Launching device of carrier rocket, using method and launching system

Abstract

The invention provides a launch device of a carrier rocket, a use method and a launch system. The launching device is used for executing a launching task or a test run task, and comprises a fixed launching pad which is fixed at a launching site, is in butt joint with a carrier rocket during execution of the launching task, is in butt joint with a movable launching pad during execution of the test run task, and comprises a traction assembly; the bottom end of the movable launching pad is butted with the fixed launching pad, and the top end is butted with a carrier rocket sub-stage during a test run task execution period; one end of the mooring tool is used for being detachably connected with the top end of the carrier rocket sub-stage during the test run task execution period, and the other end of the mooring tool is in transmission connection with the traction assembly in a detachable mode; and the control system is in communication connection with the traction assembly and the mooring tool during execution of the test run task, and controls the traction assembly to adjust the pre-tightening force of the traction assembly according to the pre-tightening force information fed back by the mooring tool. According to the launching device, manpower, material resources and time cost can be greatly saved, and the structural integrity of the rocket body is guaranteed.

Description

Technical Field

[0001] The present application relates to the field of launch and test technology of carrier rockets. Specifically, the present application relates to a launch device and a use method and a launch system of a carrier rocket. Background Art

[0002] Currently, the launch device of a carrier rocket usually refers to a fixed launch pad fixed at the launch site. The fixed launch pad is fixed at the launch site and docks with the carrier rocket to complete the launch mission of the carrier rocket.

[0003] When there is no need to perform launch missions, the fixed launch pad is idle, and the utilization rate of the fixed launch pad and related supporting facilities is low. Summary of the invention

[0004] In view of the shortcomings of the existing methods, the present application proposes a launch device and a use method and a launch system for a carrier rocket, so as to solve the technical problems existing in the related technologies, such as the fixed launch pad being idle when there is no need to perform a launch mission, and the low utilization rate of the fixed launch pad and related supporting facilities.

[0005] In a first aspect, an embodiment of the present application provides a launch device of a carrier rocket, which is used to perform a launch mission or a test mission, including: A fixed launch platform, fixed at the launch site, configured to dock with the carrier rocket during the launch mission and dock with the mobile launch platform during the test mission; the fixed launch platform includes a traction assembly; The mobile launch platform has a bottom end for docking with the fixed launch platform and a top end for docking with the launch vehicle substage during the test mission; A tethered tooling is configured such that one end is used for detachably connecting to the top end of the launch vehicle sub-stage during the test mission, and the other end is detachably connected to the pulling assembly in a transmission manner; The control system is respectively connected to the pulling assembly and the mooring tooling during the test run, and controls the pulling assembly to adjust the preload of the pulling assembly according to the preload information fed back by the mooring tooling.

[0006] In some possible embodiments, the pulling assembly includes: The pulling mechanism is at least partially embedded in and fixed inside the fixed launching platform, is in communication connection with the control system, and has a top end exposed from the fixed launching platform; The lug seat is fixed to the top end of the pulling mechanism and is configured to be connected to the mooring tooling during the commissioning mission.

[0007] In some possible embodiments, the tie-down tooling includes: The top cap tooling is installed on the top of the launch vehicle sub-stage; The flexible component comprises a first flexible member, a sensing element and a second flexible member connected in sequence; one end of the first flexible member away from the sensing element is detachably connected to the top cap tooling, and one end of the second flexible member away from the sensing element is detachably connected to the support ear seat of the pulling component; The sensor element is connected to the control system for obtaining the preload force and feeding it back to the control system.

[0008] In some possible embodiments, the top hat tooling includes: A cap, which is provided on the top of the launch vehicle sub-stage; The support member is fixedly connected to the top of the cap and is radially shaped, with the end thereof extending beyond the edge of the cap; One end of the first flexible member away from the sensing element is detachably connected to the vicinity of the end of the supporting member.

[0009] In some possible embodiments, the top hat tooling further comprises: The support seat has a side wall fixedly connected to the peripheral wall of the cap, and a top fixedly connected to the end of the support member; the support seat has a connecting hole; A shackle, detachably connected to the connecting hole; One end of the first flexible member is sleeved on the shackle.

[0010] In a second aspect, an embodiment of the present application further provides a launch system of a carrier rocket, comprising: a carrier rocket or a carrier rocket sub-stage, and a launch device of any carrier rocket provided in the first aspect above; During the launch mission of the launcher, including the fixed launch pad and docking with the launch vehicle; During the test run of the launch device, including the fixed launch pad, the mobile launch pad, the tethered tooling and the control system, the fixed launch pad is docked with the mobile launch pad, the mobile launch pad is docked with the carrier rocket sub-stage, the towing assembly of the fixed launch pad is connected to the top of the carrier rocket sub-stage through the tethered tooling, and the control system is communicated with the towing assembly and the tethered tooling of the fixed launch pad respectively.

