A rocket stabilizing device and hoisting system

Abstract

The application discloses a rocket stabilizing device and hoisting system, and belongs to the technical field of rocket launching, which comprises a fixing frame, a fastening mechanism and a wrapping belt. The fixing frame comprises a fixing frame body with an opening. The fixing frame body is provided with a limiting circular arc surface which is adapted to the outer diameter of a rocket body. The limiting circular arc surface is arranged on a minor arc with the axis of the rocket body as the center. The fastening mechanism is arranged at the end point of the limiting circular arc surface and is fixedly connected with the fixing frame body. The wrapping belt is arranged at the opening of the fixing frame. The end of the wrapping belt is fixedly connected with the fastening mechanism. The fastening mechanism is configured to adjust the length of the wrapping belt so as to fix the rocket body in the area surrounded by the wrapping belt and the fixing frame. The application does not need to set a hoisting point on the rocket body and does not need to use a hydraulic or pneumatic system, and has the advantages of simple structure, good stability and low maintenance cost in the later period.

Description

Technical Field

[0001] This invention relates to the field of rocket launch technology, and in particular to a rocket stabilization device and hoisting system. Background Technology

[0002] Currently, my country's mainstream launch vehicles employ horizontal transport, using an erector or hoisting system to convert the rocket's attitude from horizontal to vertical, before vertically hoisting it to the launch site. During vertical hoisting, lifting points are typically installed on the rocket itself or on a hydraulic clamp structure, and specialized lifting equipment is used to vertically lift the entire rocket body.

[0003] Currently, the vertical hoisting of the rocket body has the following shortcomings:

[0004] If multiple lifting points are set on the arrow, the local load-bearing strength of the arrow body must be considered during the design. The impact of adding lifting point positions on the takeoff aerodynamic characteristics needs to be verified, and the initial simulation verification calculations are quite extensive. When the arrow body is lifted as a whole with a single lifting point, the swing stability of the arrow body needs to be ensured by an auxiliary traction device.

[0005] In addition, when using hydraulic or pneumatic clamps to fix the arrow body radially, the hydraulic or pneumatic clamp system is complex and large in size. During the erection process and vertical hoisting and transportation, the interference of the hydraulic or pneumatic system needs to be considered, and the subsequent maintenance cost is high.

[0006] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the Invention

[0007] To solve the above-mentioned technical problems, this application provides a rocket stabilization device and hoisting system that does not require hoisting points on the rocket body and does not require hydraulic or pneumatic systems. It has a simple structure, good stability, and low maintenance costs.

[0008] A rocket stabilizing device, comprising:

[0009] A fixing frame; the fixing frame includes a fixing frame body with an opening; the fixing frame body has a limiting arc surface adapted to the outer diameter of the rocket body; the limiting arc surface is arranged on a minor arc with the rocket body axis as the center;

[0010] Fastening mechanism; the fastening mechanism is located at the end point of the limiting arc surface and is fixedly connected to the fixing frame;

[0011] A strap; the strap is disposed at the opening of the fixing frame; the end of the strap is fixedly connected to the fastening mechanism; the fastening mechanism is configured to adjust the length of the strap to fix the arrow body within the area enclosed by the strap and the fixing frame.

[0012] Preferably, the fastening mechanism includes a fastening frame and a first tensioning member for adjusting the length of the bag strap; one end of the first tensioning member is fixedly connected to the bag strap; the other end of the first tensioning member is fixedly connected to the fastening frame.

[0013] Preferably, the fastening mechanism further includes a guide rod for guiding the strap; the guide rod is arranged parallel to the arrow body and is fixedly or rotatably connected to the fastening frame.

[0014] Preferably, the guide rod includes a first guide rod and a second guide rod arranged parallel to each other; the second guide rod is arranged close to the arrow body; the strap passes through the second guide rod and the arrow body, as well as between the first guide rod and the second guide rod; the strap is tangential to both the first guide rod and the second guide rod.

