Transfer tooling for launch vehicle launch pad

Abstract

The embodiment of the present application provides a transfer tool for a launch platform of a carrier rocket, which is used for a launch platform of a liquid carrier rocket. The transfer tool includes: a tool body assembly, which is annular; at least three docking components, which are arranged equidistantly along the circumference of the tool body assembly, are all arranged on one side of the axial direction of the tool body assembly, and are constructed to be detachably connected to the original launch platform; at least three rocket body support seats, plug-in and unplug components, contact feedback components, and charging and discharging connector brackets, are all arranged on the side of the tool body assembly away from the docking components along the axial direction of the tool body assembly; at least three rocket body support seats are arranged equidistantly along the circumference of the tool body assembly. Therefore, when launching different types of carrier rockets, it is only necessary to install the corresponding type of transfer tool on the original carrier rocket launch platform to realize the launch of the carrier rocket, without the need to build multiple carrier rocket launch platforms, thereby shortening the launch cycle in the early stage of carrier rocket development and reducing costs.

Description

Technical Field

[0001] The present application relates to the field of launch vehicle technology, and more specifically, to a transfer tooling for a launch vehicle launch platform. Background Art

[0002] The existing launch pad for carrier rockets includes: mechanical system, hydraulic system, electrical system and accessories, etc. The mechanical system usually includes: base, rotating part, support arm and work table, etc.; the hydraulic system usually includes: oil source, hydraulic control box, hydraulic motor, cylinder and pipeline, etc.; the electrical system usually includes: control cabinet, transfer control box, oil source control box, control software, sensor and cable network, etc.; the accessories usually include: contact bracket and extraction bracket, etc., which makes the structure of the launch pad of carrier rockets complicated.

[0003] Moreover, an existing launch vehicle launch pad can usually only be used to launch one type of launch vehicle, resulting in the need to build different launch vehicle launch pads for launching different types of launch vehicles, which leads to long launch cycles and high costs in the early stages of launch vehicle development. Summary of the invention

[0004] In view of the shortcomings of the existing methods, the present application proposes a transfer tooling for a carrier rocket launch pad to solve the technical problem in the prior art that a carrier rocket launch pad can only be used for launching one type of carrier rocket.

[0005] The embodiment of the present application provides a transfer tool for a launch platform of a carrier rocket, which is used for a launch platform of a liquid carrier rocket, including:

[0006] The tooling main body component is ring-shaped;

[0007] At least three docking members are arranged equidistantly along the circumference of the tooling main assembly, are all arranged on one axial side of the tooling main assembly, and are constructed to be detachably connected to the original launch platform of the carrier rocket;

[0008] At least three arrow body support seats, a plug-in / plug-out assembly, a contact feedback assembly, and a charging / draining connector bracket are all arranged along the axial direction of the tooling main assembly on the side of the tooling main assembly away from the docking component; at least three arrow body support seats are arranged equidistantly along the circumference of the tooling main assembly.

[0009] Optionally, the contact feedback component includes:

[0010] First base;

[0011] A flip member, the flip member is rotatably connected to the first base;

[0012] A torsion spring abuts between the flip member and the first base;

[0013] A pressing member, located at an end of the flip member away from the first base, and partially located in the first cavity on a side of the flip member away from the first base;

[0014] The elastic member is arranged in the first cavity, and in a compressed state, enables the radial through hole of the pressing member to communicate with the radial through hole of the flip member.

[0015] Optionally, the flip member includes a first part;

[0016] The first part and the first base are both U-shaped in a plane parallel to the axial plane of the tooling main body component; the opening of the first part and the opening of the first base are aligned to form a receiving space and are hinged; the torsion spring is located in the receiving space;

[0017] When the extension direction of the flip member is parallel to the axial direction of the tooling main body assembly, the torsion spring is in a torsion state;

[0018] When the extending direction of the flip member is perpendicular to the axial direction of the tooling main body assembly, the torsion spring is in a free state.

[0019] Optionally, the flip member further comprises a second portion arranged on a side of the first portion away from the first base;

[0020] When the extension direction of the flip member is parallel to the axial direction of the tooling main body component, the second portion is rectangular in a plane parallel to the axial plane of the tooling main body component; the second portion includes the first cavity.

[0021] Optionally, the unplugging and unplugging assembly includes an unplugging and unplugging base, a screw and a butterfly nut; the unplugging and unplugging base is provided with a first through hole, the first through hole is configured for the screw and the unplugging and unplugging cable to pass through, the screw is connected to the butterfly nut for adjusting the position of the unplugging and unplugging cable.