[0011] In a third aspect, an embodiment of the present application further provides a method for using a launch device of any carrier rocket provided in the first aspect, comprising: During the launch device test mission, the mobile launch pad is docked on top of the fixed launch pad; Dock the launch vehicle sub-stage on top of the mobile launch pad; One end of the tethered tool is detachably connected to the top of the launch vehicle sub-stage, and the other end of the tethered tool is detachably connected to the pulling assembly of the fixed launch platform; The control system controls the pulling component to adjust the preload according to the preload information fed back by the mooring tooling; the control system is communicatively connected with the pulling component and the mooring tooling of the fixed launch station.

[0012] In some possible embodiments, before docking the movable launching platform on the top of the fixed launching platform, the method further includes: The top cap of the tethered fixture is installed on the top of the launch vehicle sub-stage; The first flexible member, the sensing element and the second flexible member are connected in sequence to form a flexible component of the tethered tooling.

[0013] In some possible embodiments, one end of the tethered tool is detachably connected to the top of the launch vehicle sub-stage, and the other end of the tethered tool is detachably connected to the pulling assembly of the fixed launch platform, including: The end of the first flexible member away from the sensing element is detachably connected to the top hat tooling through a shackle; The end of the second flexible member away from the sensing element is transmission-connected to the ear seat of the pulling assembly through a pin.

[0014] In some possible embodiments, the control system controls the pulling assembly to adjust the preload according to the preload information fed back by the tethered tooling, including: The control system obtains the initial preload information fed back by the mooring tooling, and determines whether the initial preload information meets the design requirements before the test run; if not, the pulling assembly is controlled to adjust the preload until the initial preload information fed back by the mooring tooling meets the design requirements; The control system controls the ignition test of the launch vehicle sub-stage, obtains the real-time preload information fed back by the tethered tooling during the test, and determines whether the deviation between the real-time preload information and the design preload parameters of the launch vehicle sub-stage under test is within a specified range; if so, determines that the real-time preload information meets the design requirements; if not, controls the pulling assembly to adjust the preload until the real-time preload information fed back by the tethered tooling meets the design requirements.

[0015] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include: During the launch mission, the embodiment of the present application directly docks the complete carrier rocket on the fixed launch pad without installing a mobile launch pad. The launch device provided by the embodiment of the present application has the function of executing the launch mission of the carrier rocket and the function of the carrier rocket sub-stage test mission, which can improve the utilization rate of related supporting facilities such as the fixed launch pad.

[0016] The pulling assembly in the embodiment of the present application has a smaller volume than the fixed launch platform, and basically will not affect the fixed launch platform from executing the launch mission. There is no need to repeatedly disassemble and assemble the relevant supporting structures for executing the test mission when switching the mission to be executed, which can save the manpower and material costs of executing the mission and improve the efficiency of executing the mission.

[0017] The cost of adding a pulling assembly to the embodiment of the present application is far less than the cost of building a fixed launch platform; compared with the construction cost of a new sub-level test platform, the cost of adding a pulling assembly to the fixed launch platform in the embodiment of the present application is also relatively low; the mobile launch platform and the mooring tooling are both supporting facilities for the test mission and do not need to be developed separately. Therefore, the embodiment of the present application can greatly save manpower, material resources and time costs.

[0018] The embodiment of the present application can dock with launch vehicle sub-stages of different specifications by docking with different mobile launch platforms, thereby expanding the scope of application.

[0019] The launch vehicle sub-stage of the embodiment of the present application is subjected to different impact forces during the test run due to changes in propellant consumption. The control system controls the pulling assembly to adjust the pre-tightening force based on the pre-tightening force information applied to the launch vehicle sub-stage fed back by the tethered tooling, and applies a pulling force (or vertical component) opposite to the impact force (generated after the launch vehicle sub-stage is ignited) to the launch vehicle sub-stage, thereby offsetting a portion of the impact force acting on the launch vehicle sub-stage body itself during the test run, thereby reducing the degree of deformation of the launch vehicle sub-stage body, thereby ensuring the structural integrity of the body.

