Supporting device for rocket and transferring and erecting integrated launching vehicle

Abstract

The invention relates to the technical field of rockets, in particular to a supporting device for a rocket and a transferring and erecting integrated launching vehicle. The supporting device comprises an erecting arm body and a plurality of auxiliary supporting mechanisms. The auxiliary supporting mechanism comprises a supporting bracket, a disc spring force limiter and at least two linear guide rails. The pre-pressure of the disc spring force limiter is adjustable, so that the rigidity of the supporting bracket is matched with the rigidity of the rocket body; the linear guide rails are arranged on the two sides of the supporting bracket respectively. According to the supporting device for the rocket and the transferring and erecting integrated launching vehicle, the supporting bracket is kept to be in a balanced state through the linear guide rail, the floating function is achieved, and the clamping stagnation phenomenon is prevented; force limiting supporting is achieved by adjusting the pre-pressure of the disc spring force limiter, the rigidity of the supporting bracket is made to be close to the rigidity of a rocket body, and therefore it is guaranteed that the additional bending moment cross section load generated by the erecting arm to the rocket is within the allowable range.

Description

Technical Field

[0001] This invention relates to the field of rocket technology, and in particular to a support device and a launch vehicle that integrates transport and erection for rockets. Background Technology

[0002] In recent years, launch vehicles have increasingly adopted integrated transport and erection launch vehicles for rocket launches. This method typically features horizontal transport and horizontal tilting erection capabilities. Currently, with the increasing diversification of medium and large launch vehicles, these rockets usually have a large aspect ratio, meaning they are not only large in diameter and length but also have a significant weight load. Before the rocket is transported to launch, it is fixedly connected to the erector arm. Because the erector arm is a cantilever beam structure, during the transport process, uneven road surfaces cause bumps and vibrations, and the erector arm experiences extreme conditions during the moment of rocket erection, resulting in significant deformation. Since the erector arm has different stiffness than the rocket body, the deformation of the erector arm generates an additional bending moment on the rocket. Typically, as the additional bending moment increases, the pressure at the support points on the rocket's outer shell also gradually increases. Excessive pressure at the support points can lead to uneven radial stress, increasing the risk of damage to the rocket's outer shell.

[0003] Therefore, in order to prevent the above situation from occurring, it is urgent to solve the problem of launch vehicles being damaged due to large pressure or bending moment at the support points during transportation, erection and other operations. Summary of the Invention

[0004] This invention provides a support device for rockets and an integrated launch vehicle for transport and erection, in order to solve the defects in the prior art where rockets are damaged during transport and erection operations due to large pressure or bending moment at the support points.

[0005] This invention provides a support device for a rocket, comprising: The erecting arm body has a first mounting groove; Multiple auxiliary support mechanisms are arranged sequentially on the erecting arm body along its extension direction. Each auxiliary support mechanism includes: At least one support bracket, with a support surface on one side for supporting the rocket; The disc spring force limiter has one end located in the first mounting groove and the other end connected to the support bracket. The preload of the disc spring force limiter is adjustable so that the stiffness of the multiple support brackets matches the stiffness of the arrow body. At least two linear guide rails are provided, with at least one linear guide rail on each side of each support bracket, one end of which is connected to the erecting arm body and the other end of which is connected to the support bracket.

[0006] According to the support device for rockets provided by the present invention, the disc spring force limiter includes: A limiting seat is fixed on the first mounting groove, and the limiting seat has a limiting groove; The guide rod has a limiting boss, which engages with the limiting groove through one side of the limiting boss; A disc spring assembly is sleeved on the guide rod; A supporting base plate has a positioning hole, the guide rod is at least partially inserted into the positioning hole, and the disc spring assembly is located between the limiting boss on the other side and the supporting base plate; The adapter plate is connected to the limiting seat and the support bracket.

[0007] According to the support device for rockets provided by the present invention, the end of the guide rod away from the support bracket has an assembly hole; The disc spring force limiter also includes: An adjusting washer is located on the side of the support base plate away from the disc spring assembly; The preload is connected to the assembly hole and pressed against the support base plate through the adjusting washer.

