An asymmetric carrier rocket working platform

Abstract

The present application discloses an asymmetric launch vehicle working platform, which relates to the technical field of launch vehicle launch support. The working platform can swing horizontally together with the fixed service tower revolving platform. The booster and core first-stage working platform of the working platform includes two platform plates. The two platform plates of the booster and core first-stage working platform are used to surround and bind the rocket with two boosters when swinging and closing in the horizontal direction. The two platform plates are arranged in an asymmetric form. At least one middle flap device is provided on one of the platform plates of the booster and core first-stage working platform. The middle flap device includes a middle flap and a driving member for driving the middle flap to flip in the vertical direction. The inner edge of the middle flap and the remaining inner ring positions of the platform plate of the booster and core first-stage working platform together form an area for surrounding and binding the rocket with two boosters. The above-mentioned asymmetric launch vehicle working platform optimizes the movement process of the flap, improves the safety of the launch mission, and helps to promote the rapid development of commercial spaceflight.

Description

Technical Field

[0001] This application relates to the technical field of launch support for launch vehicles, and particularly to an asymmetric launch vehicle working platform. Background Art

[0002] The launch vehicle working platform provides key support during the general assembly, fueling, and launch phases of the rocket, provides environmental protection for the rocket body, and after the rocket is hoisted to the launch position, the working platform provides support for the connection and testing of the rocket-ground interface.

[0003] In practice, the inventors found that the existing launch vehicle working platforms have the following problems: During the rocket preparation for launch phase, the working platform swings open with the fixed service tower revolving platform to make room for the rocket to take off. Due to the excitation of wind loads and other factors, the movement of the fixed service tower revolving platform may deviate from the ideal movement state during the movement process, and there is a risk that the actual distance between the working platform and the rocket exceeds the safety distance. Therefore, how to reduce the interference risk between the working platform and the rocket is an urgent problem to be solved in this field. Summary of the Invention

[0004] The purpose of this application is to provide an asymmetric launch vehicle working platform, which optimizes the movement process of the flap, improves the safety of the launch mission, and helps to promote the rapid development of commercial spaceflight.

[0005] To achieve the above object, this application provides an asymmetric launch vehicle working platform. The working platform is used to be installed on the fixed service tower revolving platform, and the working platform can swing horizontally together with the fixed service tower revolving platform. The working platform includes a booster and core stage one working platform. The booster and core stage one working platform includes two platform plates. The two platform plates of the booster and core stage one working platform are used to surround and bind the rocket with two boosters when swinging and closing horizontally. The two platform plates of the booster and core stage one working platform adopt an asymmetric layout form. At least one middle flap device is provided on one of the platform plates of the booster and core stage one working platform. The middle flap device includes a middle flap and a driving member for driving the middle flap to flip vertically. The inner edge of the middle flap and the remaining inner circle positions of the platform plate of the booster and core stage one working platform jointly form an area for surrounding and binding the rocket with two boosters.

[0006] In some embodiments, the number of the middle flap devices is two, and the two middle flap devices are arranged adjacent to each other, and the two middle flaps form a splicing in the horizontal direction.

[0007] In some embodiments, the working platform further includes a fairing working platform, which includes two platform plates. The two platform plates of the fairing working platform are arranged symmetrically. Large flap devices are provided on both of the two platform plates of the fairing working platform. The large flap device includes a large flap and a driving member for driving the large flap to flip in the vertical direction. The inner edges of the two large flaps jointly form an area surrounding the rocket fairing.

[0008] In some embodiments, a small flap device is provided on the booster and core first-stage working platform and / or the fairing working platform. The small flap device includes a small flap that can flip in the vertical direction.

[0009] When the small flap device is provided on the booster and core first-stage working platform, the small flap is located at the position where the platform plate of the booster and core first-stage working platform surrounds the rocket. When the small flap device is provided on the fairing working platform, the small flap is located at the position where the platform plate of the fairing working platform surrounds the rocket.

[0010] In some embodiments, the working platform further includes a wire rope pulling device, which is provided on the booster and core first-stage working platform and / or the fairing working platform.

[0011] When the wire rope pulling device is provided on the booster and core first-stage working platform, the wire rope cable of the wire rope pulling device is connected to the platform plate of the booster and core first-stage working platform. When the wire rope pulling device is provided on the fairing working platform, the wire rope cable of the wire rope pulling device is connected to the platform plate of the fairing working platform.