[0020] 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

[0021] 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: Figure 1 A schematic diagram of the structure of a launch system during a test mission provided by an embodiment of the present application; Figure 2 A schematic diagram of the structure of a tethered tooling for a launch device provided in an embodiment of the present application; Figure 3 for Figure 2 The local enlarged schematic diagram of point Ⅰ in the middle; Figure 4 for Figure 2 A partial enlarged schematic diagram of the middle II; Figure 5 A schematic diagram of the structure of a fixed launching platform of a launching device provided in an embodiment of the present application; Figure 6 for Figure 5 A partial enlarged schematic diagram of point III in the middle; Figure 7 A flowchart of a method for using a transmitting device provided in an embodiment of the present application; Figure 8 A schematic diagram of a flow chart of a control system adjusting a preload force in a method for using a launching device provided in an embodiment of the present application.

[0022] Reference numerals: 100-launching device; 10-fixed launching platform; 11-pulling assembly; 111-pulling mechanism; 112-supporting ear seat; 20-Active launch pad; 30-tie-down tooling; 31-top hat workwear; 311-cap; 312-support member; 313-support seat; 314-shackle; 32-Flexible component; 321-first flexible member; 322-sensing element; 323-second flexible member; 324-pin shaft; 40- control system; 200 - Launch vehicle sub-stage. DETAILED DESCRIPTION

[0023] 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.

[0024] Those skilled in the art will appreciate that, unless expressly stated, the "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of the present application refers to the presence of the features, integers, elements and / or components, but does not exclude the implementation of other features, information, data, 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".

[0025] 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.

[0026] At present, the launch device of a carrier rocket usually refers to a fixed launch pad fixed at the launch site. The fixed launch pad is fixed at the launch site, docks with the carrier rocket and then completes the launch mission of the carrier rocket. When there is no need to perform a launch mission, the fixed launch pad is idle, and the utilization rate of the fixed launch pad and related supporting facilities is low.

[0027] In the related art, by adding safety devices to the fixed launch platform, the fixed launch platform is transformed into a launch vehicle sub-stage test, and the launch mission or test mission is performed respectively. However, during the launch mission, the safety devices need to be removed to avoid affecting the launch mission. Therefore, a lot of disassembly and assembly work is required before and after switching to perform the mission, which greatly consumes manpower, material resources or time costs.

[0028] Moreover, the ropes of the safety backup device can only provide a fixed tension to the launch vehicle sub-stage to ensure that it does not tip over, and the ropes are in a loose state. After the test run is ignited, the rocket body of the launch vehicle sub-stage deforms under different working conditions, and the ropes cannot provide pre-tightening force for the rocket body, which may cause serious deformation of the rocket body and lead to structural failure.

[0029] The launch device, use method and launch system of the carrier rocket provided in this application are intended to solve the above-mentioned technical problems of the related technology.

[0030] 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.

[0031] The present application embodiment provides a launch device 100 of a carrier rocket, which is used to perform a launch mission or a test mission, such as Figure 1 and Figure 5 As shown, the launching device 100 includes: a fixed launching platform 10, a movable launching platform 20, a mooring tooling 30 and a control system 40.

[0032] The fixed launch platform 10 is fixed at the launch site and is configured to dock with the carrier rocket during a launch mission and to dock with the movable launch platform 20 during a test mission. The fixed launch platform 10 includes a pulling assembly 11 .

[0033] The bottom end of the movable launch platform 20 is used for docking with the fixed launch platform 10, and the top end is used for docking with the carrier rocket sub-stage 200 during the test mission.

[0034] The tethering fixture 30 is constructed so that one end is used for detachably connecting to the top end of the launch vehicle sub-stage 200 during the test mission, and the other end is detachably connected to the pulling assembly 11 in a transmission manner.

[0035] During the test run, the control system 40 is in communication with the pulling assembly 11 and the mooring fixture 30 , respectively, and controls the pulling assembly 11 to adjust the preload force of the pulling assembly 11 according to the preload force information fed back by the mooring fixture 30 .

[0036] In this embodiment, during the test mission, the mobile launch platform 20 and the carrier rocket sub-stage 200 can be sequentially stacked on the fixed launch platform 10, and the carrier rocket sub-stage 200 is connected to the pulling assembly 11 added to the fixed launch platform 10 by using the tethering tool 30, so that the pulling assembly 11 applies a pre-tightening force to the carrier rocket sub-stage 200. During the launch mission, the complete carrier rocket is directly docked on the fixed launch platform 10 without installing the mobile launch platform 20. The launch device 100 provided in the embodiment of the present application has the function of performing the launch mission of the carrier rocket and the test mission of the carrier rocket sub-stage 200, and can improve the utilization rate of the fixed launch platform 10 and other related supporting facilities.