[0008] According to the support device for rockets provided by the present invention, the auxiliary support mechanism further includes: An adjustment pad is placed between the adapter plate and the support bracket.

[0009] According to the rocket support device provided by the present invention, when the preload of the disc spring force limiter reaches the allowable pressure value, the lower end face of the limit seat is machined and ground by measuring the change value of the end face gap between the guide rod and the limit seat, and the thickness t is removed by grinding. The thickness of the adjusting shim is t; Satisfies: t=HS; Where t is the change in the end face gap between the guide rod and the limiting seat; H is the initial value of the end face gap between the guide rod and the limiting seat; and S is the end face gap between the guide rod and the limiting seat after the disc spring is compressed.

[0010] The rocket support device provided by the present invention further includes: The fixing base is fixed to the body of the erecting arm; The connecting seat is connected to both the fixed seat and the sliding end of the linear guide rail.

[0011] According to the support device for rockets provided by the present invention, the connecting seat has a first mounting surface and a second mounting surface that are perpendicular to each other, the first mounting surface is connected to the fixed seat, and the second mounting surface is connected to the sliding end of the linear guide rail.

[0012] According to the support device for rockets provided by the present invention, the support bracket has second mounting grooves on both sides, and the other end of the linear guide rail is disposed in the second mounting groove.

[0013] The rocket support device provided by the present invention further includes: Multiple fixed support brackets are alternately arranged on the erecting arm body along the extension direction of the erecting arm body and the auxiliary support mechanism; A tail bracket is located at one end of the erecting arm body; The clamping mechanism is located at the other end of the erecting arm body.

[0014] The present invention also provides an integrated transport and erection launch vehicle, comprising: a vehicle body; a support device for a rocket according to the present invention, disposed on the vehicle body; a transport platform, disposed on the vehicle body, the erection arm body being disposed on the transport platform; and a vehicle-mounted launch pad, disposed at one end of the transport platform.

[0015] This invention provides a support device for a rocket, comprising: an erecting arm body and multiple auxiliary support mechanisms. The erecting arm body has a first mounting groove; the multiple auxiliary support mechanisms are arranged sequentially on the erecting arm body along its extension direction. Each auxiliary support mechanism includes: at least one support bracket, a disc spring force limiter, and at least two linear guide rails. One side of the support bracket has a support surface for supporting the rocket; one end of the disc spring force limiter is located in the first mounting groove, and the other end is connected to the support bracket. The preload of the disc spring force limiter is adjustable to match the stiffness of the support bracket with the stiffness of the rocket body; at least one linear guide rail is provided on each side of each support bracket, with one end connected to the erecting arm body and the other end connected to the support bracket. The present invention provides a support device for rockets, which, by setting up linear guide rails and support brackets, can effectively reduce the pressure of the transport device on the rocket body when the rocket is subjected to bumps during transportation; by adjusting the preload of the disc spring force limiter to achieve force limiting support, the stiffness of the support bracket is made close to the stiffness of the rocket body, thereby avoiding damage caused by large bending moments of the rocket.

[0016] Furthermore, the present invention provides an integrated transport and erection launch vehicle, which has transport and erection functions, and since it includes the rocket support device in the above embodiments of the present invention, it also has the same advantages as described above. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in this invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of a support device for a rocket provided in one embodiment of the present invention.

[0019] Figure 2 This is an exploded view of the structure of a support device for a rocket provided in one embodiment of the present invention.

[0020] Figure 3 This is a partial cross-sectional view of a disc spring force limiter provided in one embodiment of the present invention.

[0021] Figure 4 yes Figure 3 A schematic diagram of the structure of part A in the middle.

[0022] Figure 5 This is an exploded view of the disc spring force limiter provided in one embodiment of the present invention.

[0023] Figure 6 This is a cross-sectional view of a disc spring force limiter provided in one embodiment of the present invention.

[0024] Figure 7 This is a schematic diagram of the structure of the limiting seat provided in one embodiment of the present invention.

[0025] Figure 8 This is a schematic diagram of the connecting seat and linear guide provided in one embodiment of the present invention.

[0026] Figure 9 This is a schematic diagram of the support bracket provided in one embodiment of the present invention.

