Support device for rocket transportation and method of using the same

Abstract

The present invention discloses a support device for rocket transportation and a method for using the same, belonging to the technical field of rocket transportation. The device comprises a support base and an arrow-supporting mechanism, wherein a nitrogen spring mechanism is provided between the support base and the arrow-supporting mechanism, wherein both ends of the nitrogen spring mechanism are respectively connected to the support base and the arrow-supporting mechanism, and wherein the nitrogen spring mechanism comprises a nitrogen spring body and a nitrogen spring housing, wherein the nitrogen spring body is disposed within the nitrogen spring housing, and a locking assembly is provided on one side of the nitrogen spring housing, wherein the locking assembly is connected to the nitrogen spring body, and the position of the nitrogen spring body is locked by the locking assembly. The present invention has a transport support capable of switching between elasticity and rigidity, and can provide cushioning in an elastic mode and stable support in a rigid mode, thereby ensuring the secure fixation of the rocket body. According to the characteristics of rocket transportation, the actual use of elastic and rigid support switching improves the stability of rocket transportation while greatly improving the safety of the rocket during transportation.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket transportation, and in particular to a supporting device for rocket transportation and a method for using the same. Background Art

[0002] Currently, during rocket transportation, the rocket body requires a reliable support structure to prevent structural damage caused by the rocket body's axial acceleration during transportation. However, the support locations of the rocket body may vary significantly depending on the rocket model and under different transportation conditions. If the support location is located at a weak point in the rocket body structure, an overly rigid support structure may cause excessive localized stress, thereby causing structural damage to the rocket body. Therefore, in some cases, elastic support is required. The stiffness of the auxiliary support is designed according to the load and stiffness range provided by the rocket designer to accommodate the deformation of the rocket body and improve the safety of the rocket body structure. When the support location of the rocket body is relatively strong, rigid support can be directly used. In this case, the auxiliary support structure does not need to provide additional elastic deformation. The load at the support location is within the load limit provided by the rocket designer to ensure that the rocket body remains stable and undamaged during transportation.

[0003] For related technology, please refer to the locking device for nitrogen spring with application number 201921028041.6.

[0004] Regarding the above-mentioned related technologies, the applicant found that the transportation support device for the rocket requires multiple mechanical equipment to work together and has a relatively complex structure. Among them, the nitrogen spring can achieve elastic support for the rocket transportation. However, since the stiffness adjustment of the nitrogen spring depends on the gas pressure, temperature changes may cause pressure fluctuations, thereby affecting the support effect. In addition, there are limitations on the operating temperature of the nitrogen spring. When the temperature is too high or too low, the stiffness adjustment of the nitrogen spring may fail, thereby causing instability in the rocket transportation and reducing safety during transportation. Summary of the Invention

[0005] In response to the deficiencies in the prior art, the present invention provides a support device for rocket transportation and a method for using the same, which can realize transport support that can be switched between elastic and rigid. It can provide buffering in the elastic mode to adapt to the deformation of the rocket, and provide stable support in the rigid mode to ensure the firm fixation of the rocket body. According to the characteristics of rocket transportation, the actual use of elastic and rigid support switching can improve the stability of rocket transportation while greatly improving the safety of the rocket during transportation.

[0006] The technical solution of the present invention to solve the above technical problems is as follows:

[0007] A support device for rocket transportation includes a support base and an arrow-supporting mechanism. A nitrogen spring mechanism is provided between the support base and the arrow-supporting mechanism. The two ends of the nitrogen spring mechanism are respectively connected to the support base and the arrow-supporting mechanism. The nitrogen spring mechanism includes a nitrogen spring body and a nitrogen spring shell. The nitrogen spring body is placed in the nitrogen spring shell. A locking assembly is provided on one side of the nitrogen spring shell. The locking assembly is connected to the nitrogen spring body, and the nitrogen spring body is locked in position by the locking assembly.