[0022] Optionally, the tooling main body assembly includes:

[0023] At least two docking rings, all of which are connected end to end in radial order to form a circular ring-shaped component;

[0024] A docking plate is provided at both ends of each docking ring, and the docking plates of two adjacent docking rings are fixedly connected.

[0025] Optionally, the docking component comprises a docking component bottom plate and a docking component base which are sequentially away from the tooling main body component and connected to each other;

[0026] Along the axial direction of the tooling main body assembly, a second cavity is formed between the bottom plate of the docking component and the base of the docking component; the base of the docking component is provided with a second through hole, the second through hole is connected to the second cavity, and the second through hole is constructed to allow a connecting piece to pass through, so as to be detachably connected between the docking component and the original carrier rocket launch platform.

[0027] Optionally, the add-drain connector bracket comprises a bracket base and a bracket mounting plate which are sequentially away from the tooling main body component and connected to each other; a third through hole is provided on the bracket mounting plate; the third through hole is configured to allow the add-drain connector pipeline to pass through;

[0028] Along the radial direction of the tooling main body assembly, the third through hole of the bracket mounting plate is located on a side of the bracket mounting plate away from the bracket base.

[0029] Optionally, an operation interface is also included; the operation interface is arranged around and fixed on the periphery of the tooling main body component.

[0030] Optionally, the arrow body support seat comprises a support seat base and a support plate which are sequentially away from the tooling main body assembly and connected to each other; the support seat base is provided with a through groove, and the through groove is connected to the fourth through hole of the support plate;

[0031] In a plane parallel to the radial plane of the tooling main body component, the orthographic projection of the periphery of the fourth through hole of the support plate is located within the projection range of the through groove of the support seat base.

[0032] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include:

[0033] The transfer tooling of the carrier rocket launch pad provided in the embodiment of the present application, the rocket body support seat, the plug-in / plug-out assembly, the contact feedback assembly, and the charging / discharging connector bracket are all arranged on the same axial side of the tooling main body assembly, and the docking component is arranged on the side of the tooling main body assembly away from the rocket body support seat; at least three rocket body support seats are arranged equidistantly along the circumference of the tooling main body assembly, and at least three docking components are arranged equidistantly along the circumference of the tooling main body assembly, and the docking components are detachably connected to the original carrier rocket launch pad, so that the transfer tooling is detachably connected to the original carrier rocket launch pad; when launching different types of carrier rockets, it is only necessary to install different transfer tooling on the original carrier rocket launch pad to realize that one carrier rocket launch pad can launch different types of carrier rockets, thereby shortening the launch cycle in the early stage of carrier rocket development and reducing the launch cost.

[0034] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0036] Figure 1 A schematic diagram of the connection relationship between a transfer tooling of a carrier rocket launch pad and the tail end of a carrier rocket provided in an embodiment of the present application;

[0037] Figure 2 A schematic diagram of the structure of a transfer tooling for a launch vehicle launch pad provided in an embodiment of the present application;

[0038] Figure 3 This is a schematic diagram of the structure of the tooling main body assembly in the embodiment of the present application;

[0039] Figure 4 This is a schematic diagram of the connection relationship between the docking ring and the docking plate in the embodiment of the present application;

[0040] Figure 5 This is a schematic diagram of the structure of the contact feedback mechanism in the embodiment of the present application;

[0041] Figure 6 A side view of the contact feedback mechanism in an embodiment of the present application;

[0042] Figure 7 for Figure 6 Section view along AA direction;

[0043] Figure 8 This is a schematic diagram of the structure of the plug-in / plug-out assembly in the embodiment of the present application;

[0044] Fig. 9 This is a structural schematic diagram of a docking component in an embodiment of the present application;

[0045] Fig.10 This is a schematic diagram of the structure of the adding and discharging connector bracket in the embodiment of the present application;

[0046] Fig.11 This is a schematic diagram of the structure of the arrow body support seat in the embodiment of the present application.

[0047] Reference numerals:

[0048] 10-Transfer tooling;

[0049] 11- tooling main assembly;

[0050] 111- docking ring; 1111- outer sealing plate; 1112- upper sealing plate; 1113- inner sealing plate; 1114- lower sealing plate;

[0051] 112- docking plate; 113- contact feedback assembly mounting plate; 114- plug-and-disconnect assembly mounting plate; 115- docking component mounting seat; 116- add-drain connector bracket mounting plate; 117- arrow body mounting plate;

[0052] 12-Contact feedback assembly;

[0053] 121- first base;

[0054] 122- flip member; 1221- first part of the flip member; 1222- second part of the flip member; 12221- first cavity of the second part of the flip member;

