft, and a fixed sleeve. One end of the rotating shaft passes through the fixed sleeve and is fixedly connected to the docking plate, and the docking plate can rotate with the rotating shaft.

[0038] The docking plate has a cube-shaped structure.

[0039] The fixing sleeve includes an integrally formed upper sleeve body and a lower sleeve body. The two ends of the lower sleeve body are fixed to the plate by bolts. The upper part of the lower sleeve body is connected to the bottom of the upper sleeve body. The middle part of the upper sleeve body is provided with a hollow space for accommodating the rotating shaft. The top of the upper sleeve body is provided with a lifting lug.

[0040] Furthermore, the second fixing device includes an electric cylinder assembly, a fixed base plate, a first rotating shaft, and a second rotating shaft. The telescopic end of the electric cylinder assembly is fixed to the side of the triangular arm away from the arrow body via the first rotating shaft. The fixed end of the electric cylinder assembly is connected to one side of the fixed base plate via the second rotating shaft. The other side of the fixed base plate is fixed to the inner frame sidewall of the support frame.

[0041] Furthermore, the launch platform includes a launch platform body, two sets of fixed arms, a twelfth rotating axis, and fixed connecting parts.

[0042] The twelfth rotating axis is disposed on both sides of the launch pad body and fixedly connected to the launch pad body. The fixed arms are symmetrically disposed on the support frame. The twelfth rotating axis on both sides is respectively connected to the fixed arms that are close to each other, and the launch pad body can rotate with the twelfth rotating axis.

[0043] The fixing connector is used to fix the launch pad body, wherein the top end of the fixing connector is connected to the surface of the launch pad body near the support frame, and the other end is fixed to the support frame.

[0044] Furthermore, it also includes a soft support device for supporting the fairing, wherein,

[0045] The soft support device includes a connecting bracket, third adjustment devices symmetrically arranged on both sides of the connecting bracket, and a flexible flat strap for connecting to the third adjustment devices on both sides.

[0046] The connecting bracket is located at one end of the support frame and is detachably and fixedly connected to the support frame;

[0047] The third adjustment device includes a base, an adjusting electric cylinder, a support rod, and a winding winch. The base is located outside the connecting bracket and is connected to the connecting bracket at one end, while the other end extends away from the connecting bracket. The bottom end of the adjusting electric cylinder is connected to the base via a thirteenth rotating shaft, and the top end of the adjusting electric cylinder is connected to the body of the support rod via a fourteenth rotating shaft. The bottom end of the support rod is connected to the connecting bracket via a fifteenth rotating shaft. The top end of the support rod is used to support the flexible flat strip. The winding winch is fixed on the base and is used to adjust the length of the flexible flat strip.

[0048] The present invention has at least the following beneficial effects:

[0049] This reusable liquid rocket integrated horizontal transport, erection, and launch system consists of a mobile vehicle, a detachable support frame, a locking device, and a launch pad.

[0050] The detachable support frame allows for the addition of more support frames based on the size of the rocket body, making it suitable for rockets of various sizes. This improves system compatibility and allows for the transfer of rockets of different sizes using a single set of tooling, significantly reducing manufacturing costs.

[0051] In addition, a portion of the locking device is used to adhere to and hold the outer circumferential surface of the reusable liquid rocket, thereby radially fixing the reusable liquid rocket. Another portion is fixedly connected to the docking plate on the outer circumferential side of the tail end, thus completing the axial fixing of the reusable liquid rocket. This ensures that the reusable liquid rocket is firmly fixed on the support frame, preventing the reusable liquid rocket from rotating or moving axially on the support frame. This reduces the risk of displacement of the rocket during horizontal transport, improves the reliability of the erection system, and ultimately facilitates safe rocket launch.

[0052] In addition, the launch pad is fixed to one end of the support frame, making the launch pad and the support frame an integrated design. The launch pad can be erected together with the support frame, which can ensure that the rocket and the launch pad are accurately docked in advance, reduce the need for on-site hoisting equipment, improve the efficiency of rocket erection, and make it easier for the launch pad to quickly support the reusable liquid rocket after it has been erected.

[0053] The entire reusable liquid rocket integrated horizontal transport, erection, and launch system is suitable for rockets of various sizes, has high compatibility, can accurately dock with the launch pad, improves work efficiency, and is universally compatible with multiple launch sites. This reduces costs and also reduces the risk of rocket displacement during horizontal transport, improving the reliability of the erection system.

[0054] It should be understood that the above general description and the following specific embodiments are merely exemplary and illustrative, and do not limit the scope of the invention. Attached Figure Description

[0055] Figure 1 This is a schematic diagram of the integrated horizontal transport, erection, and launch system for reusable liquid rockets according to the present invention.

[0056] Figure 2 This is a perspective view of the integrated horizontal transport, erection, and launch system for reusable liquid rockets according to the present invention.

[0057] Figure 3 This is a perspective view of the support frame and connecting bracket of the present invention;

[0058] Figure 4 This is a simplified structural diagram of the first locking mechanism of the present invention;

[0059] Figure 5 This is a perspective view of the first locking mechanism of the present invention;

[0060] Figure 6 This is a perspective view of the auxiliary support bracket of the present invention;

[0061] Figure 7 This is a perspective view of the launch pad of the present invention;

[0062] Figure 8 This is a perspective view of the second locking mechanism of the present invention;

[0063] Figure 9 This is a perspective view of the flat plate, locking block, docking plate, rotating shaft, and fixing sleeve of the present invention;

[0064] Figure 10 This is a simplified structural diagram of the fixing connector of the present invention;

[0065] Figure 11 This is a schematic diagram of the structure of the soft support device of the present invention being tightly attached to the fairing;

[0066] Figure 12 This is a schematic diagram of the soft support device of the present invention not being tightly attached to the fairing;

[0067] Figure 13 This is a schematic diagram of the soft support device of the present invention in application;

[0068] Figure 14 This is a simplified structural diagram of the connection between the first limiting device, the second limiting device, the elastic device, the clamping device, and the upper adjustment bracket of the present invention.

[0069] Figure 15 This is a perspective view of the first limiting device of the present invention;

[0070] Figure 16 This is a perspective view of the second limiting device of the present invention;

[0071] Figure 17 This is a perspective view of the elastic device of the present invention;

[0072] Figure 18 This is a perspective view of the strip wedge block of the present invention.