[0012] In some embodiments, the working platform further includes a lifting device, which is used to adjust the height of the platform plate of the booster and core first-stage working platform and / or the platform plate of the fairing working platform.

[0013] In some embodiments, the lifting device includes a relay pin and a climbing oil cylinder, and the height adjustment is achieved by inserting and removing the relay pin and coordinating with the telescopic stroke of the climbing oil cylinder.

[0014] In some embodiments, the working platform further includes a guiding device, which is used to guide the platform plate of the booster and core first-stage working platform and / or the platform plate of the fairing working platform to move up and down along the height.

[0015] In some embodiments, the guiding device includes a guide rail, a vertical guiding wheel, and a horizontal guiding wheel. The guide rail is fixed on the rotary platform of the fixed service tower. The vertical guiding wheel and the horizontal guiding wheel are installed on the platform plate, and the vertical guiding wheel and the horizontal guiding wheel cooperate with the guide rail.

[0016] In some embodiments, two sets of the guiding devices are respectively arranged on two symmetric sides of the working platform, and the installation position and the number of the lifting devices correspond to those of the guiding devices.

[0017] Compared with the above background art, the asymmetric launch vehicle working platform provided by the present application is used to be installed on the rotary platform of a fixed service tower. The working platform can swing horizontally together with the rotary platform of the fixed service tower. The working platform includes a booster and core first stage working platform. The booster and core first stage working platform includes two platform plates. The two platform plates of the booster and core first stage working platform are used to surround and bind the rocket with two boosters when swinging and closing in the horizontal direction. The two platform plates of the booster and core first stage working platform adopt an asymmetric arrangement form. At least one middle turning plate device is arranged on one of the platform plates of the booster and core first stage working platform. The middle turning plate device includes a middle turning plate and a driving member for driving the middle turning plate to turn in the vertical direction. The inner edge of the middle turning plate and the remaining inner ring positions of the platform plate of the booster and core first stage working platform together form an area for surrounding and binding the rocket with two boosters.

[0018] During the operation of this asymmetric launch vehicle working platform, the working platform is used in combination with the rotating platform of the fixed service tower. First, the rotating platform of the fixed service tower is fully opened, and the working platform swings horizontally with the rotating platform of the fixed service tower to the fully opened state. The transport vehicle transports the rocket body to the launch position, and the rocket body is hoisted to the launch pad in sequence by hoisting and the rocket is assembled, including the core first stage and booster combination, the core second stage, and the fairing combination. The rotating platform of the fixed service tower is closed according to the assembly process, and the working platform is closed together with the rotating platform of the fixed service tower. At this time, when the two platform plates of the booster and core first stage working platform swing and close horizontally, they surround and bind the rocket with two boosters, providing a working environment for the connection and testing of the rocket-ground interface; during the rocket launch stage, the rotating platform of the fixed service tower is fully opened, and the working platform swings horizontally with the rotating platform of the fixed service tower to the fully opened state, clearing the flight path for the rocket to take off. During the above process, especially before the working platform is closed, since a middle turning plate device is provided on one of the platform plates of the booster and core first stage working platform, the middle turning plate can be driven by the driving member in the middle turning plate device to turn in the vertical direction. For example, the middle turning plate can be turned from the horizontal state to the vertical state, so as to reduce the interference risk between the working platform and the rocket. After the rotating platform of the fixed service tower is stable in motion and the rocket is hoisted, the middle turning plate is then lowered from the vertical state to the horizontal state, and the inner edge of the middle turning plate and the rest of the inner circle position of the platform plate of the booster and core first stage working platform together form an area that surrounds and binds the rocket with two boosters. Because the two platform plates of the booster and core first stage working platform in the working platform adopt an asymmetric layout form, it can better adapt to the rocket with two boosters, achieve a full-circle surrounding effect on the outer shape of the rocket, eliminate the dead corners of the working environment, and since the structure for realizing the flipping function on the platform plate of the booster and core first stage working platform is the middle turning plate, and the middle turning plate is only a part of the area that surrounds and binds the rocket with two boosters, the operation of flipping the middle turning plate will not cause the overall flipping of the platform plate, but only cause a part of the platform plate to flip. The advantages of doing this are, on the one hand, reducing the lifting height generated by flipping, reducing the occupied space of a single layer of the working platform, and solving the interference problem between the upper and lower layers of the working platform; on the other hand, reducing the required driving force of the driving member, enabling the driving member to allow the selection of a model with a smaller driving force, smaller volume and weight, and solving the weight problem of the driving member with a large driving force.