[0037] The pulling assembly 11 in this embodiment has a smaller volume than the fixed launch platform 10, and basically will not affect the fixed launch platform 10 in executing the launch mission. There is no need to repeatedly disassemble and assemble the relevant supporting structures for executing the test mission when switching the mission to be executed, which can save the manpower and material costs of executing the mission and improve the efficiency of executing the mission.

[0038] Moreover, the cost of adding the pulling assembly 11 to the embodiment of the present application is far less than the cost of building the fixed launch platform 10; compared with the construction cost of a new sub-level test platform, the cost of adding the pulling assembly 11 to the fixed launch platform 10 in the embodiment of the present application is also relatively low; the mobile launch platform 20 and the mooring tooling 30 are both supporting facilities for the test mission and do not need to be developed separately. Therefore, the embodiment of the present application can greatly save manpower, material resources and time costs.

[0039] Moreover, by docking with different mobile launch platforms 20, it is possible to dock with launch vehicle sub-stages 200 of different specifications, thereby expanding the scope of application.

[0040] In addition, the launch vehicle sub-stage 200 is subjected to different impact forces due to changes in propellant consumption during the test run. The control system 40 controls the pulling assembly 11 to adjust the preload force based on the preload force information applied to the launch vehicle sub-stage 200 fed back by the tethering tooling 30, and applies a pulling force (or vertical component) opposite to the impact force (generated after the launch vehicle sub-stage 200 is ignited) to the launch vehicle sub-stage 200, thereby offsetting a portion of the impact force acting on the launch vehicle sub-stage 200 body itself during the test run, thereby reducing the degree of deformation of the launch vehicle sub-stage 200 body, thereby ensuring the structural integrity of the body.

[0041] In some possible embodiments, Figure 5 and Figure 6As shown, the pulling assembly 11 includes a pulling mechanism 111 and a lug seat 112 .

[0042] The pulling mechanism 111 is at least partially embedded in and fixed inside the fixed launching platform 10 , is in communication connection with the control system 40 , and has a top end exposed from the fixed launching platform 10 .

[0043] The lug seat 112 is fixed to the top end of the pulling mechanism 111 and is configured to be connected to the mooring tool 30 during the test mission.

[0044] In this embodiment, the pulling mechanism 111 is at least partially embedded and fixed inside the body of the fixed launch platform 10, and basically does not occupy the launch space on the surface of the fixed launch platform 10, and almost does not affect the launch mission, which can avoid the disassembly and assembly of the pulling mechanism 111 during the replacement of the execution mission, and can save costs and improve efficiency. The ear seat 112 is relatively small in size, fixed to the top of the pulling mechanism 111, and extends out of the surface of the fixed launch platform 10, so as to facilitate connection with the mooring tool 30, so that the pulling mechanism 111 applies a pre-tightening force to the mooring tool 30 through the ear seat 112.

[0045] In some possible embodiments, Figure 2 As shown, the tethering tool 30 includes a top hat tool 31 and a flexible component 32 .

[0046] The top cap tooling 31 is covered on the top of the launch vehicle sub-stage 200.

[0047] The flexible component 32 includes a first flexible component 321, a sensing element 322 and a second flexible component 323 connected in sequence; the end of the first flexible component 321 away from the sensing element 322 is detachably connected to the top hat tooling 31, and the end of the second flexible component 323 away from the sensing element 322 is detachably connected to the support ear seat 112 of the pulling component 11.

[0048] The sensor element 322 is connected to the control system 40 for communication, and is used to obtain the preload force and feed it back to the control system 40 .

[0049] In this embodiment, during the test run, the top cap tooling 31 is covered on the top of the launch vehicle sub-stage 200, and then connected to the ear seat 112 of the pulling assembly 11 through the flexible assembly 32, so that the preload force applied by the pulling assembly 11 acts on the top of the launch vehicle sub-stage 200, that is, the top of the launch vehicle sub-stage 200 is subjected to the preload force applied by the pulling assembly 11, and the bottom end is subjected to the reaction force from the movable launch platform 20. The forces at both ends of the launch vehicle sub-stage 200 act together, thereby keeping the molecular structure of the launch vehicle sub-stage 200 relatively stable, thereby reducing the possibility of deformation.

[0050] Optionally, the first flexible member 321 and the second flexible member 323 are both slender.

[0051] Optionally, the first flexible member 321 and the second flexible member 323 may both include steel wire ropes.

[0052] Optionally, the sensing element 322 includes a force sensor.

[0053] In some possible embodiments, Figure 2-Figure 4 As shown, the top hat tooling 31 includes: a cover cap 311 and a support member 312 .

[0054] The cap 311 is disposed on the top of the launch vehicle sub-stage 200 .