[0073] Figure label:

[0074] 1. Mobile vehicle 2. Support frame

[0075] 3 launch pads, 4 reusable liquid rockets

[0076] 5 First frame body 6 Second frame body

[0077] 7 Third frame 8 Auxiliary support bracket

[0078] 9. Crossbeam base; 10. Lifting assembly

[0079] 11 Anti-tilt limit cylinder assembly 12 Lifting support seat

[0080] 13 Arrow body support bracket 14 First locking mechanism

[0081] 15 Second locking mechanism 16 Clamping device

[0082] 17 First adjusting device 18 First fixing device

[0083] 19. Adjust the bracket upwards. 20. Adjust the bracket downwards.

[0084] 21 First electric lever 22 First rotating shaft

[0085] 23 Second rotation axis 24 Third rotation axis

[0086] 25 Fourth Rotational Shaft 26 Upper Support

[0087] 27 Lower support 28 Second electric lever

[0088] 29 Fifth Rotation Axis 30 Sixth Rotation Axis

[0089] 31 Upper longitudinal beam 32 Lower longitudinal beam

[0090] 33 Seventh Rotary Axis 34 Fixed Seat

[0091] 35 Triangular arm 36 Lifting mechanism

[0092] 37 Telescopic Mechanism 38 Eighth Rotating Axis

[0093] 39 Ninth Rotation Axis 40 Tenth Rotation Axis

[0094] 41 Eleventh Rotational Axis 42 Flat Plate

[0095] 43 Locking block 44 Anti-tilt device

[0096] 45 mating plate 46 rotating shaft

[0097] 47 Fixed sleeve 48 Electric cylinder assembly

[0098] 49 Fixed base plate 50 First rotating shaft

[0099] 51 Second rotating shaft 52 Launch pad main body

[0100] 53 Fixed arm 54 Twelfth rotating axis

[0101] 55 Fixed connector 56 First base body

[0102] 57 Second base body 58 First connector

[0103] 59 Second connector 60 Connecting rotating shaft

[0104] 61 Soft support device 62 Connecting bracket

[0105] 63 Flexible flat strip 64 Base

[0106] 65 Adjustable electric cylinder 66 Support rod

[0107] 67-roll belt winch, 68-platform

[0108] 69. Primary gas-liquid connector and rear tilting mechanism; 70. Traction release mechanism

[0109] 71 Primary electrical connector and rear tilting mechanism; 72 Reverse flow channel flip-plate mechanism

[0110] 73 First limiting device 74 Second limiting device

[0111] 75 Elastic device 76 First limiting block

[0112] 77 First adjusting bolt 78 Second limiting block

[0113] 79 Second Adjusting Bolt 80 Elastic Component

[0114] 81 First elastic seat 82 Second elastic seat

[0115] 83 strip wedge Detailed Implementation

[0116] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0117] It should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the present invention or simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention.

[0118] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0119] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments.

[0120] Furthermore, to better illustrate this application, numerous specific details are provided in the following detailed embodiments. Those skilled in the art should understand that this application can be implemented without certain specific details. In some instances, methods, means, components, and circuits well-known to those skilled in the art have not been described in detail in order to highlight the main points of this application.

[0121] like Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 and Figure 8 As shown, this invention provides an integrated horizontal transport, erection, and launch system for reusable liquid rockets, comprising a mobile vehicle 1, a detachable support frame 2, a locking device, and a launch pad 3, wherein...

[0122] The mobile vehicle 1 is located at the lower part of the support frame 2 and is used to drive the support frame 2 to move horizontally;

[0123] The upper part of the support frame 2 is equipped with a horizontally placed reusable liquid rocket 4. The support frame 2 is also used to adjust the horizontally placed reusable liquid rocket 4 to stand upright.

[0124] The locking device is located on the support frame 2 and is used to fix the reusable liquid rocket 4 axially and radially to prevent the reusable liquid rocket 4 from shifting on the support frame 2.

[0125] Launch pad 3 is fixed to one end of support frame 2 and is used to support the entire rocket body after the reusable liquid rocket 4 is erected.

[0126] Specifically, the reusable liquid rocket integrated horizontal transport, erection and launch system provided in this embodiment of the invention consists of a mobile vehicle 1, a detachable support frame 2, a locking device and a launch pad 3.

[0127] The number of detachable support frames 2 can be increased according to the size of the rocket body to accommodate rockets of various sizes, improving system compatibility. At the same time, a single set of tooling can be used to complete the transfer process of rockets of different sizes, greatly reducing manufacturing costs.

[0128] In addition, a portion of the locking device is used to adhere to and hold the outer circumference of the reusable liquid rocket 4, thereby radially fixing the reusable liquid rocket 4. Another portion is fixedly connected to the docking plate on the outer circumference of the tail end of the rocket, thereby axially fixing the reusable liquid rocket. This ensures that the reusable liquid rocket 4 is firmly fixed on the support frame 2, preventing the reusable liquid rocket 4 from rotating or moving axially on the support frame 2. This reduces the risk of displacement of the rocket during horizontal transport, improves the reliability of the erection system, and thus facilitates the safe launch of the rocket.

[0129] In addition, the launch pad 3 is fixed to one end of the support frame 2, making the launch pad 3 and the support frame 2 an integrated design. The launch pad 3 can be erected together with the support frame 2, which can ensure that the rocket and the launch pad 3 are accurately docked in advance, reduce the on-site hoisting equipment, improve the rocket's erection efficiency, and make it easier for the launch pad to quickly support the reusable liquid rocket 4 after it has been erected.

[0130] The entire reusable liquid rocket integrated horizontal transport, erection, and launch system is suitable for rockets of various sizes, has high compatibility, can accurately dock with the launch pad, improves work efficiency, and is universally compatible with multiple launch sites. This reduces costs and also reduces the risk of rocket displacement during horizontal transport, improving the reliability of the erection system.

[0131] It should be noted that, to facilitate the disassembly of the support frame 2 and to accommodate rocket bodies of different lengths, the support frame 2 is a frame structure, comprising at least a detachable first frame body 5, a second frame body 6, and a third frame body 7. This frame structure reduces the weight of the support frame 2 and facilitates its rapid erection, improving rocket launch efficiency. To ensure a tighter and more secure connection between the first frame body 5, the second frame body 6, and the third frame body 7, the second frame body 6 is positioned between the first frame body 5 and the third frame body 7, with both ends of the second frame body 6 fixed to the first frame body 5 and the third frame body 7 respectively using locking bolts. It should be noted that when fixing the first frame body 5, the second frame body 6, and the third frame body 7, their axes must coincide, and these coincident axes must be parallel to the axis of the reusable liquid rocket 4. This prevents the support frame 2 from bending, which could affect the rocket's stability.

[0132] In this embodiment, the support frame 2 is illustrated by the first frame body 5, the second frame body 6, and the third frame body 7, which are detachably set. In actual applications, the number of frame bodies can be increased according to the length of the rocket, which will not be discussed in detail here.