[0019] Combined with the above structure and process description, it can be seen that this asymmetric launch vehicle working platform has at least the following beneficial effects: This asymmetric launch vehicle working platform optimizes the movement process of the turning plate, improves the safety of the launch mission, and helps to promote the rapid development of commercial spaceflight. Description of the Drawings

[0020] To more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only the embodiments of the present application. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on the provided drawings.

[0021] Figure 1 Structural diagram of the booster and core first-stage working platform in the asymmetric launch vehicle working platform provided by the embodiment of the present application;

[0022] Figure 2 For Figure 1 Structural diagram of a platform board in

[0023] Figure 3 For Figure 1 Structural diagram of the middle turning plate device during the turning movement in

[0024] Figure 4 Structural diagram of the fairing working platform in the asymmetric launch vehicle working platform provided by the embodiment of the present application;

[0025] Figure 5 For Figure 4 Structural diagram of the fairing working platform when it is turned up in

[0026] Figure 6 For Figure 4 Structural diagram of a platform board in

[0027] Figure 7 For Figure 4 Structural diagram of the large turning plate device during the turning movement in

[0028] Figure 8 Structural diagram of the small turning plate device provided by the embodiment of the present application;

[0029] Figure 9 Structural diagram of the lifting device provided by the embodiment of the present application;

[0030] Figure 10 For Figure 9 Structural diagram of the relay pin when it is locked in

[0031] Figure 11 Structural diagram of the guide rail layout position provided by the embodiment of the present application;

[0032] Figure 12 Structural diagram of the guiding device provided by the embodiment of the present application.

[0033] Wherein:

[0034] Booster and core first-stage working platform 1,

[0035] Fairing working platform 2,

[0036] Middle turning plate device 3, middle turning plate 31, first driving oil cylinder 32, first rotating hinge seat 33,

[0037] Large turning plate device 4, large turning plate 41, second driving oil cylinder 42, second rotating hinge seat 43,

[0038] Small turning plate device 5

[0039] Wire rope pulling device 6,

[0040] Lifting device 7, relay pin 71, climbing oil cylinder 72,

[0041] Guiding device 8, guide rail 81, vertical guiding wheel 82, horizontal guiding wheel 83. Specific implementation manner

[0042] The working platform of the launch vehicle is used for providing launch support and guarantee during the general assembly and fueling stages of the rocket after the transfer. After the rocket is hoisted to the launch position, the working platform provides support for the connection and testing of the rocket-ground interface. During the rocket launch preparation stage, the working platform swings with the rotary platform of the fixed service tower to make room for the rocket to take off. Due to the excitation of wind load and other factors, the movement of the rotary platform of the fixed service tower may deviate from the ideal movement state during the movement process, which poses higher requirements for the design of the safety distance between the working platform and the rocket. To meet the growing demand for commercial rocket launches, it is of great significance to study how to reduce the interference risk between the working platform and the rocket.

[0043] In daily practice, the inventor found that the existing technical solutions have the following problems. In the design of the previous first-stage core and booster working platforms, the traditional method was to set up 4 oil cylinders to drive the turning plate mechanism to achieve the rocket avoidance function, and the driving force required for the oil cylinders was relatively large; in addition, the height after the turning plate was turned up was relatively high, and it was necessary to ensure that there was no interference with the upper working platform and the swing rod, which posed higher requirements for the space occupied by the single-layer working platform. During the working process of the previous fixed service tower rotary platform, in order to make the working platform adapt to different working heights, it was necessary to pull the working platform by a crane to achieve the lifting of the platform. Each adjustment step was relatively complex, and there were certain safety risks in pulling by a crane.

[0044] The movement process of the existing working platform is relatively complex, requires a large number of operators, and there are certain safety risks. How to optimize the turning plate and lifting mechanisms of the working platform is an urgent problem to be solved in this field.

[0045] Next, the technical solutions in the embodiments of the present application will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0046] To enable those skilled in the art of this technology to better understand the solution of the present application, the present application will be further described in detail below in conjunction with the accompanying drawings and specific implementation manners.