[0055] 123-torsion spring; 124-pressing member; 125-elastic member; 126-second base; 127-pin shaft;

[0056] 13- plug and unplug assembly;

[0057] 131 - a first through hole of the insertion / removal substrate; 1311 - a first through hole of the insertion / removal substrate;

[0058] 132-screw; 133-butterfly nut;

[0059] 14- docking member;

[0060] 141- docking member bottom plate;

[0061] 142-a docking component base; 1421-a second through hole of the docking component base;

[0062] 143 - second cavity; 144 - docking member rib;

[0063] 15-addition and discharge connector bracket; 151-bracket base; 152-bracket mounting plate; 1521-third through hole of the bracket mounting plate; 153-bracket bottom plate; 154-bracket rib plate;

[0064] 16-rocket body support seat; 161-support seat base; 1611-through groove of the support seat base; 162-support plate; 1621-fourth through hole of the support plate; 163-support seat bottom plate; 164-support seat rib plate;

[0065] 17- Operation interface;

[0066] 20-Tail end of launch vehicle. DETAILED DESCRIPTION

[0067] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0068] Those skilled in the art will appreciate that, unless expressly stated otherwise, the singular forms "a", "an", "said" and "the" used herein may also include plural forms. It should be further understood that the term "comprising" used in the specification of the present application refers to the presence of the features, integers, steps, operations, elements and / or components, but does not exclude the implementation of other features, information, data, steps, operations, elements, components and / or combinations thereof supported by the technical field. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" may be implemented as "A", or as "B", or as "A and B".

[0069] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0070] The existing launch pad for carrier rockets includes: mechanical system, hydraulic system, electrical system and accessories, etc. The mechanical system usually includes: base, rotating part, support arm and work table, etc.; the hydraulic system usually includes: oil source, hydraulic control box, hydraulic motor, cylinder and pipeline, etc.; the electrical system usually includes: control cabinet, transfer control box, oil source control box, control software, sensor and cable network, etc.; the accessories usually include: contact bracket and extraction bracket, etc., which makes the structure of the launch pad of carrier rockets complicated.

[0071] Moreover, an existing launch vehicle launch pad can usually only be used to launch one type of launch vehicle, resulting in the need to build different launch vehicle launch pads for launching different types of launch vehicles, which leads to long launch cycles and high costs in the early stages of launch vehicle development.

[0072] The following is a detailed description of the technical solution of the present application and how the technical solution of the present application solves the above technical problems with specific embodiments. It should be noted that the following implementations can refer to, draw on or combine with each other, and the same terms, similar features and similar implementation steps in different implementations will not be described repeatedly.

[0073] The present application embodiment provides a transfer tool 10 for a launch vehicle launch platform, see Figure 1-11 As shown, the adapter tool 10 is used for a liquid carrier rocket launch platform, and includes: a tool main body component 11, a contact feedback component 12, a plug-in and unplug component 13, a docking component 14, a charging and discharging connector bracket 15, and a rocket body support seat 16.

[0074] The tooling main body component 11 is ring-shaped.

[0075] At least three docking components 14 are arranged equidistantly along the circumference of the tooling main body component 11, are all arranged on one axial side of the tooling main body component 11, and are constructed to be detachably connected to the original carrier rocket launch platform.

[0076] At least three arrow body support seats 16, the plug-in and unplug assembly 13, the contact feedback assembly 12, and the filling and draining connector bracket 15 are all arranged along the axial direction of the tooling main body assembly 11 on the side of the tooling main body assembly 11 away from the docking component 14; at least three arrow body support seats 16 are arranged equidistantly along the circumference of the tooling main body assembly 11.

[0077] The transfer tooling 10 of the launch platform of the carrier rocket provided in the embodiment of the present application, the rocket body support seat 16, the plug-in and unplug assembly 13, the contact feedback assembly 12, and the charging and discharging connector bracket 15 are all arranged on the same axial side of the tooling main body assembly 11, and the docking component 14 is arranged on the side of the tooling main body assembly 11 away from the rocket body support seat 16; at least three rocket body support seats 16 are arranged equidistantly along the circumference of the tooling main body assembly 11, and at least three docking components 14 are arranged equidistantly along the circumference of the tooling main body assembly 11, and the docking components 14 are connected to the original carrier rocket. The launch pad is detachably connected, so that the transfer tooling 10 is detachably connected to the original carrier rocket launch pad; when launching different types of carrier rockets, it is only necessary to install different transfer tooling 10 on the original carrier rocket launch pad, and at the same time, mechanical interfaces, electrical interfaces and filling interfaces are reserved on the transfer tooling 10, so that one carrier rocket launch pad can launch different types of carrier rockets, thereby shortening the launch cycle in the early stage of carrier rocket development, reducing launch costs, and improving the utilization rate of the original carrier rocket launch pad.