[0027] Figure 10 This is a schematic diagram of the structure of the connector provided in one embodiment of the present invention.

[0028] Figure 11 This is a schematic diagram of the structure of the fixing base provided in one embodiment of the present invention.

[0029] Figure 12 This is a schematic diagram of the integrated transport and erection launch vehicle provided in one embodiment of the present invention.

[0030] Figure 13 This is a front view of the erecting arm provided in one embodiment of the present invention.

[0031] Figure 14 This is a top view of the erecting arm provided in one embodiment of the present invention.

[0032] Figure label: 1-Erecting arm; 2-Transfer platform; 3-Vehicle-mounted launch pad; 4-Rocket.

[0033] 11-Erecting arm body; 12-Fixed support bracket; 13-Auxiliary support mechanism; 14-Tail bracket; 15-Clamping mechanism; 131-Support bracket; 132-Disc spring force limiter; 133-Linear guide rail; 134-Connecting seat; 135-Fixed seat; 136-Adjusting pad; 1321-Limit seat; 1322-Guide rod; 1323-Disc spring assembly; 1324-Support base plate; 1325-Adapter plate; 1326-Adjusting washer; 1327-Pretensioner. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions of this invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without creative effort are within the scope of protection of this invention.

[0035] In the description of this embodiment, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this embodiment and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this embodiment.

[0036] 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 indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this embodiment, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0037] In this embodiment, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," "link," and "fix" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this embodiment based on the specific circumstances.

[0038] In embodiments of the present invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0039] Currently, there are two main approaches to designing the erecting boom to address related technical issues: The first approach involves strengthening the erecting boom structure, thereby controlling its deformation within acceptable limits by enhancing its structural rigidity. The second approach typically involves adding multiple support points to distribute and reduce pressure on the rocket. These multiple support points typically employ three or four main supports plus several auxiliary support mechanisms. The auxiliary supports are mostly implemented using hydraulic interconnection and electric lifting push rod control for lifting and adjusting.

[0040] Given the two approaches mentioned above, the first method, which involves reinforcing the erector arm structure, often results in a heavier and more complex erector arm. Increased weight leads to greater deformation, and the increased structural rigidity makes the entire transport, erection, and launch system larger, increasing manufacturing, operation, and development costs. The second approach, using a hydraulically connected and electrically operated pushrod-controlled lifting and adjustment mechanism, aims to ensure that the pressure exerted by the auxiliary support point on the rocket's outer shell does not exceed permissible surface pressure. This method often requires a complex control system that allows for real-time, free adjustment of the auxiliary support's lifting height and horizontal position within a certain range to achieve floating support. During the lifting and adjustment process, the pressure and bending moment exerted by the support point on the rocket's surface cannot be too high. If a malfunction occurs during the lifting process of any auxiliary support hydraulic cylinder or electric pushrod, the local pressure exerted by the auxiliary support on the rocket's outer shell will continuously increase, posing a risk of rocket damage.

[0041] Therefore, the present invention provides a support device for rockets to solve the problem of rockets being damaged during transport, erection and other operations due to large pressure or bending moment at the support point.

[0042] The following is combined Figures 1-14 This invention describes a support device for a rocket. The support device includes an erecting arm body 11 and a plurality of auxiliary support mechanisms 13.

[0043] The erecting arm body 11 has a first mounting groove; multiple auxiliary support mechanisms 13 are arranged sequentially on the erecting arm body 11 along its extension direction. The auxiliary support mechanisms 13 are installed on the crossbeam of the erecting arm body 11 and are important force-limiting bearing devices on the erecting arm 1. They directly bear the weight of the rocket 4 while limiting the radial degree of freedom, preventing the transport and erection integrated launch vehicle from bumping and vibrating during horizontal transport, and preventing excessive radial force on the load of the launch vehicle 4 under the extreme working condition of the erecting arm 1 during rocket erection, which would cause large surface pressure at the support position.

[0044] Each auxiliary support mechanism 13 includes: a support bracket 131, a disc spring force limiter 132, and at least two linear guide rails 133.