[0047] Please refer to Figure 1 and Figure 2 , Figure 1 , which is a structural diagram of the booster and core first-stage working platform in the asymmetric launch vehicle working platform provided by the embodiment of the present application. Figure 2 is Figure 1 a structural diagram of a platform board in

[0048] In a specific implementation manner, the asymmetric launch vehicle working platform provided by the embodiment of the present application is used to be installed on the rotary platform of the fixed service tower. The working platform can swing horizontally together with the rotary platform of the fixed service tower. The working platform includes a booster and core first-stage working platform 1. The booster and core first-stage working platform 1 includes two platform boards. The two platform boards of the booster and core first-stage working platform 1 are used to surround and bind the rockets of the two boosters when swinging and closing horizontally. The two platform boards of the booster and core first-stage working platform 1 adopt an asymmetric arrangement form. At least one middle turning plate device 3 is provided on one platform board of the booster and core first-stage working platform 1. The middle turning plate device 3 includes a middle turning plate 31 and a driving member for driving the middle turning plate 31 to turn vertically. The inner edge of the middle turning plate 31 and the remaining inner circle positions of the platform board of the booster and core first-stage working platform 1 together form a region for surrounding and binding the rockets of the two boosters.

[0049] In some cases, the rotation angle range of the rotary platform of the fixed service tower is between 0 degrees and 180 degrees, and the rotary platforms of the fixed service tower are arranged in pairs in the same height direction. The paired rotary platforms of the fixed service tower move towards each other and away from each other. When rotating to 0 degrees in the horizontal plane, the rotary platform of the fixed service tower is in the closed position. When rotating to 180 degrees in the horizontal plane, the rotary platform of the fixed service tower is in the opened position.

[0050] During the operation of this asymmetric launch vehicle working platform, the working platform is used in combination with the rotating platform of the fixed service tower. First, the rotating platform of the fixed service tower is fully opened, and the working platform swings horizontally with the rotating platform of the fixed service tower to the fully opened state. The transporter transports the rocket body to the launch position, and the rocket body is hoisted onto the launch pad in sequence and the rocket is assembled, including the core first stage and booster combination, the core second stage, and the fairing-star combination. The rotating platform of the fixed service tower is closed according to the assembly process, and the working platform is closed together with the rotating platform of the fixed service tower. At this time, when the two platform plates of the booster and core first stage working platform 1 swing and close horizontally, they surround and bind the rocket with two boosters, providing a working environment for the ground-rocket interface connection and testing; during the rocket launch phase, the rotating platform of the fixed service tower is fully opened, and the working platform swings horizontally with the rotating platform of the fixed service tower to the fully opened state, clearing a flight path for the rocket to take off. During the above process, especially before the working platform is closed, since a middle flap device 3 is provided on one platform plate of the booster and core first stage working platform 1, the middle flap 31 can be driven by the driving member in the middle flap device 3 to flip in the vertical direction, for example, the middle flap 31 is flipped from the horizontal state to the vertical state, so as to reduce the interference risk between the working platform and the rocket. After the rotating platform of the fixed service tower is stable in motion and the rocket is hoisted, the middle flap 31 is then lowered from the vertical state to the horizontal state, and the inner edge of the middle flap 31 and the remaining inner ring positions of the platform plate of the booster and core first stage working platform 1 together form a region that surrounds and binds the rocket with two boosters. Because the two platform plates of the booster and core first stage working platform 1 in the working platform adopt an asymmetric arrangement form, it can better adapt to the rocket with two boosters, achieve a full-circle surrounding effect on the rocket's outer shape, eliminate dead corners in the working environment, and since the structure for realizing the flipping function on the platform plate of the booster and core first stage working platform 1 is the middle flap 31, and the middle flap 31 is only a part of the region that surrounds and binds the rocket with two boosters, the operation of flipping the middle flap 31 does not cause the overall flipping of the platform plate, but only causes a part of the platform plate to flip. The advantages of this are that, on the one hand, it reduces the flipping height generated by flipping, reduces the occupied space of a single layer of the working platform, and solves the interference problem between the upper and lower layers of the working platform; on the other hand, it reduces the required driving force of the driving member, allowing the driving member to be selected with a smaller driving force, smaller volume and weight, and solves the weight problem of the driving member with a large driving force.