[0008] Furthermore, the locking assembly includes a fixed block and a connecting block. A locking groove that penetrates the nitrogen spring housing is opened on the nitrogen spring housing. The locking groove is arranged along the telescopic direction of the nitrogen spring body. Two fixed blocks are respectively arranged at both ends of the locking groove. A limiting rod is provided between the fixed blocks. The length direction of the limiting rod is consistent with the telescopic direction of the nitrogen spring body. The connecting block is placed in the locking groove. The connecting block is slidably connected to the limiting rod. The side of the connecting block away from the limiting rod is fixedly connected to the nitrogen spring body. A locking nut is threadedly connected to the limiting rod, and the two locking nuts are respectively placed on both sides of the connecting block.

[0009] Furthermore, the arrow supporting mechanism includes an arrow supporting seat and an arrow supporting adjustment plate. The arrow supporting adjustment plate is movably connected to the arrow supporting seat, and the side of the arrow supporting seat away from the arrow supporting adjustment plate is arranged in an arc surface.

[0010] Furthermore, a longitudinal adjustment rod is provided on the arrow support adjustment plate, which passes through the arrow support seat and is slidably connected to the arrow support seat. A longitudinal locking nut is threaded on the longitudinal adjustment rod, and two longitudinal locking nuts are respectively placed on both sides of the arrow support seat.

[0011] Furthermore, a transverse adjustment rod is provided on the arrow support adjustment plate, which passes through the arrow support seat and is slidably connected to the arrow support seat. A transverse locking nut is threadedly connected to the transverse adjustment rod, and two transverse locking nuts are respectively placed on both sides of the arrow support seat.

[0012] Furthermore, a spiral elevator is provided above the support base, and the spiral elevator is placed between the nitrogen spring mechanism and the support base. The lifting direction of the spiral elevator is consistent with the extension and contraction direction of the nitrogen spring mechanism.

[0013] Furthermore, a pressure sensor is provided below the arrow-supporting mechanism, and the pressure sensor is placed between the nitrogen spring mechanism and the arrow-supporting mechanism.

[0014] Furthermore, a guide column mechanism is provided above the support base, and the guide column mechanism includes an upper guide column and a lower guide column. The lower guide column is connected to the support base, and the upper guide column is connected to the arrow-supporting mechanism. The upper guide column and the lower guide column are sleeved with each other and slidably connected. The sliding direction of the upper guide column and the lower guide column is consistent with the extension and contraction direction of the nitrogen spring mechanism.

[0015] A method for using support equipment for rocket transportation,

[0016] First, select the elastic or rigid mode according to the needs of rocket transportation. If the elastic mode is selected, the locking component is not used to put the nitrogen spring mechanism in the working state. If the rigid mode is selected, the locking component is used to lock the nitrogen spring mechanism and put it in the non-working state.

[0017] Then it is hoisted to the designated position for rocket transportation, and docked with the rocket support point through the arrow-supporting mechanism. If the elastic mode is selected, the contact between the arrow-supporting mechanism and the rocket is adjusted vertically through the spiral elevator, and the rising height of the spiral elevator is controlled by the pressure value fed back by the pressure sensor. When the feedback value of the pressure sensor reaches the initial working pressure provided by the rocket designer, the spiral elevator is in place and locked. Under subsequent transportation conditions, the deformation of the rocket at the supporting position is adapted to by the compression or extension of the nitrogen spring mechanism. If the rigid mode is selected, the nitrogen spring mechanism is locked first, and the spiral elevator rises to the theoretical design height under the control of the motor and is locked, so that the nitrogen spring mechanism is in a non-working state.

[0018] Finally, all actions are completed before the rocket is in place, providing support during the rocket transportation process.

[0019] Furthermore, according to the requirements of rocket transportation, the corresponding elastic or rigid support mode is selected:

[0020] According to the structural strength of the rocket body support position, if the strength is weak, the elastic support mode needs to be adopted. At this time, the locking assembly is released and the nitrogen spring body is in the working state. At this time, the nitrogen spring body provides elastic support;

[0021] Judging by the structural strength of the rocket's body support position, if the strength is strong, a rigid support mode needs to be adopted. At this time, the locking assembly is locked and the nitrogen spring body is in a non-working state. At this time, the locking assembly provides stable rigid support.