[0045] The support bracket 131 has a support surface on one side for supporting the rocket 4. One end of the disc spring force limiter 132 is located in the first mounting groove, and the other end is connected to the support bracket 131. The preload of the disc spring force limiter 132 is adjustable so that the stiffness of the support bracket 131 matches the stiffness of the rocket body. This auxiliary support mechanism 13 can adjust the stiffness of the preload of the disc spring force limiter 132 according to the size of the load supported at each fulcrum, so as to adapt to and match each support load.

[0046] Linear guide rails 133 are respectively disposed on both sides of the support bracket 131, with one end connected to the erecting arm body 11 and the other end connected to the support bracket 131. Preferably, the linear guide rails 133 are linear guide rails 133.

[0047] Specifically, the upper surface of the support bracket 131 is a support surface with an arc-shaped structure, used to mount and support the rocket 4. The lower surface is flat, and the left and right sides have flat mounting surfaces. The lower surface cooperates with the disc spring force limiter 132, and the left and right sides cooperate with the linear guide rail 133 respectively.

[0048] Linear guide rails 133 are installed symmetrically on both sides of the support bracket 131. The linear guide rails 133 extend along the height direction of the support bracket 131. The sliding connection between the linear guide rails 133 and the support bracket 131 enables the support bracket 131 to float up and down on both sides. That is, the linear guide rails 133 keep the support bracket 131 in a balanced state to achieve the floating function, preventing the support bracket 131 from getting stuck during the floating process under the action of axial load. The force limiting support is achieved by adjusting the preload of the disc spring force limiter 132, so that the stiffness of the support bracket 131 is close to that of the rocket body. This ensures that the additional bending moment section load generated by the erecting arm 1 on the rocket 4 is within the allowable range, and prevents the support force of the support bracket 131 on the rocket 4 from being too large or too small during the floating process. As can be seen, the linear guide rail 133 and the support bracket 131 can effectively reduce the pressure of the transport device on the rocket body when the rocket is subjected to bumps during transportation; the disc spring force limiter 132 can adjust its preload to make the stiffness of the support bracket 131 close to that of the rocket body, thereby avoiding damage caused by large bending moments of the rocket.

[0049] This invention provides a support device for a rocket, comprising: an erecting arm body 11 and a plurality of auxiliary support mechanisms 13. The erecting arm body 11 has a first mounting groove; the plurality of auxiliary support mechanisms 13 are arranged sequentially on the erecting arm body 11 along its extension direction. Each auxiliary support mechanism 13 includes: a support bracket 131, a disc spring force limiter 132, and at least two linear guide rails 133. The support bracket 131 has a support surface on one side for supporting the rocket 4; one end of the disc spring force limiter 132 is located in the first mounting groove, and the other end is connected to the support bracket 131. The preload of the disc spring force limiter 132 is adjustable to match the stiffness of the support bracket 131 with the stiffness of the rocket body; the linear guide rails 133 are respectively located on both sides of the support bracket 131, with one end connected to the erecting arm body 11 and the other end connected to the support bracket 131. The present invention provides a support device for a rocket, wherein linear guide rails 133 are installed symmetrically on both sides of the support bracket 131. The linear guide rails 133 keep the support bracket 131 in a balanced state to achieve a floating function, preventing the support bracket 131 from getting stuck during floating under axial load during the erection process. The preload of the disc spring force limiter 132 is adjusted to achieve force-limiting support, so that the stiffness of the support bracket 131 is close to that of the rocket body, thereby ensuring that the additional bending moment section load generated by the erecting arm 1 on the rocket 4 is within the allowable range, and preventing the support force of the support bracket 131 on the rocket 4 from being too large or too small during the floating process.