[0051] Combined with the above structure and process description, it can be seen that this asymmetric launch vehicle working platform has at least the following beneficial effects: This asymmetric launch vehicle working platform optimizes the movement process of the flap, improves the safety of the launch mission, and helps to promote the rapid development of commercial spaceflight.

[0052] Please continue to refer to Figure 1 andFigure 2 In some embodiments, the number of the middle turning plate devices 3 is two, and the two middle turning plate devices 3 are arranged adjacent to each other, and the two middle turning plates 31 are spliced in the horizontal direction.

[0053] In this embodiment, by setting the number of the middle turning plate devices 3 to two, the area of a single middle turning plate 31 can be further reduced, and at the same time, the required driving force of the driving member can be further reduced. The flipping driving of the two middle turning plates 31 is respectively realized by two driving members, so that a single driving member can allow a model with a smaller driving force, smaller volume and smaller weight to be selected. Therefore, the two driving members can be selected as two small oil cylinders. This solution reduces the self-weight compared with the conventional symmetric platform design and simplifies the design.

[0054] Please refer to Figure 3 , Figure 3 for Figure 1 the structural diagram of the middle turning plate device in

[0055] In some cases, as Figure 3 shown, the driving member of the middle turning plate device 3 is selected as the first driving oil cylinder 32, and the middle turning plate device 3 further includes a first rotating hinge seat 33. The cylinder body of the first driving oil cylinder 32 is installed on the platform plate of the booster and core first-stage working platform 1 through a support, the middle turning plate 31 is rotatably installed on the platform plate of the booster and core first-stage working platform 1 through the first rotating hinge seat 33, and the rod body of the first driving oil cylinder 32 is installed on the middle turning plate 31 through a support. When in use, through the telescopic action of the first driving oil cylinder 32, the middle turning plate 31 is driven to turn up and put down.

[0056] Please refer to Figures 4 to 6 , Figure 4 for the structural diagram of the fairing working platform in the asymmetric launch vehicle working platform provided by the embodiment of the present application, Figure 5 for Figure 4 the structural diagram of the fairing working platform when it is turned up in Figure 6 for Figure 4 the structural diagram of a platform plate in

[0057] As Figure 4 shown, different from Figure 1 , in some embodiments, the working platform further includes a fairing working platform 2. The fairing working platform 2 includes two platform plates, and the two platform plates of the fairing working platform 2 are arranged symmetrically. Large turning plate devices 4 are arranged on both of the two platform plates of the fairing working platform 2. The large turning plate device 4 includes a large turning plate 41 and a driving member for driving the large turning plate 41 to turn in the vertical direction. The inner edges of the two large turning plates 41 jointly form an area surrounding the rocket fairing. Among them, the fairing has the same meaning as the star fairing. The large turning plate device 4 can avoid interference between the swinging process of the working platform and the rocket and the fairing spreader.

[0058] It should be noted that the middle flap 31 on the boost and core first-stage working platform 1 is equivalent to a partial flip of the platform board of this part of the working platform, while the large flap 41 on the fairing working platform 2 is equivalent to a complete flip of the platform board of this part of the working platform. The two are different in the form of flipping.

[0059] Furthermore, the large flap device 4 is provided with a pin locking mechanism, which can lock the movement after the flap flips in place.

[0060] Please refer to Figure 7 , Figure 7 for Figure 4 the structural diagram of the large flap device during the flipping movement in

[0061] In some cases, as Figure 7 shown, the driving part of the large flap device 4 is selected as the second driving oil cylinder 42, and the large flap device 4 further includes a second rotating hinge seat 43. The cylinder block of the second driving oil cylinder 42 is installed on the platform board of the fairing working platform 2 through a support, the large flap 41 is rotatably installed on the platform board of the fairing working platform 2 through the second rotating hinge seat 43, and the rod body of the second driving oil cylinder 42 is installed on the large flap 41 through a support. During use, the large flap 41 is driven to turn up and down by the telescopic action of the second driving oil cylinder 42.

[0062] Please continue to refer to Figure 1 and Figure 4 , and also refer to Figure 8 , Figure 8 which is the structural diagram of the small flap device provided by the embodiment of the present application.