[0022] In summary, compared with the prior art, the above technical solution has the following beneficial effects:

[0023] (1) The transport support can realize the switch between elasticity and rigidity, which can provide buffering in elastic mode to adapt to the deformation of the rocket, and provide stable support in rigid mode to ensure the stable fixation of the rocket body. According to the characteristics of rocket transportation, the actual use of elastic and rigid support switching can improve the stability of rocket transportation and greatly improve the safety of the rocket during transportation.

[0024] (2) Through the switchable design of elasticity and rigidity, the usage mode can be adjusted according to the strength and deformation requirements of the rocket support point, avoiding damage to the rocket structure due to excessive support force, improving the overall transportation safety, and selecting the elastic support mode. The nitrogen spring can provide buffering capacity within the load variation range of the support position, effectively absorbing the impact and vibration that may occur during transportation, and reducing damage to the rocket body. The nitrogen spring has low cost and simple structure. Compared with the hydraulic support system, it does not require complex pipeline control, which reduces maintenance and replacement costs;

[0025] (3) Dynamic optimization capability during transportation. For example, if the elastic mode is selected, the system can adapt the deformation of the rocket by adjusting the stiffness of the nitrogen spring according to road vibration, acceleration, deceleration, etc., thereby reducing transportation shock.

[0026] (4) The position of the arrow support seat is adjusted through the arrow support adjustment plate. By adjusting the position, the docking error is eliminated and the instability factors during the rocket transportation process are reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a main diagram of the overall structure of an embodiment of the present invention;

[0028] Figure 2 A side view of the overall structure of an embodiment of the present invention;

[0029] Figure 3 A top view of the overall structure of an embodiment of the present invention;

[0030] Figure 4 for Figure 1 A partial enlarged view of part A.

[0031] Explanation of the accompanying drawings: 1. Support base; 2. Screw elevator; 3. Nitrogen spring mechanism; 31. Nitrogen spring body; 32. Nitrogen spring housing; 321. Locking groove; 33. Locking assembly; 331. Fixing block; 332. Connecting block; 333. Limiting rod; 334. Locking nut; 4. Pressure sensor; 5. Arrow supporting mechanism; 51. Arrow supporting seat; 52. Arrow supporting adjustment plate; 53. Longitudinal adjustment rod; 54. Longitudinal locking nut; 6. Guide column mechanism; 61. Upper guide column; 62. Lower guide column. DETAILED DESCRIPTION

[0032] The principles and features of the present invention are described below in conjunction with all the accompanying drawings. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.

[0033] An embodiment of the present invention discloses a supporting device for rocket transportation and a method for using the same.

[0034] During rocket transportation, the rocket body requires a reliable support structure to prevent structural damage caused by the body's various accelerations during transport. However, the location of support structures can vary significantly between different rocket models and under different transportation conditions. If the support is located at a weak point in the rocket body structure, an overly rigid support structure may cause excessive localized stress, resulting in structural damage to the rocket body. Therefore, in some cases, elastic support is required. The stiffness of the auxiliary support is designed based on the load and stiffness ranges provided by the rocket designer to accommodate the deformation of the rocket body and improve the safety of the rocket body structure.

[0035] When the strength of the rocket body support position is high, rigid support can be used directly. At this time, the support structure does not need to provide additional elastic deformation. The support position load is within the load limit provided by the rocket designer to ensure that the rocket body remains stable and undamaged during transportation.

[0036] An auxiliary support structure that can achieve switching between elasticity and rigidity is designed. The support structure can provide buffering in the elastic mode to adapt to the deformation of the rocket, and provide stable support in the rigid mode to ensure the firm fixation of the rocket body.

[0037] Due to the characteristics of rocket transportation, the elastic structure needs to have sufficient travel under small load changes. After investigation, it was found that nitrogen springs have this characteristic. The support structure is rigidly supported by the studs and nuts on the nitrogen spring device.