[0050] In one embodiment of the present invention, the disc spring force limiter 132 includes: a limiting seat 1321, a movable guide rod, a disc spring assembly 1323, a support base plate 1324, and an adapter plate 1325. The limiting seat 1321 is fixed to a first mounting groove and has a limiting groove; the guide rod 1322 has a limiting boss, which engages with the limiting groove on one side; the disc spring assembly 1323 is sleeved on the guide rod 1322; the support base plate 1324 has a positioning hole, into which at least part of the guide rod 1322 is inserted, and the disc spring assembly 1323 is located between the other side of the limiting boss and the support base plate 1324; the adapter plate 1325 is connected to the limiting seat 1321 and the support bracket 131. Specifically, the limiting seat 1321 is fixedly connected to the end face of the first mounting groove by bolts; the engagement of the limiting groove and the limiting boss provides a height limiting function in the axial direction and a guiding function in the radial direction. The upper end of the guide rod 1322 is fixedly connected to the adapter plate 1325 by bolts. The adapter plate 1325 is connected to the lower surface of the support bracket 131 by the adjusting pad 136. The lower end of the guide rod 1322 is inserted into the positioning hole. The guide rod 1322 achieves its guiding function through the above connection method.

[0051] In the above embodiment, the height of the first support seat is limited by the limiting seat 1321 to prevent the lowest position of the support seat 131 from being higher than the lowest position of other fixed support seats 12 after the disc spring resets; the guide rod 1322 plays a guiding role to prevent the disc spring from moving during elastic compression reset and to prevent the disc spring from getting stuck during compression or reset; the disc spring assembly 1323 provides elastic force to the guide rod 1322. Secondly, the redundant guidance of the linear guide rail 133 and the guide rod 1322 improves the reliability of the adaptive lifting adjustment of the auxiliary support mechanism 13. In addition, this auxiliary support mechanism 13 replaces the hydraulic and electric lifting push rod auxiliary supports with a mechanical structure, reducing development costs, avoiding electrical or hydraulic failures during floating adjustment, and making safety risks controllable.

[0052] In one embodiment of the present invention, the end of the guide rod 1322 away from the support bracket 131 has a mounting hole. The disc spring force limiter 132 further includes: an adjusting washer 1326 and a preload member 1327. The adjusting washer 1326 is located on the side of the support base plate 1324 away from the disc spring assembly 1323; the preload member 1327 is connected to the mounting hole and is pressed against the support base plate 1324 through the adjusting washer 1326. Preferably, the preload member 1327 can be a preload bolt, the mounting hole is a bolt hole, the preload bolt passes through the adjusting washer 1326 and is gradually tightened from the mounting hole, pressing the guide rod 1322 against the support base plate 1324 through the adjusting washer 1326. In this embodiment, the range of support load on the erecting arm 1 is extracted based on the calculated deformation of the erecting arm 1. The preload of the disc spring limiter 132 is adjusted according to the load value. The preload bolt is rotated using a torque wrench, and the guide rod 1322 generates preload through the compression of the disc spring. The magnitude of the disc spring preload is calculated using a torque wrench.

[0053] In one embodiment of the present invention, the auxiliary support mechanism 13 further includes: an adjustment pad 136, which is disposed between the adapter plate 1325 and the support bracket 131, and the height of the support bracket 131 is compensated by adjusting the pad 136 to ensure its installation accuracy.

[0054] In one embodiment of the present invention, after the preload of the disc spring force limiter 132 reaches the allowable pressure value, the lower end face of the limit seat 1321 is machined and ground by measuring the change in the end face gap between the guide rod 1322 and the limit seat 1321, and the thickness t is removed by grinding. The thickness of the adjusting shim 136 is t. The following condition is satisfied: t = HS; where t is the change in the end face gap between the guide rod 1322 and the limit seat 1321; H is the initial value of the end face gap between the guide rod 1322 and the limit seat 1321; and S is the end face gap between the guide rod 1322 and the limit seat 1321 after the disc spring is compressed.

[0055] In the above embodiment, the pre-pressure range of the disc spring force limiter 132 is detected to be within the allowable range, and the pressure value corresponding to each 1mm compression change is recorded. A shim can be added inside the disc spring force limiter 132 to adjust the pre-pressure, so that the stiffness of the support bracket 131 is close to that of the arrow body. In order to ensure that the lowest point of the support bracket 131 and other fixed support brackets 12 are always at the same level after the support bracket 131 is reset, the thickness t of the lower end face of the limit seat 1321 is measured and a thickness t adjustment shim 136 is added between the support bracket 131 and the disc spring force limiter 132 to ensure its installation accuracy.