[0133] To ensure the stability of the reusable liquid rocket structure mounted on the frame structure and prevent deformation due to lack of support (the rocket body is too long, and the lack of support in the middle section will cause it to sink under gravity), auxiliary support brackets 8 are provided at the upper part of the frame structure to support the rocket body 4. These auxiliary support brackets 8 are respectively installed on the first frame body 5 and the second frame body 6, and are arranged along the axial direction of the rocket body. To facilitate the delivery of liquid and gas to the rocket and to keep the external structure of the frame structure simple, the frame structure internally includes a pipeline system for delivering liquid and gas to the reusable liquid rocket 4, as well as a hydraulic cylinder structure. Furthermore, to facilitate the erection and adjustment of the reusable liquid rocket, the support frame 2 is also used to erect the horizontally placed reusable liquid rocket 4. One end of the hydraulic cylinder structure is fixedly connected to the internal crossbeam of the support frame 2 via a pivot, and the other end is fixed to the ground.

[0134] To prevent the support frame 2 from being burned by the high-temperature flames generated by the engine, for example, a heat shield is installed on the outer surface of the support frame 2. The heat shield can protect the support frame 2 from deformation due to high temperature, and also protect the pipes and electrical equipment inside the support frame 2, keeping the entire support frame 2 and its internal structure intact and facilitating reuse. To ensure that the heat shield is firmly fixed to the support frame 2, for example, the heat shield is fixed to the support frame 2 with locking bolts.

[0135] In this embodiment, the auxiliary support 8 includes a crossbeam base 9, a lifting assembly 10, an anti-tilt limiting cylinder assembly 11, a lifting support seat 12, and an arrow body support 13, wherein...

[0136] Both the lifting platform assembly 10 and the anti-tilt limit cylinder assembly 11 are located between the crossbeam base 9 and the lifting support seat 12. The anti-tilt limit cylinder assembly 11 is symmetrically arranged on both sides of the lifting platform assembly 10.

[0137] The lower end of the crossbeam base 9 is connected to the support frame 2, and the upper end of the crossbeam base 9 is connected to the lower ends of the lifting assembly 10 and the anti-tilt limit cylinder assembly 11 respectively. The upper ends of the lifting assembly 10 and the anti-tilt limit cylinder assembly 11 are connected to the lower ends of the lifting support seat 12 respectively. The upper end face of the lifting support seat 12 is fixedly connected to the lower end face of the arrow body support bracket 13. The upper end face of the arrow body support bracket 13 is used to fit against the surface of the arrow body.

[0138] In addition, the anti-tilt limiting cylinder assembly 11 includes an anti-tilt base and an elastic cylinder. The lower end of the anti-tilt base is fixedly connected to the crossbeam base 9, and the upper end of the anti-tilt base is welded and fixed to the lower end of the cylinder. The upper end of the cylinder is used to abut against the lower end face of the lifting support seat 12. In this embodiment, the structure of the cylinder is similar to a corrugated tube structure. To increase the elasticity of the cylinder, the cylinder can be a double-layer corrugated tube structure. In practical applications, a metal spring is provided inside the cylinder, and a support plate is provided on the upper part of the cylinder. The upper end of the metal spring is fixedly connected to the lower end of the support plate, and the outer circumferential side of the support plate is in contact with the inner wall of the cylinder and can slide along the inner wall of the cylinder. The lower end of the metal spring is fixed to the anti-tilt base. In addition, in order to ensure the stability of the anti-tilt base structure and avoid deformation due to excessive pressure, for example, the shape of the anti-tilt base is a cylindrical structure, and reinforcing plates are evenly provided on the outer circumferential side of the cylinder.

[0139] In use, the lifting support seat 12 is raised and lowered by the lifting assembly 10, thereby ensuring that the arrow body support 13 moves up and down with the lifting support seat 12. The anti-tilt limit cylinder assembly 11 supports both ends of the lifting support seat 12 to ensure that both ends of the lifting support seat 12 are balanced and to prevent the lifting support seat 12 from tilting. This further facilitates the support of the arrow body support 13 on the arrow body, thereby ensuring the stability of the arrow body structure.

[0140] In the same embodiment, in order to ensure that the reusable liquid rocket 4 is firmly fixed on the support frame 2 and to prevent the reusable liquid rocket 4 from rotating and moving axially on the support frame 2, for example, the locking device includes a first locking mechanism 14 and a second locking mechanism 15, wherein the first locking mechanism 14 is used to radially fix the rocket body end near the fairing end, and the second locking mechanism 15 is used to fix the rocket body near the rocket engine end to limit the axial movement of the reusable liquid rocket 4.

[0141] Specifically, the first locking mechanism 14 is fixed to the first frame body 5 and is located away from the second frame body 6. It includes at least two sets of symmetrically arranged clamping devices 16, a first adjusting device 17 and a first fixing device 18. The two ends of each set of first adjusting devices 17 are respectively connected to the corresponding clamping device 16 and the first fixing device 18.

[0142] The clamping device 16 is used to fit against the corresponding surface of the arrow body;

[0143] The first adjustment device 17 is used to adjust the distance between the clamping device 16 and the surface of the arrow body;

[0144] The first fixing device 18 is used to fix the first adjusting device 17 so that the first locking mechanism 16 is fixed on the support frame 2.

[0145] In this embodiment, in order to ensure the structural stability of the clamping device 16 and to make the clamping device 16 fit more closely to the surface of the arrow body, for example, the clamping device 16 is roughly triangular in shape, and the end face of the clamping device 16 near the surface of the arrow body is a curved end face.

[0146] The first adjustment device 17 includes an upper adjustment bracket 19, a lower adjustment bracket 20, and a first electric lever 21. The upper end of the upper adjustment bracket 19, near the arrow body, is connected to the clamping device 16 via a first rotating shaft 22 (the clamping device 16 can rotate outward around the first rotating shaft 22). The lower end of the upper adjustment bracket 19, near the arrow body, is connected to the lower adjustment bracket 20, near the arrow body, via a second rotating shaft 23 (the lower end of the upper adjustment bracket 19 can rotate outward around the second rotating shaft 23). The upper end of the first electric lever 21 is connected to the upper end of the upper adjustment bracket 19, away from the arrow body, via a third rotating shaft 24 (the upper end of the upper adjustment bracket can rotate outward around the third rotating shaft). The lower end of the first electric lever 21 is connected to the lower adjustment bracket 20, away from the arrow body, via a fourth rotating shaft 25.