[0038] Reference Figure 1 and Figure 2 A support device for rocket transport includes a support base 1 and an arrow-carrying mechanism 5. The support base 1 is constructed of steel and can be adjusted to accommodate interfaces on different transport platforms. A nitrogen spring mechanism 3 is installed between the support base 1 and the arrow-carrying mechanism 5. The nitrogen spring mechanism 3 is connected to the support base 1 and the arrow-carrying mechanism 5 at both ends. When in use, the nitrogen spring mechanism 3 is positioned vertically, which can be used as a reference for the Z-axis coordinate setting.

[0039] A screw jack 2 is installed above the support base 1, positioned between the nitrogen spring mechanism 3 and the support base 1. Its lifting direction aligns with the expansion and contraction direction of the nitrogen spring mechanism 3. Screw jack 2 is used to adjust the height of the support assembly. Located at the base of the nitrogen spring mechanism 3, it adjusts the lifting height to ensure vertical adaptation to various rocket transport conditions. Screw jack 2 is fixed to the support base 1, and its upper flange connects to the nitrogen spring mechanism 3, housing the latter.

[0040] Reference Figure 1 and Figure 3A pressure sensor 4 is provided below the arrow-supporting mechanism 5, and the pressure sensor 4 is placed between the nitrogen spring mechanism 3 and the arrow-supporting mechanism 5. The pressure sensor 4 is used to monitor the support load, monitor the actual force conditions at the support position, and feed the data back to the control system to ensure that the rocket support point load is consistent with the design value. An interface compatible with the pressure sensor 4 is reserved at the upper end of the nitrogen spring mechanism 3, and the pressure sensor 4 is connected to the arrow-supporting mechanism 5 through a joint bearing. The corresponding model equipment of the screw elevator 2 and the pressure sensor 4 is selected according to the upper limit of the static load.

[0041] Reference Figure 1 and Figure 2 A guide column mechanism 6 is provided above the support base 1. The guide column mechanisms 6 are symmetrically arranged on either side of the nitrogen spring mechanism 3. The arrow-carrying mechanism 5 is installed in conjunction with the guide column structure. The guide column mechanism 6 includes an upper guide column 61 and a lower guide column 62. The lower guide column 62 is connected to the support base 1, and the upper guide column 61 is connected to the arrow-carrying mechanism 5. The upper guide column 61 and the lower guide column 62 are mutually sleeved and slidably connected. The sliding direction of the upper guide column 61 and the lower guide column 62 is consistent with the expansion and contraction direction of the nitrogen spring mechanism 3. The guide column mechanism 6 is connected to the arrow-carrying mechanism 5 and mainly bears lateral loads. The upper guide column 61 and the lower guide column 62 are made of high-strength steel to ensure structural strength.

[0042] Reference Figure 1 and Figure 4 The nitrogen spring mechanism 3 includes a nitrogen spring body 31 and a nitrogen spring housing 32. The nitrogen spring body 31 is placed within the nitrogen spring housing 32 and is used to provide adjustable elastic support. The nitrogen spring body 31, placed within the nitrogen spring housing 32, serves as a core buffer element, providing support in elastic mode to accommodate rocket deformation. The stiffness of the nitrogen spring body 31 is calculated based on the load range and deformation size provided by the rocket, and the corresponding model equipment is selected.

[0043] A locking assembly 33 is provided on one side of the nitrogen spring housing 32 . The locking assembly 33 is connected to the nitrogen spring body 31 . The nitrogen spring body 31 is locked in position by the locking assembly 33 .