[0056] In one embodiment of the invention, the support device for the rocket further includes a fixed base 135 and a connecting base 134. The fixed base 135 is fixed to the erecting arm body 11; the connecting base 134 is connected to the fixed base 135 and the sliding end of the linear guide rail 133, respectively.

[0057] In the above embodiment, the fixing base 135 consists of a base body and multiple reinforcing plates. The base body is an integral structure consisting of a base plate, a top plate, and a vertical plate connected together. The base plate is fixed to the upper surface of the erecting arm body 11 by bolts, and the top plate is fixed to the connecting base 134 by bolts. Two reinforcing plates are connected between the base plate, the top plate, and the vertical plate; two other reinforcing plates are located on the opposite side and connected between the base plate and the vertical plate, thereby enhancing the structural stability of the fixing base 135.

[0058] In one embodiment of the present invention, the connecting seat 134 has a first mounting surface and a second mounting surface that are perpendicular to each other. The first mounting surface is connected to the fixed seat 135, and the second mounting surface is connected to the sliding end of the linear guide rail 133. Specifically, the first mounting surface and the second mounting surface are an integral structure; the first mounting surface is a flat surface and is fixedly connected to the top plate by bolts, and the second mounting surface is a vertical surface, the outer surface of which is used to connect to the linear guide rail 133.

[0059] In one embodiment of the present invention, the support bracket 131 has second mounting grooves on both sides, and the other end of the linear guide rail 133 is disposed in the second mounting groove. Preferably, the second mounting groove is a rectangular groove, and a portion of the linear guide rail 133 can be embedded in the rectangular groove and fixed with bolts, while the other portion of the linear guide rail 133 is fixed to the second mounting surface of the connecting seat 134 with bolts.

[0060] In one embodiment of the present invention, the support device for the rocket further includes: a plurality of fixed support brackets 12, a tail bracket 14, and a clamping mechanism 15. The plurality of fixed support brackets 12 are alternately arranged on the erecting arm body 11 along the extending direction of the erecting arm body 11, and alternately with the auxiliary support mechanism 13; the tail bracket 14 is located at one end of the erecting arm body 11; and the clamping mechanism 15 is located at the other end of the erecting arm body 11. Specifically, the fixed support brackets 12 and the auxiliary support mechanism 13 are alternately arranged to balance floating and support effects; the tail bracket 14 is located at the tail of the erecting arm body 11 and is used to support the tail end of the rocket 4; the clamping mechanism 15 is located at the head of the erecting arm body 11 and is used to hold and clamp the head of the rocket 4.

[0061] Preferably, polyurethane rubber pads are attached to the fixed support bracket 12 and the support bracket 131 to provide cushioning and protection for the rocket 4.

[0062] The present invention also provides an integrated transport and erection launch vehicle. This integrated transport and erection launch vehicle includes: a vehicle body, an erection arm 1, a transport platform 2, and a vehicle-mounted launch pad 3. The erection arm 1 includes: a support device for the rocket (i.e., the erection arm body 11 and multiple auxiliary support mechanisms 13), a fixed support bracket 12, a tail bracket 14, and a clamping mechanism 15, etc. The transport platform 2 is mounted on the vehicle body, and the erection arm body 11 is mounted on the transport platform 2; the vehicle-mounted launch pad 3 is located at one end of the transport platform 2.

[0063] Specifically, the transfer platform 2 is mounted on the vehicle body. The erecting arm 1 includes: an erecting arm body 11, multiple auxiliary support mechanisms 13, a fixed support bracket 12, a tail bracket 14, and a clamping mechanism 15, etc. The erecting arm body 11 and the vehicle-mounted launch pad 3 are both mounted on the transfer platform 2. The vehicle-mounted launch pad 3 is mounted at the rear end of the transfer platform 2. The rocket 4 is mounted on the erecting arm 1 and supported by the support bracket 131 and the fixed support bracket 12. The support bracket 131 is a floating bracket, while the fixed support bracket 12 is a non-floating bracket.

[0064] The present invention provides an integrated transport and erection launch vehicle, which has transport and erection functions, and, since it includes the rocket support device in the above embodiments of the present invention, it also has the same advantages as described above.