[0015] Preferably, the fixed frame also includes a lifting through hole for the lifting component to pass through.

[0016] Preferably, it also includes a second tensioning member for fixing the rocket stabilizing device and the rocket erecting device radially to the rocket body, and a third tensioning member for fixing the rocket stabilizing device and the rocket erecting device axially to the rocket body.

[0017] According to another aspect of this application, a lifting system is also provided, including the aforementioned rocket stabilizing device, as well as a lifting device, a lifting component, and a pallet; the pallet is fixed to the bottom end of the rocket body; the lifting component is disposed between the lifting device and the pallet; the lifting component passes through the rocket stabilizing device; one end of the lifting component is fixedly connected to the lifting device, and the other end is fixedly connected to the pallet.

[0018] Preferably, the lifting component includes a load-bearing lifting component and an adjusting lifting component; the load-bearing lifting component includes a first load-bearing lifting component and a second load-bearing lifting component; the line connecting the first load-bearing lifting component and the second load-bearing lifting component is located on one side of the rocket body axis, and the adjusting lifting component is located on the other side of the rocket body axis.

[0019] Preferably, the distance between the line connecting the first and second load-bearing components and the axis of the rocket body is 100mm.

[0020] Preferably, the supporting lifting component includes an upper lifting component, a lower lifting component, and a connecting component; one end of the connecting component is fixedly connected to the upper lifting component, and the other end of the connecting component is fixedly connected to the lower lifting component; the connecting component passes through the rocket stabilizing device.

[0021] Compared with the prior art, this application has at least the following beneficial effects:

[0022] 1. The arrow body stabilization device of the present invention uses a pre-tightening method to fix the arrow body radially, which eliminates the need to set up lifting points on the arrow body and eliminates the need to use hydraulic or pneumatic systems. It has a simple structure, good stability, and low maintenance cost.

[0023] 2. The arrow body stabilizing device of the present invention adopts a wrapping belt pre-tensioning form, the wrapping belt specifications are adjustable to adapt to arrow bodies of different sizes and specifications, it has strong enveloping properties, strong operability and maintainability, no hydraulic or electrical equipment, and strong working stability.

[0024] 3. The arrow body stabilizing device of the present invention has a guide rod, which can guide the strap, increase the fit between the strap and the arrow body, improve the radial fixing effect of the arrow body, and control the pressure between the strap and the arrow body within a reasonable range.

[0025] 4. The stabilizing device of the present invention has a first tensioning member during the rocket erection process, which adjusts the tension of the straps and adjusts the radial fixing force of the rocket body.

[0026] 5. The stabilizing device of the present invention has a second tensioning member during the rocket erection process, which fixes the stabilizing device to the erection device in the axial and radial directions of the rocket body, preventing the stabilizing device and the rocket body from slipping during the erection and hoisting process.

[0027] 6. The hoisting system of the present invention adopts a three-point hoisting method, and the load-bearing hoisting component and the adjusting hoisting component are set on both sides of the rocket shaft. The relative position of the rocket body's center of mass is adjusted by adjusting the length of the hoisting component, so that the center of mass of the rocket body is stable during the vertical hoisting process.

[0028] 7. The hoisting system boom of the present invention can adopt an assembled structure, the length is adjustable, it is suitable for rocket bodies of different heights and sizes, and has strong versatility. Attached Figure Description

[0029] The following sections will describe some specific embodiments of the invention in detail by way of example and not limitation, with reference to the accompanying drawings. The same reference numerals in the drawings denote the same or similar parts or portions. Those skilled in the art should understand that these drawings are not necessarily drawn to scale.