[0055] The support member 312 is fixedly connected to the top of the cover cap 311 and is radially arranged, with the end thereof extending out from the edge of the cover cap 311 .

[0056] One end of the first flexible member 321 away from the sensing element 322 is detachably connected to the vicinity of the end of the supporting member 312 .

[0057] In this embodiment, during the execution of the test mission, the cap 311 can cover the top end of the entire launch vehicle sub-stage 200 inside, and the support member 312 is fixedly pressed on the top end of the cap 311, which can protect the entire launch vehicle sub-stage 200 inside, thereby preventing the launch vehicle sub-stage 200 from breaking through the cap 311 due to excessive impact force during the test process, or preventing the cap 311 from being torn by the flexible component 32 due to excessive pre-tightening force, thereby ensuring the smooth progress of the test mission and improving the success rate of the test mission.

[0058] In some possible embodiments, Figure 2-Figure 4 As shown, during the commissioning task, the top hat tooling 31 also includes: a support seat 313 and a shackle 314.

[0059] The side wall of the support seat 313 is fixedly connected to the peripheral wall of the cap 311 , and the top is fixedly connected to the end of the support member 312 ; the support seat 313 has a connecting hole.

[0060] The shackle 314 is detachably connected to the connecting hole.

[0061] One end of the first flexible member 321 is sleeved on the shackle 314 .

[0062] In this embodiment, the support seat 313 is fixed to the peripheral wall of the cap 311 and supported at the bottom end of the support member 312, which can enhance the strength of the support member 312 when subjected to a downward load. The detachable connection between the support seat 313 and the first flexible member 321 is achieved through the shackle 314, thereby enabling the detachable connection between the top cap tooling 31 and the flexible component 32, which has a simple structure and is easy to operate, and can ensure the installation efficiency of the mooring tooling 30.

[0063] Based on the same inventive concept, Figure 1 As shown, an embodiment of the present application also provides a launch system for a carrier rocket, including: a carrier rocket or a carrier rocket sub-stage 200, and a launch device 100 for a carrier rocket as provided in any of the above embodiments.

[0064] During the launch mission performed by the launch device 100, including the fixed launch platform 10, docking with the carrier rocket.

[0065] During the test run mission of the launch device 100, which includes a fixed launch platform 10, a movable launch platform 20, a tethering tool 30 and a control system 40, the fixed launch platform 10 is docked with the movable launch platform 20, the movable launch platform 20 is docked with the carrier rocket sub-stage 200, the pulling assembly 11 of the fixed launch platform 10 is connected to the top of the carrier rocket sub-stage 200 through the tethering tool 30, and the control system 40 is communicatively connected with the pulling assembly 11 of the fixed launch platform 10 and the tethering tool 30 respectively.

[0066] The launch system of the carrier rocket provided in this embodiment includes the launch device 100 of any carrier rocket provided in the above embodiments, and the implementation principles are similar, which will not be repeated here.

[0067] In this embodiment, the launching device 100 has the function of executing both the launch mission of the carrier rocket and the test mission of the carrier rocket sub-stage 200, which can improve the utilization rate of relevant supporting facilities such as the fixed launching platform 10.

[0068] The pulling assembly 11 in this embodiment has a smaller volume than the fixed launch platform 10, and basically will not affect the fixed launch platform 10 in executing the launch mission. There is no need to repeatedly disassemble and assemble the relevant supporting structures for executing the test mission when switching the mission to be executed, which can save the manpower and material costs of executing the mission and improve the efficiency of executing the mission.

[0069] Moreover, the cost of adding the pulling assembly 11 to the embodiment of the present application is far less than the cost of building the fixed launch platform 10; compared with the construction cost of a new sub-level test platform, the cost of adding the pulling assembly 11 to the fixed launch platform 10 in the embodiment of the present application is also relatively low; the mobile launch platform 20 and the mooring tooling 30 are both supporting facilities for the test mission and do not need to be developed separately. Therefore, the embodiment of the present application can greatly save manpower, material resources and time costs.

[0070] Moreover, by docking with different mobile launch platforms 20, it is possible to dock with launch vehicle sub-stages 200 of different specifications, thereby expanding the scope of application.

[0071] In addition, the launch vehicle sub-stage 200 is subjected to different impact forces due to changes in propellant consumption during the test run. The control system 40 controls the pulling assembly 11 to adjust the preload force based on the preload force information applied to the launch vehicle sub-stage 200 fed back by the tethering tooling 30, and applies a pulling force (or vertical component) opposite to the impact force (generated after the launch vehicle sub-stage 200 is ignited) to the launch vehicle sub-stage 200, thereby offsetting a portion of the impact force acting on the launch vehicle sub-stage 200 body itself during the test run, thereby reducing the degree of deformation of the launch vehicle sub-stage 200 body, thereby ensuring the structural integrity of the body.