[0063] As Figure 8 shown, in some embodiments, the boost and core first-stage working platform 1 and / or the fairing working platform 2 are provided with a small flap device 5, and the small flap device 5 includes a small flap that can flip in the vertical direction.

[0064] As Figure 1 shown, when the boost and core first-stage working platform 1 is provided with the small flap device 5, the small flap is located at the position where the platform board of the boost and core first-stage working platform 1 surrounds the rocket. As Figure 4 shown, when the fairing working platform 2 is provided with the small flap device 5, the small flap is located at the position where the platform board of the fairing working platform 2 surrounds the rocket.

[0065] In this embodiment, the small flap device 5 has a closing function. When the small flap device 5 flips up to close, it can avoid interference with the rocket during the movement of the working platform. After the fixed service tower slewing platform closes in place, it is necessary to deploy the small flap device 5 to facilitate the staff to approach the rocket for work.

[0066] In some cases, when the large, medium, and small flap groups are deployed and lowered, the distance between the flaps and the rocket is 250 mm. When all the flaps are closed and turned up, the distance between the working platform's turning path and the rocket is 400 mm.

[0067] It should be noted that except for the lifting of the fixed service tower's turning platform and the small flaps at the platform edge that require on-site operation by personnel, the deployment and closing actions can be automatically controlled.

[0068] In some embodiments, the working platform further includes a wire rope pulling device 6, and the wire rope pulling device 6 is arranged on the booster and core first-stage working platform 1 and / or the fairing working platform 2.

[0069] As Figure 1 shown, when the wire rope pulling device 6 is arranged on the booster and core first-stage working platform 1, the wire rope of the wire rope pulling device 6 is connected to the platform plate of the booster and core first-stage working platform 1. As Figure 4 shown, when the wire rope pulling device 6 is arranged on the fairing working platform 2, the wire rope of the wire rope pulling device 6 is connected to the platform plate of the fairing working platform 2. By the wire rope pulling device 6, the continuous load of the second driving oil cylinder 42 is reduced, and the overall safety is improved.

[0070] In some cases, the platform plates of the booster and core first-stage working platform 1 and the fairing working platform 2 are made of patterned aluminum plates. The working platform is designed with a steel structure. After all the steel materials meet the requirements of shape tolerances, they must be sandblasted or shot-peened before feeding; the outer surfaces of all post-weld annealing parts must be spray-rusted.

[0071] Please refer to Figure 9 and Figure 10 , Figure 9 which is the structural diagram of the lifting device provided by the embodiment of the present application, Figure 10 and Figure 9 is the structural diagram of the relay pin when it is locked in

[0072] In some embodiments, the working platform further includes a lifting device 7, and the lifting device 7 is used to adjust the height of the platform plate of the booster and core first-stage working platform 1 and / or the platform plate of the fairing working platform 2.

[0073] In this embodiment, the height of the working platform is adjusted by the lifting device 7 to adapt to different working positions. Further, when some working platforms rise to the upper limit elevation, the working position is above the booster. At this time, a large hole will appear in the original position of the booster. A safety net and railing are used to restrict access to this area by personnel.

[0074] In some cases, the boost and core first-stage working platform 1 can adapt to the boost in the rocket's I and III quadrants, and the fairing working platform 2 can adapt to rockets with different core diameters. If other rocket models need to be launched, the platform plates of the boost and core first-stage working platform 1 and the fairing working platform 2 can be replaced to meet the hole requirements. Interfaces have been reserved in advance on the hydraulic pipelines according to subsequent requirements.

[0075] In some embodiments, the lifting device 7 includes a relay pin 71 and a climbing oil cylinder 72, and the height adjustment is achieved by inserting and removing the relay pin 71 and coordinating with the telescopic stroke of the climbing oil cylinder 72.

[0076] In this embodiment, the lifting device 7 is composed of a relay pin 71 and a climbing oil cylinder 72. The relay pin 71 can be manually inserted and removed, and it coordinates with the small-stroke telescoping of the oil cylinder 72. The modulus of each lifting distance is 200 mm, and the maximum single lifting distance is 800 mm. The working platforms do not cross each other.

[0077] In some cases, the rising speed of the working platform is not greater than 3 m / min, and the falling speed is not greater than 2 m / min; the acceleration of the working platform during lifting and lowering is not greater than 0.1g.