[0147] In use, by adjusting the length of the first electric lever 21, the lower end of the upper adjustment bracket 19 is rotated along the first rotating shaft 22, thereby moving the upper end of the upper adjustment bracket 19. This causes the clamping device 16 to move with the upper adjustment bracket 19, thereby adjusting the distance between the clamping device 16 and the surface of the rocket body. This ensures that the clamping device 16 is in close contact with the surface of the rocket body, thus completing the support and fixation of the rocket body. This further prevents the reusable liquid rocket 4 from radially moving on the support frame 2, thereby ensuring that the rocket body is firmly fixed.

[0148] like Figure 14 , Figure 15 , Figure 16 , Figure 17When the clamping device 16 is in contact with the arrow body, in order to ensure uniform pressure on the arrow body surface and avoid damage to the arrow body surface due to uneven pressure, and to further limit the movement of the lower end of the clamping device 16 to the upward adjustment bracket 19, for example, a first limiting device 73 is provided on the outer surface of the side of the upward adjustment bracket 19 close to the clamping device 16. The first limiting device 73 includes a first limiting block 76 with a through hole and a first adjusting bolt 77. The first limiting block 76 is welded and fixed to the upward adjustment bracket 19. One end of the first adjusting bolt 77 passes through the through hole and is used to support the lower end of the clamping device 16 on the outer surface of the side close to the upward adjustment bracket 19, thereby adjusting the contact distance between the lower end of the clamping device 16 and the arrow body, ensuring that the entire clamping device is evenly attached to the arrow body surface and ensuring the integrity of the arrow body surface. In addition, in order to facilitate the adjustment of the length of the first adjusting bolt 77, for example, the first adjusting bolt 77 and the through hole are provided with internal and external threads.

[0149] Furthermore, the upper end of the clamping device 16 is further limited to rotate and move along the first rotation axis 22 to the side of the upward adjustment bracket 19. A second limiting device 74 is also provided on the upper surface of the side of the upward adjustment bracket 19 that contacts the clamping device 16. The second limiting device 74 includes two sets of parallel limiting mechanisms. Each set of limiting mechanisms includes a second limiting block 78 with a through hole and a second adjusting bolt 79. The second limiting block 78 is fixed to the upper surface of the upward adjustment bracket 19. One end of the second adjusting bolt 79 passes through the through hole and is used to support the upper outer surface of the clamping device 16, thereby adjusting the contact distance between the upper end of the clamping device 16 and the arrow body, ensuring that the entire clamping device is evenly fitted to the arrow body surface. In this embodiment, to facilitate the adjustment of the second limiting device 74, the second adjusting bolt 79 and its corresponding through hole are connected by internal and external threads. In addition, the arrangement of two sets of parallel limiting mechanisms makes the support of the limiting mechanisms on the upper outer surface of the clamping device 16 more solid, and at the same time can also disperse the pressure on the surface of the clamping device 16, making the structure of the clamping device 16 more stable.

[0150] To prevent the lower end of the clamping device 16 from moving away from the upper adjustment bracket 19 (the clamping device 16 may rotate outwards along the first rotation axis 22, potentially shifting its lower end to the upper end), an elastic device 75 is provided on the outer surface of the upper adjustment bracket 19 closest to the clamping device 16. The elastic device 75 includes an elastic element 80, a first elastic seat 81, and a second elastic seat 82. The two ends of the elastic element 80 are connected to the first elastic seat 81 and the second elastic seat 82, respectively. The first elastic seat 81 and the second elastic seat 82 are fixed to the upper adjustment bracket 19 and the clamping device 16, respectively. The elastic device 75 prevents the lower end of the clamping device 16 from moving towards the upper adjustment bracket 19, keeping its displacement within a reasonable range. In this embodiment, a metal spring is used as an example of the elastic element; however, other elastic components can also be used in practical applications, which will not be discussed further here.

[0151] To ensure the first locking mechanism 14 is more securely fixed and to prevent displacement, while facilitating adjustment of the fixed position and angle of the first fixing device 18, for example, the first fixing device 18 includes an upper support 26, a lower support 27, and a second electric lever 28. The upper end of the upper support 26 is connected to the lower end of the lowering bracket 20 near the arrow body via a fifth rotating shaft 29. The lower end of the upper support 26 is locked and fixed to the upper longitudinal beam 31 (located on the first frame and away from the ground) on the side of the support frame 2 near the arrow body by bolts and nuts. The upper end of the lower support 27 is connected to the lower end of the second electric lever 28 via a sixth rotating shaft 30. The lower end of the lower support 27 is locked and fixed to the lower longitudinal beam 32 (located on the first frame and near the ground) on the side of the support frame 2 near the arrow body by bolts and nuts. The upper end of the second electric lever 28 is connected to the lower end of the lowering bracket 20 away from the arrow body via a seventh rotating shaft 33.

[0152] To ensure the structural stability of the upper support 26 and the lower support 27, and to facilitate fixing and rotation, for example, the upper support 26 and the lower support 27 are both triangular prism structures with a hollow center. The hollow design can also reduce the weight of the upper support 26 and the lower support 27, making it easier for the upper support 26 and the lower support 27 to rotate quickly and improving response efficiency.

[0153] In addition, in order to obtain the pressure on the first rotating shaft 22 in a timely manner, for example, a first pin force sensor is also installed on the first rotating shaft. The pressure on the first rotating shaft 22 can be obtained in a timely manner through the force sensor, and then the pressure applied to the surface of the arrow body by the clamping device 16 can be adjusted according to the pressure data.

[0154] It should be noted that the second locking mechanism 15 is fixedly connected to the docking plate on the outer side of the tail end of the rocket to complete the axial fixation of the reusable liquid rocket 4. The second locking mechanism 15 is fixed on the third frame body 7 and away from the end of the second frame body 6. The second locking mechanism 15 includes at least two sets of symmetrically arranged docking devices, a second adjustment device, and a second fixing device.

[0155] Specifically, one side of the docking device is used to be fixedly connected to the docking panel on the outside of the arrow body, and the other side is connected to the upper end of the second adjustment device. The lower end of the second adjustment device is fixedly connected to the upper end of the support frame 2. The upper end of the second fixing device is fixed to the side of the second adjustment device away from the arrow body, and the lower end of the second fixing device is fixed to the inner frame sidewall of the support frame 2.

[0156] In this embodiment, the second adjustment device includes a fixed base 34, a triangular arm 35, a lifting mechanism 36, and a telescopic mechanism 37.