[0072] Based on the same inventive concept, the present application embodiment also provides a method for using the launch device 100 of a carrier rocket as provided in any of the above embodiments. The flow chart of the method is as follows: Figure 7 As shown, the method includes steps S101 to S104: S101: While the launching device 100 is performing a test mission, the movable launching platform 20 is docked on top of the fixed launching platform 10.

[0073] S102: docking the carrier rocket sub-stage 200 on top of the movable launch platform 20.

[0074] S103: One end of the mooring tool 30 is detachably connected to the top of the launch vehicle sub-stage 200, and the other end of the mooring tool 30 is detachably connected to the pulling assembly 11 of the fixed launch platform 10.

[0075] S104: the control system 40 controls the pulling assembly 11 to adjust the preload according to the preload information fed back by the mooring tooling 30 ; the control system 40 is in communication connection with the pulling assembly 11 of the fixed launch station 10 and the mooring tooling 30 .

[0076] In this embodiment, the fixed launch platform 10 is fixed at the launch site, the movable launch platform 20 that matches the size of the carrier rocket sub-stage 200 is docked with the fixed launch platform 10, the carrier rocket sub-stage 200 is docked with the movable launch platform 20, and the top of the carrier rocket sub-stage 200 is connected to the newly added pulling assembly 11 of the fixed launch platform 10 through the mooring tooling 30, so that the top of the carrier rocket sub-stage 200 is subjected to a pulling force (or vertical component) opposite to the impact force, thereby offsetting a part of the impact force acting on the rocket body itself of the carrier rocket sub-stage 200 during the test run.

[0077] Moreover, the control system 40 controls the pulling assembly 11 to adjust the preload according to the preload information applied to the launch vehicle sub-stage 200 fed back by the tethering tooling 30, and can adjust the pulling force (or vertical component) applied to the top of the launch vehicle sub-stage 200 according to the different impact forces applied to the rocket body under different working conditions, thereby reducing the degree of deformation of the rocket body of the launch vehicle sub-stage 200, thereby ensuring the structural integrity of the rocket body.

[0078] It should be noted that the order of docking the mobile launch platform 20 with the fixed launch platform 10 in the above step S101 and docking the carrier rocket sub-stage 200 with the mobile launch platform 20 in step S102 is not fixed and depends on the actual situation.

[0079] In some possible embodiments, before docking the movable launching platform 20 on the top of the fixed launching platform 10 in the above step S101, the following steps are also included: The top cap fixture 31 of the tethering fixture 30 is covered on the top of the launch vehicle sub-stage 200 .

[0080] The first flexible member 321 , the sensing element 322 and the second flexible member 323 are connected in sequence to form the flexible component 32 of the mooring tool 30 .

[0081] In this embodiment, the top of the launch vehicle sub-stage 200 is pre-covered with a top cap tooling 31, and the flexible component 32 can be assembled in advance to prepare for the test run, so that it can be directly used during the test run, thereby reducing the assembly time during the test run and improving the test run efficiency.

[0082] In some possible embodiments, the above step S103 of detachably connecting one end of the tethering tool 30 to the top of the launch vehicle sub-stage 200 and detachably connecting the other end of the tethering tool 30 to the pulling assembly 11 of the fixed launch platform 10 includes the following steps: One end of the first flexible member 321 away from the sensing element 322 is detachably connected to the top hat tooling 31 via a shackle 314 .

[0083] One end of the second flexible member 323 away from the sensor element 322 is transmission-connected to the ear seat 112 of the pulling assembly 11 via a pin shaft 324 .

[0084] In this embodiment, the first flexible member 321 at one end of the sensor element 322 is detachably connected to the top cap tooling 31 through the shackle 314, and the second flexible member 323 at the other end of the sensor element 322 is detachably connected to the support ear seat 112 through the pin 324, so that the preload force applied by the pulling mechanism 111 is sequentially transmitted to the top cap tooling 31 through the support ear seat 112, the pin 324, the second flexible member 323, the sensor element 322 and the first flexible member 321, and then acts on the top of the launch vehicle sub-stage 200. Since the sensor element 322 is arranged between the first flexible member 321 and the second flexible member 323, the force applied to the first flexible member 321 or the second flexible member 323 is transmitted through the sensor element 322, so that the sensor element 322 obtains the force applied to the first flexible member 321 or the second flexible member 323, and then transmits it to the control system 40.