[0078] Optionally, in the embodiment of the present application, the docking member 14 is detachably connected to the body support seat of the original carrier rocket launch platform. Before the transfer tool 10 is installed on the original carrier rocket launch platform, the upper surface of the body support seat of the original carrier rocket launch platform is first leveled using the leveling system of the original carrier rocket launch platform to prevent the flatness of the upper surface of the body support seat of the original carrier rocket launch platform from affecting the flatness of the docking member 14 of the transfer tool 10; then the transfer tool 10 is hoisted to the top of the original carrier rocket launch platform, and each docking member 14 of the transfer tool 10 is aligned with the body support seat of the original carrier rocket launch platform one by one, and the docking member 14 is fixed to the body support seat of the original carrier rocket launch platform by a connecting piece, and the connecting piece includes a bolt. An inclination sensor is used to measure the side of the arrow body support seat 16 of the adapter tooling 10 away from the tooling main body assembly 11. The measured content includes the lateral inclination angle and the longitudinal inclination angle. According to the measured values ​​of the lateral inclination angle and the longitudinal inclination angle, adjustments are made by adding gaskets so that the sides of each arrow body support seat 16 away from the tooling main body assembly 11 are basically coplanar.

[0079] In the embodiment of the present application, the contact feedback assembly 12, the plug-in / plug-out assembly 13, the docking member 14, the charging / discharging connector bracket 15, and the arrow body support seat 16 are all detachably connected to the tooling main body assembly 11, so as to facilitate replacement.

[0080] Optionally, in one embodiment of the present application, see Figure 1 and Figure 5-7 As shown, the contact feedback assembly 12 includes: a first base 121 , a flip member 122 , a torsion spring 123 , a pressing member 124 , and an elastic member 125 .

[0081] The flip member 122 is rotatably connected to the first base 121 .

[0082] The torsion spring 123 is abutted between the flip member 122 and the first base 121 .

[0083] The pressing member 124 is located at one end of the flip member 122 away from the first base 121 , and is partially located in the first cavity 12221 on the side of the flip member 122 away from the first base 121 .

[0084] The elastic member 125 is disposed in the first cavity 12221 , and in a compressed state, enables the radial through hole of the pressing member 124 to communicate with the radial through hole of the flip member 122 .

[0085] In the embodiment of the present application, the contact feedback assembly 12 also includes a second base 126. One end of the second base 126 is detachably connected to the tooling main body assembly 11, and the other end is detachably connected to the first base 121. The flip member 122 is rotatably connected to the first base 121, the torsion spring 123 abuts between the flip member 122 and the first base 121, and the pressing member 124 is partially located in the first cavity 12221 of the flip member 122; the elastic member 125 is arranged in the first cavity 12221, and when the elastic member 125 is in a free state, one end of the elastic member 125 contacts the pressing member 124, and the other end contacts the bottom wall of the first cavity 12221; when the elastic member 125 is in a compressed state, the radial through hole of the pressing member 124 is connected to the radial through hole of the flip member 122. The elastic member 125 includes a compression spring.

[0086] Before the rocket body of the carrier rocket is erected to the right position, the elastic member 125 is in a compressed state through the pressing member 124, and the quick release pin passes through the radial through hole of the flip member 122 and the radial through hole of the pressing member 124 in sequence, thereby locking the flip member 122 and the pressing member 124, so that the elastic member 125 is in a compressed state; after the rocket body of the carrier rocket is erected to the right position, the quick release pin is unlocked, and the pressing member 124 moves toward the rocket body under the action of the elastic member 125, so that the pressing member 124 abuts against the time sensor at the bottom of the rocket body. Since the magnitude of the force between the pressing member 124 and the time sensor is related to the elastic member 125, the force between the pressing member 124 and the time sensor can be adjusted by adjusting the relevant parameters of the elastic member 125.

[0087] Optionally, in one embodiment of the present application, see Figure 5-7 As shown, the flip member 122 includes a first portion 1221. The first portion 1221 and the first base 121 are both U-shaped in a plane parallel to the axial plane of the tooling body assembly 11; the opening of the first portion 1221 is aligned with the opening of the first base 121 to form an accommodation space, and is hinged; the torsion spring 123 is located in the accommodation space.

[0088] When the extending direction of the flip member 122 is parallel to the axial direction of the tooling main body assembly 11 , the torsion spring 123 is in a torsion state.