[0030] In the picture:

[0031] Figure 1 This is a schematic diagram of the overall structure of the rocket stabilization device of the present invention;

[0032] Figure 2 for Figure 1 A magnified view of a portion of position A in the middle;

[0033] Figure 3 This is a schematic diagram of the connection position between the guide rod and the strap in this invention;

[0034] Figure 4This is a schematic diagram showing the connection between the hoisting system of the present invention and the rocket body;

[0035] Figure 5 This is a schematic diagram showing the position of the lifting component relative to the center of the rocket body in this invention;

[0036] Figure 6 This is a schematic diagram of the hoisting system of the present invention;

[0037] Figure 7 This is a schematic diagram of the structure of the lifting component of the present invention penetrating the rocket stabilization device.

[0038] The above figures include the following reference numerals:

[0039] 10. Strap; 20. Fixing frame; 21. Fixing frame body; 22. Limiting arc surface; 30. Fastening mechanism; 31. Fastening frame; 32. First guide rod; 33. First tensioning member; 34. Second tensioning member; 35. Second guide rod; 36. Lifting through hole; 100. Lifting tool; 200. Rocket body; 300. Lifting component; 301. Upper lifting component; 302. Connecting component; 303. Lower lifting component; 310. First load-bearing lifting component; 320. Second load-bearing lifting component; 330. Adjusting lifting component; 400. Pallet; 500. Rocket stabilizing device. Detailed Implementation

[0040] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0041] like Figures 1-3 As shown, a rocket stabilizing device includes: a fixing frame 20, a fastening mechanism 30, and a strap 10. The fixing frame 20 includes a fixing frame body 21 with an opening, and the fixing frame body 21 has a limiting arc surface 22 adapted to the outer diameter of the rocket body, and the limiting arc surface 22 is arranged on a minor arc with the rocket body axis as the center. Because the limiting arc surface 22 is arranged on a minor arc with the rocket body axis as the center, the rocket stabilizing device can be engaged with the rocket body from the side of the rocket body and can be detached from the side of the rocket body.

[0042] The fastening mechanism 30 is located at the end of the limiting arc surface 22 and is fixedly connected to the fixed frame 21.

[0043] The strap 10 is positioned at the opening of the fixing frame 20, and its end is fixedly connected to the fastening mechanism 30. The fastening mechanism 30 is configured to adjust the length of the strap 10 to secure the arrow body within the area enclosed by the strap 10 and the fixing frame 20. The strap 10 is preferably made of a flexible material with tensile strength, which can bind and limit the arrow body while providing better fit and self-adaptability.

[0044] The fastening mechanism 30 includes a fastening frame 31 and a first tensioning member 33 for adjusting the length of the strap 10. One end of the first tensioning member 33 is fixedly connected to the strap 10, and the other end is fixedly connected to the fastening frame 31.

[0045] Preferably, the fastening mechanism 30 has two parts, which are fixed to both ends of the fixed frame 21.

[0046] The first tensioning member 33 is preferably a turnbuckle. Furthermore, other mechanical structures that can adjust the distance between connection points by self-adjustment are also applicable to this invention, such as ball screw structures, multi-link mechanisms, and worm gears.

[0047] In another embodiment of the present invention, the fastening mechanism 30 further includes a guide rod for guiding the strap 10. The guide rod is arranged parallel to the arrow body and is fixedly or rotatably connected to the fastening frame 31. The guide rod guides the strap 10, thereby controlling the connection position between the strap and the fastening mechanism 30, making the force distribution more reasonable. Simultaneously, the guide rod controls the position of the strap 10 near the fastening mechanism 30, ensuring that the strap 10 has a better enveloping effect on the arrow body, ensuring the contact area between the arrow body and the strap 10, and controlling the pressure between the strap 10 and the arrow body within a reasonable range. In other embodiments of the present invention, the connection between the strap 10 and the fastening mechanism 30 can be achieved without the guide rod, and the radial direction of the arrow body can be limited by the combination of the strap 10 and the fastening mechanism 30.

[0048] When the guide rod is fixedly connected to the fastening frame 31, the strap 10 can slide along the surface of the guide rod, realizing relative movement between the guide rod and the fastening frame 31. When the guide rod is rotatably connected to the fastening frame 31, the strap 10 moves along its length direction by means of its rotation.