[0044] The locking assembly 33 includes a fixing block 331 and a connecting block 332. A locking groove 321 is formed on the nitrogen spring housing 32 and penetrates the nitrogen spring housing 32. The locking groove 321 is arranged along the extension and contraction direction of the nitrogen spring body 31. Two fixing blocks 331 are respectively arranged at both ends of the locking groove 321. A limiting rod 333 is provided between the fixing blocks 331. The length direction of the limiting rod 333 is consistent with the extension and contraction direction of the nitrogen spring body 31. The connecting block 332 is placed in the locking groove 321. The connecting block 332 is slidably connected to the limiting rod 333. The side of the connecting block 332 away from the limiting rod 333 is fixedly connected to the nitrogen spring body 31. A locking nut 334 is threadedly connected to the limiting rod 333. The two locking nuts 334 are respectively placed on both sides of the connecting block 332.

[0045] The locking assembly 33 realizes the switching between the elastic and rigid modes by setting a locking nut 334 and then tightening or loosening the locking nut 334 and the connecting block 332 to realize the switching of the support mode. When the locking nut 334 locks the connecting block 332, the nitrogen spring body 31 is constrained, so that the support structure is in a rigid support state.

[0046] When the locking nut 334 and the connecting block 332 are in a non-locking state, the nitrogen spring body 31 is released, so that the supporting structure provides elastic buffering, and the supporting structure is in an elastic supporting state.

[0047] Reference Figure 1 and Figure 3 The arrow-supporting mechanism 5 includes an arrow-supporting seat 51 and an arrow-supporting adjustment plate 52, which are movably connected to the arrow-supporting seat 51. The side of the arrow-supporting seat 51, which is away from the arrow-supporting adjustment plate 52, is configured as an arc surface. The arrow-supporting seat 51 is configured as an arc surface that directly contacts the rocket body. Its position can be adjusted via threaded adjustment to accommodate the position requirements of different rocket support points, evenly transmitting support force to the rocket body. By changing the contact position of the support surface, the arrow body is better protected. The arrow-supporting seat 51 is constructed of high-strength steel to ensure structural strength.

[0048] The arrow-supporting adjustment plate 52 can be moved along the X-axis or the Y-axis alone, or can be arranged in combination and move along the X-axis and the Y-axis in combination.

[0049] If moving on the X-axis, a longitudinal adjustment rod 53 is provided on the arrow supporting adjustment plate 52. The longitudinal adjustment rod 53 passes through the arrow supporting seat 51 and is slidably connected to the arrow supporting seat 51. A longitudinal locking nut 54 is threadedly connected to the longitudinal adjustment rod 53. Two longitudinal locking nuts 54 are respectively placed on both sides of the arrow supporting seat 51.

[0050] If moving on the Y-axis, a transverse adjustment rod is provided on the arrow supporting adjustment plate 52, which passes through the arrow supporting seat 51 and is slidingly connected to the arrow supporting seat 51. A transverse locking nut is threadedly connected to the transverse adjustment rod, and two transverse locking nuts are respectively placed on both sides of the arrow supporting seat 51.

[0051] The above embodiment proposes a nitrogen spring support structure that can freely switch between elasticity and rigidity, which is used to provide reliable support during rocket transportation and ensure the safety of the rocket body under different transportation conditions. The elastic support provided by the nitrogen spring meets the needs of rocket bodies with relatively weak support position structures, and the rigid support can be achieved through the locking assembly on the nitrogen spring mechanism 3 to adapt to rocket bodies with strong support position strength and no elasticity requirements. The arrow support mechanism 5 adopts a threaded position adjustment method, combined with the selection of a pressure sensor 4 to monitor the support position load, and adapts the nitrogen spring of corresponding stiffness according to the requirements of the rocket party. The spiral elevator 2 is selected according to the load upper limit to achieve stable support during the rocket transportation process.

[0052] The transport support can realize switching between elasticity and rigidity. It can provide buffering in elastic mode to adapt to the deformation of the rocket, and provide stable support in rigid mode to ensure the firm fixation of the rocket body. According to the characteristics of rocket transportation, the actual use of elastic and rigid support switching can improve the stability of rocket transportation while greatly improving the safety of the rocket during transportation.