[0089] When the extending direction of the flip member 122 is perpendicular to the axial direction of the tooling main body assembly 11 , the torsion spring 123 is in a free state.

[0090] In the embodiment of the present application, before the rocket body of the carrier rocket is erected in place, the pressing piece 124 is locked by the quick release pin, so that the elastic piece 125 is always in a compressed state; after the rocket body of the carrier rocket is erected in place, the quick release pin is unlocked, and the elastic piece 125 pushes the pressing piece 124 to move in the direction close to the rocket body until the pressing piece 124 abuts against the time sensor at the bottom of the rocket body, so that the contact feedback component 12 can be docked with the rocket body without the need for special tools. Moreover, since the magnitude of the force between the pressing piece 124 and the time sensor can be reflected by the deformation of the elastic piece 125, the force between the pressing piece 124 and the time sensor can be accurately designed by the elastic piece 125.

[0091] In the embodiment of the present application, the torsion spring 123 is located between the first portion 1221 of the flip member 122 and the first base 121. Before the rocket body of the carrier rocket is erected, the elastic member 125 is in a compressed state, and the pressing member 124 is locked by the quick release pin; under the action of external force, the flip member 122 gradually changes from a state perpendicular to the axial direction of the tooling main assembly 11 to a state parallel to the axial direction of the tooling main assembly 11. During this process, the torsion spring 123 is in a torsion state, and the torsion spring 123 accumulates a certain torque or rotational force. After the rocket body of the carrier rocket is erected, the quick release pin is unlocked, and the pressing member 124 abuts against the time sensor at the bottom of the rocket body. There is friction between the pressing member 124 and the time sensor, so that the pressing member 124 and the time sensor remain stationary, so that the extension direction of the flip member 122 remains parallel to the axial direction of the tooling main assembly 11. When the launch vehicle ignites and just starts to take off, the pressing piece 124 loses contact with the timing sensor, and the torsion spring 123 immediately drives the flip piece 122 to rotate to a state perpendicular to the axial direction of the tooling main body assembly 11, thereby preventing the contact feedback assembly 12 from being burned and allowing the contact feedback assembly 12 to be reused.

[0092] In the embodiment of the present application, through holes are provided at corresponding positions of the first part 1221 of the flip member 122 and the first base 121, and the pin shaft 127 passes through the through hole of the first base 121 and the through hole of the first part 1221 in sequence, so that the first part 1221 and the first base 121 can rotate relative to each other.

[0093] Optionally, in one embodiment of the present application, see Figure 5-7 As shown, the flip member 122 further includes a second portion 1222 disposed on a side of the first portion 1221 away from the first base 121 .

[0094] When the extension direction of the flip member 122 is parallel to the axial direction of the tooling main body assembly 11 , the second portion 1222 is rectangular in a plane parallel to the axial plane of the tooling main body assembly 11 ; the second portion 1222 includes a first cavity 12221 .

[0095] In the embodiment of the present application, the second part 1222 of the flip member 122 includes a hollow cylindrical shape, the first part 1221 includes a U shape, the second part 1222 includes a first cavity 12221, the opening direction of the first cavity 1222 is opposite to the U-shaped opening direction of the first part 1221, the first part 1221 interacts with the torsion spring 123 and the first base 121, so that the torsion spring 123 can drive the flip member 122 to rotate; the pressing member 124, the elastic member 125 interact with the second part 1222, so that the pressing member 124 can abut against the timing sensor at the bottom of the arrow body. Therefore, the contact feedback component 12 can complete the docking with the arrow body without special tools, which is simple to operate, saves time and reduces costs.

[0096] Optionally, in one embodiment of the present application, see Figure 1 and Figure 8 As shown, the unplugging assembly 13 includes an unplugging base 131, a screw 132 and a butterfly nut 133; the unplugging base 131 is provided with a first through hole 1311, and the first through hole 1311 is constructed to allow the screw 132 and the unplugging cable to pass through, and the screw 132 is connected to the butterfly nut 133 for adjusting the position of the unplugging cable.

[0097] In the embodiment of the present application, the plug-in / plug-out base 131 is provided with a first through hole 1311, and the plug-in / plug-out cable of the original launch platform of the carrier rocket passes through the first through hole 1311 and is connected to the corresponding circuit of the rocket body, and the screw 132 passes through the first through hole 1311 and is connected to the butterfly nut 133. By tightening the butterfly nut 133, the size of the through hole 1311 is adjusted, so as to limit the plug-in / plug-out cable in the first through hole 1311. Moreover, the operation of tightening the butterfly nut 133 can be completed manually, which is easy to operate.