[0049] Preferably, the guide rods include a first guide rod 32 and a second guide rod 35 arranged parallel to each other. The second guide rod 35 is positioned close to the arrow body, and the strap 10 passes through the space between the second guide rod 35 and the arrow body, as well as between the first guide rod 32 and the second guide rod 35. The strap 10 is tangentially positioned to both the first guide rod 32 and the second guide rod 35. The second guide rod 35, positioned close to the arrow body, guides the strap 10 closer to the arrow body at the connection point between the strap 10 and the fastening mechanism 30, maximizing the contact area between the strap 10 and the arrow body and reducing the pressure on the contact surface between the arrow body and the strap 10. The distance between the first guide rod 32 and the arrow body is greater than the distance between the second guide rod 35 and the arrow body, and this distance is controlled at a reasonable position. This ensures that the strap 10, guided by the first guide rod 32, is positioned more appropriately at the connection point with the fastening mechanism 30, guaranteeing the bonding strength at the connection point and preventing excessive concentration of stress.

[0050] In addition, the fixed frame 21 also includes a lifting through hole 36 for the lifting component to pass through. The lifting through hole 36 is arranged parallel to the axial direction of the rocket body. The lifting through hole 36 allows the lifting component to pass through it and limits its width. When the rocket body tilts to the side, it limits the tilting and effectively prevents the rocket body from overturning during the lifting process.

[0051] As another embodiment of the present invention, it further includes a second tensioning member 34 for fixing the rocket stabilizing device and the rocket erecting device radially to the rocket body, and a third tensioning member (not shown) for fixing the rocket stabilizing device and the rocket erecting device axially to the rocket body. The second tensioning member 34 is used to secure the mechanism to the rocket erecting device radially to the rocket body, and the third tensioning member is used to secure the mechanism to the rocket erecting device axially to the rocket body.

[0052] like Figures 4-7 As shown, a lifting system includes the aforementioned rocket stabilizing device 500, a lifting device 100, a lifting component 300, and a pallet 400. The pallet 400 is fixed to the bottom end of the rocket body 200 by means of screws or other detachable fixing methods. The lifting component 300 is disposed between the lifting device 100 and the pallet 400; one end of the lifting component 300 is fixedly connected to the lifting device 100, and the other end is fixedly connected to the pallet 400. Simultaneously, the lifting component 300 passes through the lifting through hole 36, penetrating the rocket stabilizing device 500.

[0053] The lifting component 300 includes a load-bearing lifting component and an adjusting lifting component 330. The load-bearing lifting component includes a first load-bearing lifting component 310 and a second load-bearing lifting component 320, with the line connecting the first and second load-bearing lifting components 310 and 320 located on one side of the axis of the rocket body 200. The adjusting lifting component 330 is located on the other side of the axis of the rocket body 200. The length of the adjusting lifting component 330 is adjustable, allowing for adjustments to the verticality and center of gravity of the rocket body 200.

[0054] The first load-bearing lifting member 310 and the second load-bearing lifting member 320 are preferably lifting rods, chains, or lifting wire ropes.

[0055] The adjusting lifting component 330 is preferably a lifting rod, chain, or wire rope equipped with a telescopic structure. The telescopic structure is preferably a hand-operated hoist.

[0056] Preferably, the distance between the line connecting the first bearing member 310 and the second bearing member 320 and the axis of the arrow body 200 is 100mm. Within this distance range, the first bearing member 310 and the second bearing member 320 can provide good support for the arrow body 200. At the same time, when adjusting the adjusting member 330, the center of gravity of the arrow body 200 can be well controlled.