[0053] Through the switchable design of elasticity and rigidity, the usage mode can be adjusted according to the strength and deformation requirements of the rocket support point to avoid damage to the rocket structure due to excessive support force and improve overall transportation safety. By selecting the elastic support mode, the nitrogen spring can provide buffering capacity within the load variation range of the support position, effectively absorbing the impact and vibration that may be generated during transportation, and reducing damage to the rocket body. The nitrogen spring has low cost and simple structure. Compared with the hydraulic support system, it does not require complex pipeline control, which reduces maintenance and replacement costs.

[0054] Dynamic optimization capabilities during transportation. For example, in elastic mode, the system can adapt the stiffness of the nitrogen spring to the rocket's deformation according to road vibration, acceleration, and deceleration during transportation, reducing transportation shock. The position of the arrow support 51 can be adjusted using the arrow support adjustment plate 52. This adjustment eliminates docking errors and reduces instability during rocket transportation.

[0055] The implementation principle of a support device for rocket transportation according to an embodiment of the present invention is as follows:

[0056] First, install the support structure, fix the lower half of the lower guide column 62 and the screw elevator 2 on the support base 1, then install the nitrogen spring housing 32, the nitrogen spring body 31 and the pressure sensor 4, and finally connect the arrow support seat 51 and the upper guide column 61.

[0057] After the initial installation of the support structure itself is complete, the operating mode is selected according to the design requirements. If the elastic mode is selected, the nitrogen spring locking assembly 33 is not installed, and the nitrogen spring is in an operational state. If the rigid mode is selected, the locking assembly 33 is installed to lock the nitrogen spring body 31, making it inoperative. The support position load is determined by the deformation of the arrow body, and its upper limit matches the screw jack 2.

[0058] After the support structure itself is installed, it is hoisted to the designated position of the rocket transport platform. The position of the arrow support seat 51 on the arrow support adjustment plate 52 is adjusted by adjusting the longitudinal thread or the transverse thread on the arrow support seat 51 to ensure that the arrow support seat 51 is fully docked with the theoretical rocket body support point.

[0059] If elastic support is used, the contact between the arrow support seat 51 and the rocket body is adjusted vertically through the spiral elevator 2, and the rising height of the spiral elevator 2 is controlled by the pressure value fed back by the pressure sensor 4. When the feedback value of the pressure sensor 4 reaches the initial working pressure provided by the rocket designer, the spiral elevator 2 is in place and locked. Under subsequent transportation conditions, the nitrogen spring body 31 is compressed or extended to adapt to the deformation of the rocket body in the support position.

[0060] If rigid support is used, the nitrogen spring body 31 is locked first, and the spiral elevator 2 rises to the theoretical design height and is locked under the control of the motor. All actions are completed before the rocket is in place. During the transportation of the rocket, the auxiliary support structure provides rigid support, and the nitrogen spring body 31 does not work.

[0061] A method for using support equipment for rocket transportation. First, an elastic or rigid mode is selected according to the needs of rocket transportation. If the elastic mode is selected, the locking assembly is not used, so that the nitrogen spring mechanism 3 is in a working state. If the rigid mode is selected, the locking assembly is used to lock the nitrogen spring mechanism 3, so that the nitrogen spring mechanism 3 is in a non-working state.

[0062] It is then hoisted to the designated position for rocket transportation and docked with the rocket support point through the arrow-supporting mechanism 5. If the elastic mode is selected, the contact between the arrow-supporting mechanism 5 and the rocket is adjusted vertically through the spiral elevator 2, and the rising height of the spiral elevator 2 is controlled by the pressure value fed back by the pressure sensor 4. When the feedback value of the pressure sensor 4 reaches the initial working pressure provided by the rocket designer, the spiral elevator 2 is in place and locked. Under subsequent transportation conditions, the deformation of the rocket in the supporting position is adapted to by the compression or extension of the nitrogen spring mechanism 3. If the rigid mode is selected, the nitrogen spring mechanism 3 is locked first, and the spiral elevator 2 rises to the theoretical design height under the control of the motor and is locked, so that the nitrogen spring mechanism 3 is in a non-working state.