[0098] Optionally, in one embodiment of the present application, Figure 2-4 As shown, the tooling main body assembly includes: at least two docking rings 111 and a docking plate 112 .

[0099] At least two docking rings 111, all of which are connected end to end in sequence along the radial direction to form a circular ring-shaped component.

[0100] A docking plate 112 is provided at both ends of each docking ring 111 , and the docking plates 112 of two adjacent docking rings 111 are fixedly connected.

[0101] In the embodiment of the present application, the docking plate 112 connecting the two docking rings 111 can be fixedly connected by bolts.

[0102] In the embodiments of the present application, Figure 3-4 As shown, the docking ring 111 includes an outer sealing plate 1111, an upper sealing plate 1112, an inner sealing plate 1113 and a lower sealing plate 1114. The outer sealing plate 1111, the upper sealing plate 1112, the inner sealing plate 1113 and the lower sealing plate 1114 enclose a hollow docking ring 111. The docking ring 111 is designed as a hollow structure, which can reduce the weight of the docking ring 111. Along the radial direction of the tooling main body assembly 11, the inner sealing plate 1113 is closer to the center of the tooling main body assembly 11 than the outer sealing plate 1111. Along the axial direction of the tooling main body assembly, the upper sealing plate 1112 and the lower sealing plate 1114 are respectively located at the two ends of the inner sealing plate 1113 and the outer sealing plate 1111.

[0103] In the embodiments of the present application, Figure 3As shown, the tooling main body component 11 also includes: a contact feedback component mounting plate 113, a plug-in and plug-out component mounting plate 114, a docking component mounting seat 115, a charging and draining connector bracket mounting plate 116, and an arrow body mounting plate 117. The docking component mounting seat 115 is arranged on a side of the inner sealing plate 1113 away from the outer sealing plate 1111, and the mounting ends of the docking component mounting seat 115 and the docking component 14 are close to the lower sealing plate 1114. The arrow body mounting plate 117, the plug-in and plug-out component mounting plate 114, the contact feedback component mounting plate 113, and the charging and draining connector bracket mounting plate 116 are all arranged on a side of the upper sealing plate 1112 away from the lower sealing plate 1114.

[0104] Optionally, in one embodiment of the present application, see Figure 1 and Fig. 9 As shown, the docking component 14 includes a docking component bottom plate 141 and a docking component base 142 which are sequentially away from the tooling main body assembly 11 and connected to each other.

[0105] Along the axial direction of the tooling main body assembly 11, a second cavity 143 is formed between the docking component bottom plate 141 and the docking component base 142; the docking component base 142 is provided with a second through hole 1421, and the second through hole 1421 is connected to the second cavity 143. The second through hole 1421 is constructed for a connecting piece to pass through, so as to be detachably connected to the docking component 14 and the original carrier rocket launch platform.

[0106] In the embodiment of the present application, the docking member 14 also includes a docking member rib 144. The two adjacent side surfaces of the docking member rib 144, one side surface is fixedly connected to the docking member bottom plate 141, and the other side surface is fixedly connected to the docking member base 142, so that the connection between the docking member bottom plate 141 and the docking member base 142 is more secure.

[0107] In the embodiment of the present application, the connecting member includes a bolt, etc., and the second through hole 1421 is connected to the second cavity 143, so that the connecting member can be passed through the second through hole 1421, and the docking member 14 can be detachably connected to the original launch platform of the carrier rocket through bolts and nuts, so as to facilitate the replacement of the transfer tool 10.

[0108] In one embodiment of the present application, see Figure 1 and Fig.10 As shown, the add-drain connector bracket 15 includes a bracket base 151 and a bracket mounting plate 152 which are sequentially away from the tooling main body assembly 11 and connected to each other; a third through hole 1521 is provided on the bracket mounting plate 152; the third through hole 1521 is constructed to allow the add-drain connector pipeline to pass through.

[0109] Along the radial direction of the tooling main body assembly 11 , the third through hole 1521 of the bracket mounting plate 152 is located on a side of the bracket mounting plate 152 away from the bracket base 151 .

[0110] In the embodiment of the present application, the adding and discharging connector bracket 15 also includes a bracket bottom plate 153 and a bracket rib 154. The bracket bottom plate 153 is located on the side of the bracket base 151 away from the bracket mounting plate 152. The two adjacent side surfaces of the bracket rib 154, one side surface is fixedly connected to the bracket base 151, and the other side surface is fixedly connected to the bracket bottom plate 153, so that the connection between the bracket base 151 and the bracket bottom plate 153 is more secure.