[0157] The lower end of the fixed base 34 is fixed to the support frame 2. The upper end of the fixed base 34 is connected to the lower end of the triangular arm 35 through the eighth rotating shaft 38. The triangular arm 35 can rotate along the surface of the eighth rotating shaft 38. The upper end of the triangular arm 35 and the side closer to the arrow body is connected to the lower end of the lifting mechanism 36 through the ninth rotating shaft 39. The upper end of the lifting mechanism 36 is connected to the docking device. The upper end of the triangular arm 35 and the side farther from the arrow body is connected to the fixed end of the telescopic mechanism 37 through the tenth rotating shaft 40. The telescopic end of the telescopic mechanism 37 is connected to the outer wall of the lifting mechanism 36 through the eleventh rotating shaft 41.

[0158] In addition, in order to obtain the pressure on the tenth rotating shaft 40 in a timely manner, for example, a tenth pin force sensor is also installed on the tenth rotating shaft 40. The force sensor can obtain the pressure on the tenth rotating shaft 40 in a timely manner, and then adjust the pressure applied by the telescopic mechanism 37 to the lifting mechanism 36 according to the pressure data.

[0159] Furthermore, in this embodiment, the first rotating shaft 22 and the tenth rotating shaft 40 are used for explanation. In actual operation, pin-shaft force sensors can be installed on each rotating shaft according to actual needs, so as to obtain the pressure of each rotating shaft in a timely manner and facilitate the timely acquisition of pressure data of each rotating shaft.

[0160] In addition, the components (movable components) connected to each rotating axis can all rotate along the surface of the rotating axis.

[0161] To ensure the stability of the second adjustment device structure and prevent deformation, for example, the space enclosed by the triangular arm 35, the lifting mechanism 36, and the telescopic mechanism 37 forms a triangular structure.

[0162] In the same embodiment, the lifting mechanism 36 is an electric cylinder structure. The output end of the electric cylinder structure is also provided with a plate 42 and a locking block 43. The upper part of the plate 42 is provided with a slot with two ends communicating (the extension direction of the two ends of the slot is perpendicular to the rocket axis). One side surface of the locking block 43 is in close contact with the slot sidewall on the plate 42. The locking block 43 is fixed to the plate 42 by locking bolts.

[0163] To precisely adjust the height of the lifting mechanism 36, for example, a scale mark is provided on the surface along the axial direction of the lifting mechanism 36 and located at the output end.

[0164] In this embodiment, to adjust the position of the second adjustment device in a timely manner, allowing the triangular arm 35 to rotate rapidly along the surface of the eighth rotation axis 38, the second fixing device includes, for example, an electric cylinder assembly 48, a fixed base plate 49, a first rotating shaft 50, and a second rotating shaft 51. The telescopic end of the electric cylinder assembly 48 is fixed to the side of the triangular arm 35 away from the rocket body via the first rotating shaft 50. The fixed end of the electric cylinder assembly 48 is connected to one side of the fixed base plate 49 via the second rotating shaft 51. The other side of the fixed base plate 49 is fixed to the inner frame sidewall of the support frame 2. After the rocket is erected, the electric cylinder assembly 48 drives the triangular arm 35 to rotate along the surface of the eighth rotation axis 38, thereby providing sufficient flight clearance for the rocket.

[0165] During transportation, in order to further secure the second adjustment device and prevent it from shaking, for example, the lifting mechanism 36 is also provided with an anti-tilt device 44 on the side near the arrow body. One end of the anti-tilt device 44 is connected to the outer wall of the lifting mechanism 36, and the other end is fixed to the crossbeam on the support frame 2.

[0166] The anti-tilt device 44 includes an adjusting sleeve, adjusting rods located at both ends of the adjusting sleeve, a first locking shaft and a second locking shaft. One end of the adjusting rod is threadedly connected to the adjusting sleeve, and the other end is connected to the outer wall of the lifting mechanism 36 through the first locking shaft. The other end is fixed to the crossbeam on the support frame 2 through the second locking shaft. In this embodiment, the outer wall of the lifting mechanism and the crossbeam on the support frame are respectively provided with fixing block groups. Each fixing block group includes two symmetrical fixing blocks with through holes. The first locking shaft and the second locking shaft pass through the corresponding through holes to complete the fixation with the lifting mechanism 36 and the crossbeam. The two ends of the adjusting rod can rotate along the surfaces of the first locking shaft and the second locking shaft.

[0167] like Figure 1 , Figure 2 , Figure 8 , Figure 9 and Figure 18 As shown, the docking device includes a docking plate 45, a rotating shaft 46 and a fixed sleeve 47. One end of the rotating shaft 46 passes through the fixed sleeve 47 and is fixedly connected to the docking plate 45, and the docking plate 45 can rotate with the rotating shaft 46.

[0168] To ensure the structural stability of the docking plate 45, for example, the docking plate 45 is a cube. To facilitate docking of the docking plate 45 with the rocket, the surface of the docking plate 45 that docks with the rocket is a curved surface.

[0169] The fixing sleeve 47 includes an integrally formed upper sleeve body and a lower sleeve body. The two ends of the lower sleeve body are fixed to the plate 42 by bolts. The upper part of the lower sleeve body is connected to the bottom of the upper sleeve body. The middle part of the upper sleeve body is provided with a hollow space for accommodating the rotating shaft 46. The top of the upper sleeve body is provided with a lifting lug.

[0170] To ensure the fixed sleeve 47 is securely fixed to the plate 42 and to prevent displacement of the fixed sleeve 47 on the surface of the plate 42, for example, the plate 42 is also provided with strip-shaped wedges 83 (in this embodiment, there are two strip-shaped wedges 83). The two sides of the strip-shaped wedges abut against the inner wall of the slot and the outer wall of the fixed sleeve, respectively, and are fixed to the plate 42 by locking bolts. Each strip-shaped wedge 83 is symmetrically arranged on both sides of the fixed sleeve 47 (lower sleeve body) (each strip-shaped wedge is sandwiched between the fixed sleeve 47 and the slot wall), ensuring that the fixed sleeve 47 is securely fixed while preventing displacement of the fixed sleeve 47 along the rocket axial direction. In addition, by replacing the strip-shaped wedges 83 of different sizes, the position of the docking device can be finely adjusted (moved on the plate surface, i.e., along the rocket axial direction), thereby ensuring that the docking plate 45 can quickly dock with the rocket and improve work efficiency. In this embodiment, the height of the strip-shaped wedges 83, the lower sleeve body, and the slot wall are all the same, and the shape of the strip-shaped wedges 83 is a cuboid structure.