[0078] Please refer to Figure 11 and Figure 12 , Figure 11 which is the structural diagram of the guide rail layout position provided by the embodiment of the present application, Figure 12 and which is the structural diagram of the guiding device provided by the embodiment of the present application.

[0079] In some embodiments, the working platform further includes a guiding device 8, and the guiding device 8 is used to guide the platform plates of the boost and core first-stage working platform 1 and / or the fairing working platform 2 to move up and down along the height.

[0080] In the present application, taking the boost and core first-stage working platform 1 as an example, the platform plate of the boost and core first-stage working platform 1 is installed on the lifting frame body, and the lifting frame body is movably assembled with the guiding device 8, and the guiding device 8 provides a movement limiting effect on the platform plate of the boost and core first-stage working platform 1.

[0081] In some embodiments, the guiding device 8 includes a guide rail 81, a vertical guiding wheel 82 and a horizontal guiding wheel 83. The guide rail 81 is fixed on the fixed service tower revolving platform, and the vertical guiding wheel 82 and the horizontal guiding wheel 83 are installed on the platform plate, and the vertical guiding wheel 82 and the horizontal guiding wheel 83 cooperate with the guide rail 81.

[0082] As an option, the guide rail 81 is screwed to the two-section fixed service tower revolving platform and is a through-length guide rail. Guide wheels are arranged on the upper and lower parts of the column of the working platform to play a guiding role during the lifting and lowering of the working platform.

[0083] In some embodiments, two sets of guiding devices 8 are respectively arranged on two symmetric sides of the working platform, and the installation position and number of the lifting device 7 correspond to those of the guiding device 8.

[0084] In a specific embodiment, the working process includes the following implementation steps: Check whether there is interference and redundant objects around the working platform, evacuate personnel from the working platform and only leave the operator, confirm that the relay pin 71 at the lower part of the climbing oil cylinder 72 is firmly inserted, pull out the relay pin 71 at the upper part of the climbing oil cylinder 72, extend the climbing oil cylinder 72, firmly insert the relay pin 71 at the upper part of the climbing oil cylinder 72, slightly contract the climbing oil cylinder 72 until the relay pin 71 at the upper part is stressed and the relay pin 71 at the lower part is unloaded, pull out the relay pin 71 at the lower part, contract the climbing oil cylinder 72 to drive the platform to rise together, insert the relay pin 71 at the lower part, slightly extend the climbing oil cylinder 7 until the relay pin 71 at the lower part is stressed and the relay pin 71 at the upper part is unloaded, pull out the relay pin 71 at the upper part to complete one oil cylinder crawl, and repeat the above actions for continuous lifting.

[0085] Compared with the prior art, the present application has at least the following beneficial effects. The asymmetric carrier rocket working platform provided by the present application can adapt to rockets with two boosters tied. Two middle turning plates driven by small oil cylinders are provided to avoid interference between the working platform and the rocket. This solution reduces the self-weight compared with the previous symmetric platform design, reduces the requirement for the working space, reduces the number of drives, and simplifies the control. The working platform realizes automatic height adjustment through the lifting mechanism and realizes guiding during the movement process through the roller mechanism. Compared with the previous working platform, a crane is no longer used, which simplifies the operation steps, reduces the operation difficulty of the staff, and improves the safety of the working platform.

[0086] In summary, the present application provides an asymmetric carrier rocket working platform, which can provide support for the connection and testing of the rocket-ground interface. The working platform is connected to the rotary platform of the fixed service tower. During the rocket preparation and launch stage, the working platform swings away with the rotary platform of the fixed service tower to make space for the rocket to take off. This working platform has a lifting function and can meet the working requirements at different elevation positions. Compared with the original fixed service tower rotary platform, the present application optimizes the movement process, reduces the demand for operators, improves the safety of the launch mission, and is more conducive to promoting the rapid development of commercial spaceflight.

[0087] It should be noted that many components mentioned in the present application are common standard components or components known to those skilled in the art, and their structures and principles can be known by those skilled in the art through technical manuals or obtained through conventional experimental methods.

[0088] It should be noted that in this specification, relational terms such as first and second are only used to distinguish one entity from several other entities, and do not necessarily require or imply any actual relationship or order between these entities.