[0111] The filling and draining connector is installed on the filling and draining connector bracket 15. The filling and draining connector is located on the side of the bracket mounting plate 152 away from the bracket base 151. The filling and draining connector is used to fill the launch vehicle. After the filling is completed, the filling and draining connector is removed.

[0112] In one embodiment of the present application, Figure 1-2 As shown, the transfer tooling 10 of the carrier rocket launch platform also includes an operation interface 17 ; the operation interface 17 is arranged around and fixed to the periphery of the tooling main body component 11 .

[0113] In an embodiment of the present application, an operation interface 17 is provided on the periphery of the tooling main body assembly 11, so that when an operator needs to operate on the transfer tooling 10 during the process of preparing for launch of the carrier rocket, the ladder can be hung on the operation interface 17, so that the operator can operate along the circumference of the tooling main body assembly 11.

[0114] Optionally, in one embodiment of the present application, see Figure 1 and Fig.11 As shown, the arrow body support seat 16 includes a support seat base 161 and a support plate 162 which are sequentially away from the tooling main body assembly 11 and connected to each other; the support seat base 161 is provided with a through groove 1611, and the through groove 1611 is connected to the fourth through hole 1621 of the support plate 162.

[0115] In a plane parallel to the radial plane of the tooling main body assembly 11 , the orthographic projection of the periphery of the fourth through hole 1621 of the support plate 162 is located within the projection range of the through groove 1611 of the support seat base 161 .

[0116] Optionally, the conducting direction or the extending direction of the through slot 1611 is parallel to the radial plane of the tooling main body assembly 11 , and the through slot 1611 is open at one side away from the tooling main body assembly 11 and is covered by the support plate 162 .

[0117] In the embodiment of the present application, the arrow body support seat 16 further includes a support seat bottom plate 163 and a support seat rib plate 164. The support seat bottom plate 163 is located on the side of the support seat base 161 away from the support plate 162, and the two adjacent side surfaces of the support seat rib plate 164, one side surface is fixedly connected to the support seat base 161, and the other side surface is fixedly connected to the support seat bottom plate 163, so that the connection between the support seat base 161 and the support seat bottom plate 163 is more firmly.

[0118] In the embodiment of the present application, after the rocket body is erected into place, the tail end 20 of the carrier rocket abuts against the support plate 162, and bolts are passed through the fourth through hole 1621 to detachably connect the windproof tie rod seat of the tail end 20 of the carrier rocket to the rocket body support seat 16, thereby increasing the stability of the carrier rocket. Before the carrier rocket is ignited and takes off, the bolts passing through the fourth through hole 1621 are removed.

[0119] By applying the embodiments of the present application, at least the following beneficial effects can be achieved:

[0120] 1. The transfer tooling 10 of the launch platform of the carrier rocket provided in the embodiment of the present application, the rocket body support seat 16, the plug-in assembly 13, the contact feedback assembly 12, and the charging and discharging connector bracket 15 are all arranged on the same axial side of the tooling main body assembly 11, and the docking member 14 is arranged on the side of the tooling main body assembly 11 away from the rocket body support seat 16; at least three rocket body support seats 16 are arranged equidistantly along the circumference of the tooling main body assembly 11, and at least three docking members 14 are arranged equidistantly along the circumference of the tooling main body assembly 11, and the docking member 14 is connected to the original carrier rocket The rocket launch platform is detachably connected, so that the adapter tool 10 is detachably connected to the original carrier rocket launch platform; when launching different types of carrier rockets, it is only necessary to install different adapter tools 10 on the original carrier rocket launch platform, and at the same time, mechanical interfaces, electrical interfaces and filling interfaces are reserved on the adapter tool 10, so that one carrier rocket launch platform can launch different types of carrier rockets, thereby shortening the launch cycle in the early stage of carrier rocket development, reducing launch costs, and improving the utilization rate of the original carrier rocket launch platform.

[0121] Those skilled in the art will appreciate that the various operations, methods, steps, measures, and schemes in the processes discussed in this application may be alternated, altered, combined, or deleted. Further, other steps, measures, and schemes in the various operations, methods, and processes discussed in this application may also be alternated, altered, rearranged, decomposed, combined, or deleted. Further, the steps, measures, and schemes in the prior art that are similar to those disclosed in this application may also be alternated, altered, rearranged, decomposed, combined, or deleted.