[0171] It should be noted that, in order to limit the movement of the fixing sleeve 47 away from the plate (the lower sleeve moves upward and detaches from the plate), for example, the two sides of the lower sleeve are first inclined structures, the upper end of the first inclined structure gradually expands downward, and the side of the strip wedge block 83 near the lower sleeve is provided with a second inclined structure that matches the inclined structure, the upper end of the second inclined structure gradually contracts downward. The surfaces of the first and second inclined structures that are close to each other are tightly attached to each other. By setting the first and second inclined structures, the contact area between the two is increased, thereby increasing the downward pressure on the lower sleeve (force analysis of the first inclined structure, in which there is a vertical downward pressure and a horizontal downward pressure in the direction of the center of the sleeve), preventing the fixing sleeve 47 from moving away from the plate while also preventing the lower sleeve from sliding on the surface of the plate 42, further ensuring that the fixing sleeve 47 is firmly fixed on the plate 42.

[0172] like Figure 1 , Figure 7 and Figure 10As shown, in order to ensure that the launch pad 3 is firmly fixed to the support frame 2, for example, the launch pad 3 includes a launch pad body 52, two sets of fixed arms 53, a twelfth rotating shaft 54 ​​and a fixed connector 55.

[0173] Specifically, when the launch platform 3 is fixed to the third frame body 7, the twelfth rotation axis 54 is set on both sides of the launch platform body 52 and fixedly connected to the launch platform body 52. ​​The fixed arms 53 are symmetrically arranged on the support frame 2 (third frame body 7). The twelfth rotation axis 54 on both sides is connected to the fixed arms 53 that are close to each other, and the launch platform body 52 can rotate with the twelfth rotation axis 54.

[0174] The fixing connector 55 is used to fix the launch pad body 52 and prevent the launch pad body 52 from rotating with the twelfth rotation axis 54. The top end of the fixing connector 55 is connected to the surface of the launch pad body 52 near the support frame 2, and the bottom end is fixed to the support frame 2. Through the cooperation of the fixing connector 55, the twelfth rotation axis 54 and the fixing arm 53, the launch pad 3 is firmly fixed, so that the launch pad 3 and the support frame 2 form an integrated design, which facilitates the precise docking of the entire rocket with the launch pad and improves the rocket's erection efficiency. In this embodiment, the fixed connector 55 includes a first base body 56, a second base body 57, a first connector 58, a second connector 59, and a connecting rotation shaft 60. The bottom end of the first base body 56 is connected to the third frame body 7, the upper end of the first base body 56 is connected to the bottom end of the first connector 58, the upper end of the first connector 58 is connected to the lower end of the second connector 59 via the connecting rotation shaft, the upper end of the second connector 59 is connected to the lower end of the second base body 57, and the upper end of the second base body 57 is fixedly connected to the launch pad body 52. ​​In this embodiment, the first connector 58 and the second connector 59 have a U-shaped structure, and the cross-section of the connecting rotation shaft 60 along the axial direction is I-shaped.

[0175] The launch pad body 52 includes a platform 68, and on the platform 68, a primary gas-liquid connector and a tilting mechanism 69, a traction release mechanism 70, a primary electrical connector and a tilting mechanism 71, and a reflux trough flap mechanism 72.

[0176] The primary gas-liquid connector and the rear tilting mechanism 69 are symmetrically arranged on the platform 68 and located on one side close to the twelfth rotating shaft 54. The traction release mechanism 70 is evenly arranged on the platform 68 at equal intervals along the circumference. The primary electrical connector and the rear tilting mechanism 71 are located on one side of the platform and are arranged perpendicular to the extension direction of the twelfth rotating shaft 54. The backflow trough flap mechanism 72 is located at the center of the platform 68.

[0177] The first-stage gas-liquid connector and the rear tilting mechanism 69 are used to refuel the first stage of the reusable liquid rocket with gas and liquid. When the rocket takes off, the first-stage gas-liquid connector is tilted back by the rear tilting mechanism 69 to provide sufficient space for the rocket to take off.

[0178] Traction Release Mechanism 70: Safety Locking at Initial Ignition. After rocket ignition, traction release mechanism 70 restrains the rocket on the launch pad. The engine first operates stably on the platform at about 75% of its operating condition and will not take off immediately. This leaves a fault diagnosis window for the propulsion system and avoids fatal faults such as single engine failure to ignite or unstable combustion during engine start-up, which could directly carry the rocket into the air and cause catastrophic accidents such as launch pad explosions.

[0179] After a health check, the system is released precisely. It completes intelligent fault detection of the entire rocket propulsion system in about 0.3 seconds. After confirming that all engine conditions are completely normal, the four sets of traction release mechanisms are unlocked simultaneously, and the rocket is officially ignited and lifted off. This is equivalent to adding an extra critical safety insurance to the launch process.

[0180] The first-stage electrical connector and the rear-tilting mechanism 71 are used to energize the first stage of the reusable liquid rocket. When the rocket takes off, the first-stage electrical connector and the rear-tilting mechanism 71 tilt backward to provide sufficient space for the rocket to take off.

[0181] Flow trough flap mechanism 72: Pre-launch sealing protection: When the rocket is vertically erected on the launch pad, the flap is fully closed, completely sealing the deep pit entrance of the flow trough, forming a flat launch pad surface, preventing personnel, tools, and debris from accidentally falling into the flow trough, and ensuring the safety of personnel operations throughout the entire pre-launch process. Rapid opening at launch: Seconds before rocket ignition, the flap is rapidly flipped downwards and opened by an electric actuator, completely clearing the exhaust channel, ensuring that the 3000℃ high-temperature, high-speed exhaust plume ejected by the rocket can smoothly enter the flow trough without being blocked by the sealed structure, preventing backfire and avoiding ablation of the rocket body bottom and launch pad facilities.

[0182] It should be noted that, in order to facilitate the fixing of the two sets of fixing arms 53 while reserving sufficient space for the second locking mechanism 15, for example, a fourth frame and a fifth frame are symmetrically provided on both sides of the third frame 7. The fourth and fifth frames are fixed to the third frame 7 by bolts, and the two sets of fixing arms are fixed to the fourth and fifth frames respectively. The arrangement of the fourth and fifth frames can meet the fixing of rockets with different radial dimensions, improving the applicability of the entire system. In addition, to avoid scorching by high-temperature flames, heat shields are fixed on the outer side of the fourth and fifth frames.

[0183] like Figure 11 , Figure 12 and Figure 13 As shown, in order to effectively support the fairing and prevent it from deforming during horizontal transport, the erection system also includes a soft support device 61, which is used to support the fairing.

[0184] The soft support device 61 includes a connecting bracket 62, third adjustment devices symmetrically arranged on both sides of the connecting bracket 62, and a flexible flat strap 63 for connecting to the third adjustment devices on both sides.