[0085] In some possible embodiments, the control system 40 in the above step S104 controls the pulling assembly 11 to adjust the preload force according to the preload force information fed back by the mooring tool 30, including the following steps: The control system 40 obtains the initial preload information fed back by the mooring tooling 30, and determines whether the initial preload information meets the design requirements before the test run; if not, the pulling assembly 11 is controlled to adjust the preload until the initial preload information fed back by the mooring tooling 30 meets the design requirements.

[0086] The control system 40 controls the ignition test of the launch vehicle sub-stage 200, obtains the real-time preload information fed back by the tethering tooling 30 during the test, and determines whether the deviation between the real-time preload information and the design preload parameters of the launch vehicle sub-stage 200 under test is within a specified range; if so, determines that the real-time preload information meets the design requirements; if not, controls the pulling assembly 11 to adjust the preload until the real-time preload information fed back by the tethering tooling 30 meets the design requirements.

[0087] In this embodiment, the control system 40 obtains the initial preload information fed back by the sensor element 322 of the mooring tooling 30, and determines whether the initial preload information meets the design requirements before the test run; if not, the pulling assembly 11 is controlled to adjust the preload until the initial preload information fed back by the sensor element 322 of the mooring tooling 30 meets the design requirements; if so, the launch vehicle sub-stage 200 is controlled to ignite and start testing the launch vehicle sub-stage 200.

[0088] In this embodiment, during the test run after the launch vehicle sub-stage 200 is ignited, the sensor element 322 of the mooring fixture 30 feeds back the real-time preload information received to the control system 40 in real time, and the control system 40 determines in real time whether the deviation between the real-time preload information fed back by the sensor element 322 of the mooring fixture 30 and the corresponding design preload parameter is within the specified range. If so, it is determined that the real-time preload information of the mooring fixture 30 is within the normal range, and the test run task can be carried out normally. If not, it is necessary to control the preload applied by the pulling assembly 11 to adjust so that the preload information fed back by the sensor element 322 of the mooring fixture 30 meets the design requirements, ensuring that the launch vehicle sub-stage 200 is always tested in a reasonable state, ensuring the smooth progress of the test, and ensuring the structural integrity of the launch vehicle sub-stage 200 during the experiment.

[0089] By applying the embodiments of the present application, at least the following beneficial effects can be achieved: 1. During the test run, the fixed launch platform 10 may be sequentially stacked with a mobile launch platform 20 and a carrier rocket sub-stage 200, and the carrier rocket sub-stage 200 may be connected to the pulling assembly 11 added to the fixed launch platform 10 by using a tethering tool 30, so that the pulling assembly 11 applies a pre-tightening force to the carrier rocket sub-stage 200. During the launch mission, the complete carrier rocket is directly docked on the fixed launch platform 10 without installing the mobile launch platform 20. The launch device 100 provided in the embodiment of the present application has the function of performing the launch mission of the carrier rocket and the test run mission of the carrier rocket sub-stage 200, and can improve the utilization rate of the fixed launch platform 10 and other related supporting facilities.

[0090] 2. The pulling component 11 has a smaller volume than the fixed launch platform 10, and basically will not affect the fixed launch platform 10 in executing the launch mission. There is no need to repeatedly disassemble and assemble the relevant supporting structures for executing the test mission when switching the mission to be executed, which can save the manpower and material costs of executing the mission and improve the efficiency of executing the mission.

[0091] 3. The cost of adding the pulling assembly 11 is much lower than the cost of building the fixed launch platform 10; compared with the construction cost of a new sub-level test platform, the cost of adding the pulling assembly 11 to the fixed launch platform 10 in the embodiment of the present application is also relatively low; the mobile launch platform 20 and the mooring tooling 30 are both supporting facilities for the test mission and do not need to be developed separately. Therefore, the embodiment of the present application can greatly save manpower, material resources and time costs.

[0092] 4. By docking with different mobile launch platforms 20, it is possible to dock with launch vehicle sub-stages 200 of different specifications, thereby expanding the scope of application.

[0093] 5. The carrier rocket sub-stage 200 is subjected to different impact forces due to changes in propellant consumption during the test run. The control system 40 controls the pulling assembly 11 to adjust the preload force based on the preload force information applied to the carrier rocket sub-stage 200 fed back by the tethering tooling 30, and applies a pulling force (or a vertical component force) opposite to the impact force (generated after the ignition of the carrier rocket sub-stage 200) to the carrier rocket sub-stage 200, thereby offsetting a portion of the impact force acting on the body of the carrier rocket sub-stage 200 during the test run, thereby reducing the degree of deformation of the body of the carrier rocket sub-stage 200, thereby ensuring the structural integrity of the body.