[0122] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the referred device or component must have a specific orientation, be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0123] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0124] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0125] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0126] It should be understood that, although the various steps in the flowchart of the accompanying drawings are displayed in sequence according to the indication of the arrows, the order of implementation of these steps is not limited to the order indicated by the arrows. Unless there is a clear description herein, in some implementation scenarios of the embodiments of the present application, the steps in each process can be performed in other orders according to demand. Moreover, some or all of the steps in each flow chart may include multiple sub-steps or multiple stages based on actual implementation scenarios. Some or all of these sub-steps or stages may be executed at the same time, or may be executed at different times in different scenarios at the execution time, and the execution order of these sub-steps or stages may be flexibly configured according to demand, and the embodiments of the present application do not limit this.

[0127] The above is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the scheme of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. A transfer tool for a launch vehicle launch platform, characterized in that: For liquid launch vehicle launch pads, including: The tooling main body component is ring-shaped; At least three docking members are arranged equidistantly along the circumference of the tooling main assembly, are all arranged on one axial side of the tooling main assembly, and are constructed to be detachably connected to the original launch platform of the carrier rocket; At least three arrow body support seats, a plug-in / plug-out assembly, a contact feedback assembly, and a charging / discharging connector bracket are all arranged along the axial direction of the tooling main assembly on a side of the tooling main assembly away from the docking member; at least three arrow body support seats are arranged equidistantly along the circumference of the tooling main assembly; The contact feedback component comprises: First base; A flip member, the flip member is rotatably connected to the first base, the flip member includes a first part, the first part and the first base are both U-shaped in a plane parallel to the axial plane of the tooling main body component; the opening of the first part is aligned with the opening of the first base to form an accommodating space, and the openings are hinged; a torsion spring abutting between the flip member and the first base, the torsion spring being located in the accommodation space; A pressing member, located at an end of the flip member away from the first base, and partially located in the first cavity on a side of the flip member away from the first base; an elastic member, disposed in the first cavity, and in a compressed state, causing the radial through hole of the pressing member to communicate with the radial through hole of the flip member; When the extension direction of the flip member is parallel to the axial direction of the tooling main body assembly, the torsion spring is in a torsion state; When the extending direction of the flip member is perpendicular to the axial direction of the tooling main body assembly, the torsion spring is in a free state.

2. The transfer tooling for a carrier rocket launch platform according to claim 1, characterized in that: The flip member further comprises a second portion disposed on a side of the first portion away from the first base; When the extension direction of the flip member is parallel to the axial direction of the tooling main body component, the second portion is rectangular in a plane parallel to the axial plane of the tooling main body component; the second portion includes the first cavity.

3. The transfer tooling for a launch vehicle launch platform according to claim 1, characterized in that: The plug-in / out assembly includes a plug-in / out base, a screw and a butterfly nut; the plug-in / out base is provided with a first through hole, the first through hole is configured to allow the screw and the plug-in / out cable to pass through, the screw is connected to the butterfly nut, and is used to adjust the position of the plug-in / out cable.

4. The transfer tool for a launch platform of a carrier rocket according to claim 1, characterized in that: The tooling main body assembly comprises: At least two docking rings, all of which are connected end to end in radial order to form a circular ring-shaped component; A docking plate is provided at both ends of each docking ring, and the docking plates of two adjacent docking rings are fixedly connected.

5. The transfer tool for a carrier rocket launch platform according to claim 1, characterized in that: The docking component comprises a docking component bottom plate and a docking component base which are sequentially away from the tooling main body component and connected; Along the axial direction of the tooling main body assembly, a second cavity is formed between the docking component bottom plate and the docking component base; The docking component base is provided with a second through hole, the second through hole is communicated with the second cavity, and the second through hole is configured to allow a connecting piece to pass through, so as to be detachably connected between the docking component and the original carrier rocket launch platform.

6. The transfer tool for a carrier rocket launch platform according to claim 1, characterized in that: The add-drain connector bracket comprises a bracket base and a bracket mounting plate which are sequentially away from the tooling main body component and connected to each other; a third through hole is provided on the bracket mounting plate; the third through hole is configured to allow the add-drain connector pipeline to pass through; Along the radial direction of the tooling main body assembly, the third through hole of the bracket mounting plate is located on a side of the bracket mounting plate away from the bracket base.

7. The transfer tool for a carrier rocket launch platform according to claim 1, characterized in that: It also includes an operation interface; the operation interface is arranged around and fixed on the periphery of the tooling main body component.

8. The transfer tooling for a carrier rocket launch platform according to claim 1, characterized in that: The arrow body support seat comprises a support seat base and a support plate which are sequentially away from the tooling main body assembly and connected to each other; the support seat base is provided with a through groove, and the through groove is connected to the fourth through hole of the support plate; In a plane parallel to the radial plane of the tooling main body component, the orthographic projection of the periphery of the fourth through hole of the support plate is located within the projection range of the through groove of the support seat base.

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