[0063] Finally, all actions are completed before the rocket is in place, providing support during the rocket transportation process.

[0064] According to the requirements of rocket transportation, choose the corresponding elastic or rigid support mode:

[0065] According to the structural strength of the rocket body support position, if the strength is weak, an elastic support mode needs to be adopted. At this time, the locking assembly 33 is released, and the nitrogen spring body 31 is in a working state. At this time, the nitrogen spring body 31 provides elastic support.

[0066] According to the structural strength of the rocket body support position, if the strength is strong, a rigid support mode needs to be adopted. At this time, the locking assembly 33 is locked and the nitrogen spring body 31 is in a non-working state. At this time, the locking assembly 33 provides stable rigid support.

[0067] Traditional rocket transport auxiliary support structures usually adopt hydraulic structures, which have complex overall systems, high failure rates and high maintenance costs. This design uses nitrogen springs, which are mature products, low equipment costs, strong replaceability and low maintenance costs.

[0068] Traditional rocket transport support structures typically use fixed rigid supports. This design utilizes a combination of nitrogen springs and locking components 33, enabling the support structure to switch freely between elastic and rigid support. In elastic mode, the system adapts the stiffness of the nitrogen springs to the rocket's deformation during transport, based on road vibrations, acceleration / deceleration, and other factors, reducing transport shock.

[0069] The position of the arrow support seat 51 on the arrow support adjustment plate 52 is adjusted by screw thread. By adjusting the position, the docking error is eliminated and the instability factors in the rocket transportation process are reduced.

[0070] In summary, through a switchable design of elasticity and rigidity, the support structure can adjust its usage mode based on the strength and deformation requirements of the rocket's support points, preventing damage to the rocket structure due to excessive support force and improving overall transportation safety. If the elastic support mode is selected, the nitrogen spring can provide cushioning capacity within the load variation range of the support position, effectively absorbing the shock and vibration that may occur during transportation and reducing damage to the rocket body. Nitrogen springs are low-cost and simple in structure. Compared to hydraulic support systems, they do not require complex piping control, further reducing maintenance and replacement costs.

[0071] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A support device for rocket transportation, characterized in that: The invention comprises a support base (1) and an arrow-supporting mechanism (5); a nitrogen spring mechanism (3) is provided between the support base (1) and the arrow-supporting mechanism (5); two ends of the nitrogen spring mechanism (3) are respectively connected to the support base (1) and the arrow-supporting mechanism (5); the nitrogen spring mechanism (3) comprises a nitrogen spring body (31) and a nitrogen spring shell (32); the nitrogen spring body (31) is placed in the nitrogen spring shell (32); a locking assembly (33) is provided on one side of the nitrogen spring shell (32); the locking assembly (33) is connected to the nitrogen spring body (31); and the nitrogen spring body (31) is locked in position by the locking assembly (33); Depending on the needs of rocket transportation, choose the corresponding elastic or rigid mode: According to the structural strength of the rocket body support position, if the strength is weak, the elastic mode needs to be adopted, at this time the locking component (33) is released, the nitrogen spring body (31) is in the working state, and the nitrogen spring body (31) provides elastic support; According to the structural strength of the rocket body support position, if the strength is strong, a rigid mode needs to be adopted. At this time, the locking component (33) is locked and the nitrogen spring body (31) is in a non-working state. At this time, the locking component (33) provides stable rigid support.

2. A rocket transport support device according to claim 1, characterized in that: The locking assembly (33) comprises a fixing block (331) and a connecting block (332). A locking groove (321) penetrating the nitrogen spring housing (32) is provided on the nitrogen spring housing (32). The locking groove (321) is arranged along the telescopic direction of the nitrogen spring body (31). Two fixing blocks (331) are respectively arranged at both ends of the locking groove (321). A limiting rod (333) is provided between the fixing blocks (331). The length direction of the limiting rod (333) is consistent with the telescopic direction of the nitrogen spring body (31). The connecting block (332) is placed in the locking groove (321). The connecting block (332) is slidably connected to the limiting rod (333). The side of the connecting block (332) away from the limiting rod (333) is fixedly connected to the nitrogen spring body (31). A locking nut (334) is threadedly connected to the limiting rod (333). The two locking nuts (334) are respectively placed on both sides of the connecting block (332).