[0057] In one embodiment of the present invention, the supporting lifting member includes an upper lifting member 301, a lower lifting member 303, and a connecting member 302. One end of the connecting member 302 is fixedly connected to the upper lifting member 301, and the other end of the connecting member 302 is fixedly connected to the lower lifting member 303. The connecting member 302 is disposed at the position of the rocket stabilizing device 500 and inserted into the lifting through hole 36, thereby enabling the supporting lifting member to penetrate through the rocket stabilizing device 500. The connection member 302 facilitates the installation of the supporting lifting member, especially the installation at the position of the rocket stabilizing device 500, and avoids situations where the supporting lifting member has connection points that cannot be penetrated.

[0058] Preferably, the connector 302 is a long strip structure made of a rigid material capable of supporting the arrow body 200.

[0059] In addition, the lifting rods, chains, or wire ropes other than the 330 telescopic structure of the lifting component can also be connected by upper lifting components, lower lifting components, and connecting components. The principle and function are the same as those of the load-bearing lifting components, and will not be elaborated here.

[0060] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0061] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0062] It should be noted that the terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this application described herein can be implemented in sequences other than those illustrated or described herein.

[0063] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A rocket stabilizing device, characterized in that, include: A fixing frame; the fixing frame includes a fixing frame body with an opening; the fixing frame body has a limiting arc surface adapted to the outer diameter of the rocket body; the limiting arc surface is arranged on a minor arc with the rocket body axis as the center; Fastening mechanism; the fastening mechanism is located at the end point of the limiting arc surface and is fixedly connected to the fixing frame; A strap; the strap is disposed at the opening of the fixing frame; the end of the strap is fixedly connected to the fastening mechanism; The fastening mechanism is configured to adjust the length of the strap to secure the arrow body within the area enclosed by the strap and the mounting bracket; The fastening mechanism includes a fastening frame and a first tensioning member for adjusting the length of the bag strap; one end of the first tensioning member is fixedly connected to the bag strap; the other end of the first tensioning member is fixedly connected to the fastening frame; The fastening mechanism further includes a guide rod for guiding the strap; the guide rod is arranged parallel to the arrow body and is fixedly or rotatably connected to the fastening frame; The guide rod includes a first guide rod and a second guide rod arranged parallel to each other; the second guide rod is positioned close to the arrow body; the strap passes between the second guide rod and the arrow body, and between the first guide rod and the second guide rod; the strap is tangential to both the first guide rod and the second guide rod.

2. The rocket stabilizing device as described in claim 1, characterized in that, The fixed frame also includes a hoisting through hole for the hoisting component to pass through.

3. The rocket stabilizing device as described in claim 1, characterized in that, It also includes a second tensioning member for fixing the rocket stabilizing device and the rocket erecting device radially to the rocket body, and a third tensioning member for fixing the rocket stabilizing device and the rocket erecting device axially to the rocket body.

4. A hoisting system, characterized in that, The device includes the rocket stabilizing device as described in any one of claims 1-3, as well as a lifting device, a lifting component, and a tray; the tray is fixed to the bottom end of the rocket body; the lifting component is disposed between the lifting device and the tray; the lifting component passes through the rocket stabilizing device; one end of the lifting component is fixedly connected to the lifting device, and the other end is fixedly connected to the tray.

5. The hoisting system as described in claim 4, characterized in that, The lifting components include a load-bearing lifting component and an adjusting lifting component; the load-bearing lifting component includes a first load-bearing lifting component and a second load-bearing lifting component; the line connecting the first load-bearing lifting component and the second load-bearing lifting component is located on one side of the rocket body axis, and the adjusting lifting component is located on the other side of the rocket body axis.

6. The hoisting system as described in claim 5, characterized in that, The distance between the line connecting the first and second load-bearing components and the axis of the rocket body is 100mm.

7. The hoisting system as described in claim 6, characterized in that, The supporting lifting component includes an upper lifting component, a lower lifting component, and a connecting component; one end of the connecting component is fixedly connected to the upper lifting component, and the other end of the connecting component is fixedly connected to the lower lifting component; the connecting component passes through the rocket stabilizing device.

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