[0185] The connecting bracket 62 is located at one end of the support frame 2 (the end closest to the first frame body) and is detachably and fixedly connected to the support frame 2. In this embodiment, the connecting bracket 62 is generally a cuboid frame structure, wherein the height of the cuboid frame structure at the end closest to the first frame body is greater than the height of the cuboid frame structure at the end furthest from the first frame body. Additionally, the cuboid frame structure also contains air conditioning pipelines for supplying gas to the interior of the fairing.

[0186] The third adjustment device includes a base 64, an adjusting electric cylinder 65, a support rod 66, and a winding winch 67. The base is located outside the connecting bracket 62 and one end is connected to the connecting bracket 62, while the other end extends away from the connecting bracket 62. The bottom end of the adjusting electric cylinder 65 is connected to the base 64 via a thirteenth rotating shaft, and the top end of the adjusting electric cylinder 65 is connected to the body of the support rod 66 via a fourteenth rotating shaft. The bottom end of the support rod 66 is connected to the connecting bracket 62 via a fifteenth rotating shaft. The top end of the support rod 66 is used to support the flexible flat strip 63. The winding winch is fixed on the base 64 and is used to adjust the length of the flexible flat strip 63.

[0187] When the rocket body is fixed to the support frame 2, the flexible flat strip 63 located between the two third adjustment devices is set in parallel. A portion of the flexible flat strip 63 is wound around the surface of the winding winch 67. In use, the winding winch 67 is started to control the length of the flexible flat strip 63. At the same time, the telescopic end of the electric cylinder 65 is adjusted to move upward, so that the support rod 66 rotates along the surface of the fifteenth rotating axis. At this time, the support flexible flat strip 63 is just tightly attached to the bottom of the fairing. Then, the electric cylinder 65 and the winding winch 67 are closed, thereby completing the support of the fairing by the soft support device 61.

[0188] The flexible flat strip 63 forms a large-arc envelope support surface, which has a large area of ​​flexible contact with the outer surface of the fairing. This can significantly reduce the contact pressure and avoid local stress concentration and structural deformation caused by rigid support. At the same time, it can effectively buffer the vibration and impact during transportation and prevent scratches on the fairing's thermal protection coating and paint surface, thus meeting the high-precision protection requirements of large thin-walled fairings.

[0189] In addition, to prevent the flexible support strip 63 from detaching from the top of the support rod 66, the top of the support rod 66 has a U-shaped opening, and double rollers are provided inside the U-shaped opening. The two ends of the double rollers are fixed to the groove wall of the U-shaped opening. The flexible support strip 63 on the support rod 66 is located between the double rollers. The part between the double rollers and the groove wall forms a closed space, which effectively prevents the flexible support strip 63 from detaching from the top of the support rod 66, thereby facilitating the support of the fairing by the soft support device 61.

[0190] The entire erection system also has the following advantages:

[0191] First, launch efficiency has been greatly improved, supporting high-density, flight-like launches. The integrated design of the entire system has realized the "factory assembly and testing, launch only at the work station" mode, reducing the time occupied by a single launch work station from the traditional 7-10 days to less than 3 days. The turnaround efficiency of the launch site work station has been increased by more than 100%, which can meet the high-frequency launch requirements of commercial satellite constellation networking.

[0192] Secondly, it has excellent transportability and flexible and efficient cross-base deployment. The segmented and detachable erector frame, along with the dual-mode design, ensures that the system fully complies with domestic highway transport width restrictions in a straight-line configuration. Cross-base transfers do not require special approval for exceeding width and size limits, enabling rapid deployment to multiple launch sites and meeting the scheduling needs of multi-site collaborative launches in commercial aerospace.

[0193] Third, the zero-second collaborative avoidance system significantly improves launch safety. It constructs a multi-level zero-second collaborative avoidance system consisting of "restraint release + gas-liquid-electric connector + erector frame tilting back". All ground interfaces are simultaneously unlocked and avoidance at the moment of rocket liftoff, eliminating the launch risks caused by interface jamming and untimely detachment, and greatly improving launch reliability and safety.

[0194] Fourth, it is universally compatible with multiple launch sites, significantly reducing the total life cycle cost. The mobile launch pad adopts a standardized bottom interface, and one system can be compatible with multiple fixed launch positions of different specifications. There is no need to customize special tooling for different launch sites, reducing the R&D and manufacturing cost of ground equipment by more than 50%. At the same time, the three-level model does not require the construction of a vertical assembly plant with ultra-high clearance. Horizontal assembly and testing can be completed in a flat plant, reducing launch site infrastructure investment by more than 30% and significantly reducing the total life cycle cost.

[0195] Fifth, the system has a high degree of integration and is convenient and reliable in operation and maintenance. It integrates functions such as transportation, erection, launch, and environmental protection into two main structures, which greatly reduces the number of scattered equipment and cross-system interfaces, and reduces the workload of interface coordination and on-site debugging. The modular design supports segmented maintenance and rapid replacement, with a small impact range of failures and high operation and maintenance efficiency.

[0196] The above embodiments can be combined with each other and have corresponding technical effects.

[0197] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A reusable liquid rocket integrated horizontal transport, erection, and launch system, characterized in that, It includes a mobile vehicle, a detachable support frame, a locking device, and a launch pad, among which... The mobile vehicle is located at the lower part of the support frame and is used to drive the support frame to move horizontally; The upper part of the support frame is provided with a horizontally placed reusable liquid rocket, and the support frame is also used to adjust the horizontally placed reusable liquid rocket to stand upright. The locking device is located on the support frame and is used to fix the reusable liquid rocket axially and radially to prevent the reusable liquid rocket from shifting on the support frame. The launch pad is fixed to one end of the support frame and is used to support the entire rocket body after the reusable liquid rocket is erected.

2. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 1, characterized in that, The support frame is a frame structure and includes at least a detachable first frame, a second frame, and a third frame. The second frame is located between the first frame and the third frame, and its two ends are fixedly connected to the first frame and the third frame, respectively. The upper part of the frame structure is provided with an auxiliary support bracket for supporting the body of the reusable liquid rocket. The auxiliary support bracket is respectively set on the first frame body and the second frame body. The interior of the frame structure is provided with a pipeline system for supplying liquid and gas to the reusable liquid rocket and a hydraulic cylinder structure. One end of the hydraulic cylinder structure is fixedly connected to the internal crossbeam of the support frame through a rotating shaft, and the other end is used to fix it to the ground.

3. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 2, characterized in that, The auxiliary support bracket includes a crossbeam base, a lifting assembly, an anti-tilt limiting cylinder assembly, a lifting support seat, and an arrow body support bracket, wherein... Both the lifting platform assembly and the anti-tilt limiting cylinder assembly are located between the crossbeam base and the lifting support seat, with the anti-tilt limiting cylinder assemblies symmetrically arranged on both sides of the lifting platform assembly. The lower end of the crossbeam base is connected to the support frame, and the upper end of the crossbeam base is connected to the lower ends of the lifting assembly and the anti-tilt limiting cylinder assembly respectively. The upper ends of the lifting assembly and the anti-tilt limiting cylinder assembly are connected to the lower ends of the lifting support seat respectively. The upper end face of the lifting support seat is fixedly connected to the lower end face of the arrow body support bracket, and the upper end face of the arrow body support bracket is used to fit against the surface of the arrow body.

4. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 1, characterized in that, The locking device includes a first locking mechanism and a second locking mechanism, wherein the first locking mechanism is used to radially fix the rocket body end near the fairing end, and the second locking mechanism is used to fix the rocket body near the rocket engine end to limit the axial movement of the reusable liquid rocket.

5. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 4, characterized in that, The first locking mechanism includes at least two sets of symmetrically arranged clamping devices, a first adjusting device, and a first fixing device. The two ends of each set of the first adjusting device are respectively connected to the corresponding clamping device and the first fixing device. The clamping device is used to fit against the corresponding arrow body surface; The first adjusting device is used to adjust the distance between the clamping device and the surface of the arrow body; The first fixing device is used to fix the first adjusting device so that the first locking mechanism is fixed on the support frame.

6. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 5, characterized in that, The clamping device is roughly triangular in shape, and the end face of the clamping device near the surface of the arrow body is a curved end face. The first adjustment device includes an upper adjustment bracket, a lower adjustment bracket, and a first electric lever. The upper end of the upper adjustment bracket, near the arrow body, is connected to the clamping device via a first rotating shaft. The lower end of the upper adjustment bracket, near the arrow body, is connected to the lower adjustment bracket, near the arrow body, via a second rotating shaft. The upper end of the first electric lever is connected to the upper end of the upper adjustment bracket, away from the arrow body, via a third rotating shaft. The lower end of the first electric lever is connected to the lower adjustment bracket, away from the arrow body, via a fourth rotating shaft. The first fixing device includes an upper support, a lower support, and a second electric lever. The upper end of the upper support is connected to the lower end of the lowering bracket and the end near the arrow body via a fifth rotating shaft. The lower end of the upper support is fixed to the upper longitudinal beam on the side of the support frame near the arrow body. The upper end of the lower support is connected to the lower end of the second electric lever via a sixth rotating shaft. The lower end of the lower support is fixed to the lower longitudinal beam on the side of the support frame near the arrow body. The upper end of the second electric lever is connected to the lower end of the lowering bracket and the end away from the arrow body via a seventh rotating shaft. Both the upper support and the lower support are triangular prism structures with a hollow center.

7. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 4, characterized in that, The second locking mechanism includes at least two sets of symmetrically arranged docking devices, a second adjusting device, and a second fixing device. One side of the docking device is used to be fixedly connected to the docking panel on the outside of the arrow body, and the other side is connected to the upper end of the second adjustment device. The lower end of the second adjustment device is fixedly connected to the upper end of the support frame. The upper end of the second fixing device is fixed to the side of the second adjustment device away from the arrow body, and the lower end of the second fixing device is fixed to the inner frame sidewall of the support frame.

8. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 7, characterized in that, The second adjustment device includes a fixed base, a triangular arm, a lifting mechanism, and a telescopic mechanism, wherein... The lower end of the fixed base is fixed to the support frame. The upper end of the fixed base is connected to the lower end of the triangular arm through the eighth rotating shaft. The upper end of the triangular arm, on the side closer to the arrow body, is connected to the lower end of the lifting mechanism through the ninth rotating shaft. The upper end of the lifting mechanism is connected to the docking device. The upper end of the triangular arm, on the side farther from the arrow body, is connected to the fixed end of the telescopic mechanism through the tenth rotating shaft. The telescopic end of the telescopic mechanism is connected to the outer wall of the lifting mechanism through the eleventh rotating shaft. The space enclosed by the triangular arm, the lifting mechanism, and the telescopic mechanism forms a triangular structure.

9. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 8, characterized in that, The lifting mechanism is an electric cylinder structure. The output end of the electric cylinder structure is also provided with a plate and a locking block. The upper part of the plate is provided with a slot with two ends communicating. One side surface of the locking block is in close contact with the slot sidewall on the plate. The locking block is fixed to the plate by locking bolts. A scale mark is provided on the surface of the lifting mechanism along its axial direction and located at the output end; The lifting mechanism is also equipped with an anti-tilt device on the side near the arrow body. One end of the anti-tilt device is connected to the outer wall of the lifting mechanism, and the other end is fixed to the crossbeam on the support frame.

10. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 7, characterized in that, The second fixing device includes an electric cylinder assembly, a fixed base plate, a first rotating shaft, and a second rotating shaft. The telescopic end of the electric cylinder assembly is fixed to the side of the triangular arm away from the arrow body via the first rotating shaft. The fixed end of the electric cylinder assembly is connected to one side of the fixed base plate via the second rotating shaft. The other side of the fixed base plate is fixed to the inner frame sidewall of the support frame.

11. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 7, characterized in that, The docking device includes a docking plate, a rotating shaft, and a fixed sleeve. One end of the rotating shaft passes through the fixed sleeve and is fixedly connected to the docking plate, and the docking plate can rotate with the rotating shaft. The docking plate has a cube-shaped structure. The fixing sleeve includes an integrally formed upper sleeve body and a lower sleeve body. The two ends of the lower sleeve body are fixed to the plate by bolts. The upper part of the lower sleeve body is connected to the bottom of the upper sleeve body. The middle part of the upper sleeve body is provided with a hollow space for accommodating the rotating shaft. The top of the upper sleeve body is provided with a lifting lug.

12. The integrated horizontal transport, erection, and launch system for reusable liquid rockets according to claim 1, characterized in that, The launch pad includes a launch pad body, two sets of fixed arms, a twelfth rotating axis, and fixed connecting parts. The twelfth rotating axis is disposed on both sides of the launch pad body and fixedly connected to the launch pad body. The fixed arms are symmetrically disposed on the support frame. The twelfth rotating axis on both sides is respectively connected to the fixed arms that are close to each other, and the launch pad body can rotate with the twelfth rotating axis. The fixing connector is used to fix the launch pad body, wherein the top end of the fixing connector is connected to the surface of the launch pad body near the support frame, and the other end is fixed to the support frame.

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