[0065] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs. Those skilled in the art can understand and implement this without any creative effort.

[0066] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A support device for a rocket, characterized in that, include: The erecting arm body (11) has a first mounting groove; Multiple auxiliary support mechanisms (13) are arranged sequentially on the erecting arm body (11) along the extension direction of the erecting arm body (11). Each auxiliary support mechanism (13) includes: At least one support bracket (131) has a support surface on one side for supporting the rocket; The disc spring force limiter (132) has one end located in the first mounting groove and the other end connected to the support bracket (131). The preload of the disc spring force limiter (132) is adjustable so that the stiffness of the multiple support brackets (131) matches the stiffness of the arrow body. At least two linear guide rails (133) are provided on both sides of each of the support brackets (131), and one end of the linear guide rail (133) is connected to the erecting arm body (11), and the other end is connected to the support bracket (131).

2. The support device for a rocket according to claim 1, characterized in that, The disc spring force limiter (132) includes: A limiting seat (1321) is fixed on the first mounting groove, and the limiting seat (1321) has a limiting groove; The guide rod (1322) has a limiting boss, which is engaged with the limiting groove through one side of the limiting boss; Disc spring assembly (1323) is sleeved on the guide rod (1322). The support base plate (1324) has a positioning hole, the guide rod (1322) is at least partially inserted into the positioning hole, and the disc spring assembly (1323) is located between the other side of the limiting boss and the support base plate (1324). The adapter plate (1325) is connected to the limiting seat (1321) and the support bracket (131).

3. The support device for a rocket according to claim 2, characterized in that, The guide rod (1322) has an assembly hole at one end away from the support bracket (131); The disc spring force limiter (132) also includes: An adjusting washer (1326) is provided on the side of the support base plate (1324) away from the disc spring assembly (1323); The preload (1327) is connected to the assembly hole and is pressed against the support base plate (1324) by the adjusting washer (1326).

4. The support device for a rocket according to claim 2, characterized in that, The auxiliary support mechanism (13) also includes: An adjusting pad (136) is provided between the adapter plate (1325) and the support bracket (131).

5. The support device for a rocket according to claim 4, characterized in that, When the preload of the disc spring force limiter (132) reaches the allowable pressure value, the lower end face of the limit seat (1321) is machined and ground by measuring the change value of the end face gap between the guide rod (1322) and the limit seat (1321), and the thickness t is removed by grinding. The thickness of the adjusting shim (136) is t; Satisfies: t=HS; Where t is the change value of the end face gap between the guide rod (1322) and the limiting seat (1321); H is the initial value of the end face gap between the guide rod (1322) and the limiting seat (1321); and S is the end face gap between the guide rod (1322) and the limiting seat (1321) after the disc spring is compressed.

6. The support device for a rocket according to claim 1, characterized in that, Also includes: A fixing seat (135) is fixed on the erecting arm body (11); The connecting seat (134) is connected to the sliding end of the fixed seat (135) and the linear guide (133), respectively.

7. The support device for a rocket according to claim 6, characterized in that, The connecting seat (134) has a first mounting surface and a second mounting surface that are perpendicular to each other. The first mounting surface is connected to the fixed seat (135), and the second mounting surface is connected to the sliding end of the linear guide (133).

8. The support device for a rocket according to claim 1, characterized in that, The support bracket (131) has second mounting grooves on both sides, and the other end of the linear guide rail (133) is located in the second mounting groove.

9. The support device for a rocket according to claim 1, characterized in that, Also includes: Multiple fixed support brackets (12) are alternately arranged on the erecting arm body (11) along the extension direction of the erecting arm body (11) and the auxiliary support mechanism (13); Tail bracket (14) is located at one end of the erecting arm body (11); The clamping mechanism (15) is located at the other end of the erecting arm body (11).

10. A launch vehicle integrating transfer and erection, characterized in that, include: Vehicle body; The support device for the rocket as described in any one of claims 1 to 9 is disposed on the vehicle body; The transfer platform (2) is mounted on the vehicle body, and the erecting arm body (11) is mounted on the transfer platform (2); The vehicle-mounted launcher (3) is located at one end of the transfer platform (2).

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