[0089] The above has introduced in detail the asymmetric launch vehicle working platform provided by this application. Specific examples are used in this article to elaborate on the principle and implementation manner of this application. The description of the above embodiments is only used to help understand the method and its core idea of this application. It should be pointed out that for those of ordinary skill in the art in this technical field, without departing from the principle of this application, several improvements and modifications can still be made to this application, and these improvements and modifications also fall within the protection scope of the claims of this application.

Claims

1. An asymmetric launch vehicle working platform, characterized in that, The working platform is used to be installed on the slewing platform of the fixed service tower. The working platform can swing horizontally together with the slewing platform of the fixed service tower. The working platform includes a booster and core stage 1 working platform, and the booster and core stage 1 working platform includes two platform plates. The two platform plates of the booster and core stage 1 working platform are used to surround and bind the rocket with two boosters when swinging and closing in the horizontal direction. The two platform plates of the booster and core stage 1 working platform are arranged in an asymmetric form. At least one mid-flipping plate device is provided on one of the platform plates of the booster and core stage 1 working platform. The mid-flipping plate device includes a mid-flipping plate and a driving member for driving the mid-flipping plate to flip in the vertical direction. The inner edge of the mid-flipping plate and the remaining inner ring position of the platform plate of the booster and core stage 1 working platform together form an area for surrounding and binding the rocket with two boosters. The working platform further includes a fairing working platform, and the fairing working platform includes two platform plates. The two platform plates of the fairing working platform are arranged symmetrically. Large flipping plate devices are provided on both of the two platform plates of the fairing working platform. The large flipping plate device includes a large flipping plate and a driving member for driving the large flipping plate to flip in the vertical direction. The inner edges of the two large flipping plates together form an area for surrounding the rocket fairing.

2. The asymmetric carrier rocket working platform according to claim 1, characterized in that The number of the mid-flipping plate devices is two, and the two mid-flipping plate devices are arranged adjacent to each other. The two mid-flipping plates form a splicing in the horizontal direction.

3. The asymmetric launch vehicle working platform according to claim 1, characterized in that, The booster and core stage 1 working platform and / or the fairing working platform is provided with a small flipping plate device, and the small flipping plate device includes a small flipping plate that can flip in the vertical direction. When the booster and core stage 1 working platform is provided with a small flipping plate device, the small flipping plate is located at the position where the platform plate of the booster and core stage 1 working platform surrounds the rocket; when the fairing working platform is provided with a small flipping plate device, the small flipping plate is located at the position where the platform plate of the fairing working platform surrounds the rocket.

4. The asymmetric carrier rocket working platform according to claim 1, wherein The working platform further includes a wire rope pulling device, and the wire rope pulling device is arranged on the booster and core stage 1 working platform and / or the fairing working platform. When the booster and core stage 1 working platform is provided with a wire rope pulling device, the wire rope cable of the wire rope pulling device is connected to the platform plate of the booster and core stage 1 working platform; when the fairing working platform is provided with a wire rope pulling device, the wire rope cable of the wire rope pulling device is connected to the platform plate of the fairing working platform.

5. The asymmetric launch vehicle working platform according to claim 1, wherein The working platform further includes a lifting device, and the lifting device is used to adjust the height of the platform plate of the booster and core stage 1 working platform and / or the platform plate of the fairing working platform.

6. The asymmetric launch vehicle working platform according to claim 5, characterized in that, The lifting device includes a relay pin and a climbing oil cylinder, and the height adjustment is realized by inserting and pulling out the relay pin and coordinating with the telescopic stroke of the above climbing oil cylinder.

7. The asymmetric launch vehicle working platform according to claim 5, wherein, The working platform further includes a guiding device, and the guiding device is used to guide the platform plate of the booster and core stage 1 working platform and / or the platform plate of the fairing working platform to move up and down along the height.

8. The asymmetric launch vehicle working platform according to claim 7, characterized in that, The guiding device includes a guide rail, a vertical guiding wheel and a horizontal guiding wheel. The guide rail is fixed on the rotary platform of the fixed service tower. The vertical guiding wheel and the horizontal guiding wheel are installed on the platform plate, and the vertical guiding wheel and the horizontal guiding wheel cooperate with the guide rail.

9. The asymmetric launch vehicle working platform according to claim 8, characterized in that, Two sets of the guiding devices are respectively arranged on the two symmetric sides of the working platform, and the installation position and the installation quantity of the lifting device correspond to those of the guiding device.

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