3. The support device for rocket transportation according to claim 1, characterized in that: The arrow-supporting mechanism (5) comprises an arrow-supporting seat (51) and an arrow-supporting adjustment plate (52). The arrow-supporting adjustment plate (52) is movably connected to the arrow-supporting seat (51). The side of the arrow-supporting seat (51) away from the arrow-supporting adjustment plate (52) is arranged in an arc shape.

4. A rocket transport support device according to claim 3, characterized in that: The arrow supporting adjustment plate (52) is provided with a longitudinal adjustment rod (53), which passes through the arrow supporting seat (51) and is slidably connected to the arrow supporting seat (51). The longitudinal adjustment rod (53) is threadedly connected with a longitudinal locking nut (54), and two longitudinal locking nuts (54) are respectively placed on both sides of the arrow supporting seat (51).

5. The support device for rocket transportation according to claim 3, characterized in that: The arrow supporting adjustment plate (52) is provided with a transverse adjustment rod, which passes through the arrow supporting seat (51) and is slidably connected to the arrow supporting seat (51). The transverse adjustment rod is threadedly connected with a transverse locking nut, and the two transverse locking nuts are respectively placed on both sides of the arrow supporting seat (51).

6. The support device for rocket transportation according to claim 1, characterized in that: A spiral elevator (2) is provided above the support base (1), and the spiral elevator (2) is placed between the nitrogen spring mechanism (3) and the support base (1). The lifting direction of the spiral elevator (2) is consistent with the extension and contraction direction of the nitrogen spring mechanism (3).

7. A support device for rocket transportation according to claim 6, characterized in that: A pressure sensor (4) is provided below the arrow-supporting mechanism (5), and the pressure sensor (4) is placed between the nitrogen spring mechanism (3) and the arrow-supporting mechanism (5).

8. The support device for rocket transportation according to claim 1, characterized in that: A guide column mechanism (6) is provided above the support base (1). The guide column mechanism (6) comprises an upper guide column (61) and a lower guide column (62). The lower guide column (62) is connected to the support base (1), and the upper guide column (61) is connected to the arrow-supporting mechanism (5). The upper guide column (61) and the lower guide column (62) are sleeved with each other and slidably connected. The sliding direction of the upper guide column (61) and the lower guide column (62) is consistent with the telescopic direction of the nitrogen spring mechanism (3).

9. The method for using a support device for rocket transportation according to claim 7, characterized in that: First, an elastic or rigid mode is selected according to the requirements of rocket transportation. If the elastic mode is selected, the locking component is not used, so that the nitrogen spring mechanism (3) is in a working state. If the rigid mode is selected, the locking component is used to lock the nitrogen spring mechanism (3), so that the nitrogen spring mechanism (3) is in a non-working state. Then it is hoisted to the designated position for rocket transportation, and docked with the rocket support point through the arrow supporting mechanism (5). If the elastic mode is selected, the contact between the arrow supporting mechanism (5) and the rocket is adjusted vertically through the spiral elevator (2). The pressure value fed back by the pressure sensor (4) controls the height of the spiral elevator (2). When the feedback value of the pressure sensor (4) reaches the initial working pressure provided by the rocket designer, the spiral elevator (2) is in place and locked. Under the subsequent transportation working conditions, the deformation of the rocket at the supporting position is adapted by the compression or extension of the nitrogen spring mechanism (3). If the rigid mode is selected, the nitrogen spring mechanism (3) is locked first, and the spiral elevator (2) rises to the theoretical design height under the control of the motor and is locked, so that the nitrogen spring mechanism (3) is in a non-working state. Finally, all actions are completed before the rocket is in place, providing support during the rocket transportation process.

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