[0094] 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, or be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0095] 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.

[0096] 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.

[0097] 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.

[0098] 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 launch device for a carrier rocket, characterized in that: Used to perform launch missions or test missions, including: A fixed launch platform, fixed at the launch site, configured to dock with the carrier rocket during the launch mission and dock with the mobile launch platform during the test mission; the fixed launch platform includes a traction assembly; The movable launch platform has a bottom end for docking with the fixed launch platform and a top end for docking with the carrier rocket substage during the test mission; A tethered tooling is configured such that one end is used for detachably connecting to the top end of the launch vehicle sub-stage during the test mission, and the other end is detachably connected to the pulling assembly in a transmission manner; The control system is respectively connected to the pulling assembly and the mooring tooling during the test run, and controls the pulling assembly to adjust the preload of the pulling assembly according to the preload information fed back by the mooring tooling.

2. The launch device of a carrier rocket according to claim 1, characterized in that: The pulling assembly comprises: A pulling mechanism, at least partially embedded in and fixed inside the fixed launch platform, connected in communication with the control system, with a top end exposed from the fixed launch platform; A lug seat is fixed to the top end of the pulling mechanism and is configured to be connected to the mooring tooling during a test run.

3. The launch device of a carrier rocket according to claim 1, characterized in that: The mooring tooling comprises: A top cap tooling, which is provided on the top of the launch vehicle sub-stage; The flexible component comprises a first flexible member, a sensing element and a second flexible member connected in sequence; one end of the first flexible member away from the sensing element is detachably connected to the top cap tooling, and one end of the second flexible member away from the sensing element is detachably connected to the ear seat of the pulling component; The sensor element is in communication connection with the control system, and is used for acquiring the preload force and feeding back the preload force to the control system.

4. The launch device of a carrier rocket according to claim 3, characterized in that: The top hat tooling comprises: A cap, which is arranged on the top of the launch vehicle sub-stage; A support member, fixedly connected to the top of the cap, radially arranged, with the end thereof extending beyond the edge of the cap; One end of the first flexible member away from the sensing element is detachably connected to the vicinity of the end of the supporting member.

5. The launch device of a carrier rocket according to claim 4, characterized in that: The top hat tooling also includes: A support seat, the side wall of which is fixedly connected to the peripheral wall of the cap, and the top of which is fixedly connected to the end of the support member; the support seat has a connecting hole; a shackle, detachably connected to the connecting hole; One end of the first flexible member is sleeved on the shackle.

6. A launch system for a carrier rocket, characterized in that: include: A launch vehicle or a launch vehicle sub-stage, and a launch device for a launch vehicle as claimed in any one of claims 1 to 5; During the launch mission of the launch device, including fixing the launch platform and docking with the carrier rocket; During the period when the launch device performs the test mission, it includes a fixed launch platform, a movable launch platform, a tethered tool and a control system. The fixed launch platform is docked with the movable launch platform, and the movable launch platform is docked with the carrier rocket sub-stage. The traction assembly of the fixed launch platform is connected to the top of the carrier rocket sub-stage through the tethered tool, and the control system is communicatively connected with the traction assembly of the fixed launch platform and the tethered tool respectively.

7. A method for using the launch device of a carrier rocket as claimed in any one of claims 1 to 5, characterized in that: include: During the launch device's test mission, docking the movable launch platform on top of the fixed launch platform; docking the carrier rocket sub-stage on top of the movable launch pad; One end of the tethered tool is detachably connected to the top of the launch vehicle sub-stage, and the other end of the tethered tool is detachably connected to the pulling assembly of the fixed launch platform; The control system controls the pulling component to adjust the preload according to the preload information fed back by the mooring tooling; the control system is in communication connection with the pulling component of the fixed launch station and the mooring tooling.

8. The method for using the launch device of a carrier rocket according to claim 7, characterized in that: Before docking the mobile launch platform on top of the fixed launch platform, it also includes: The top cap of the tethered fixture is arranged on the top of the launch vehicle sub-stage; The first flexible member, the sensing element and the second flexible member are connected in sequence to form a flexible component of the tethered tooling.

9. The method for using the launch device of a carrier rocket according to claim 8, characterized in that: One end of the tethered tool is detachably connected to the top of the carrier rocket sub-stage, and the other end of the tethered tool is detachably connected to the pulling assembly of the fixed launch platform, including: Removably connecting one end of the first flexible member away from the sensing element to the top hat fixture via a shackle; The end of the second flexible member away from the sensor element is transmission-connected to the ear seat of the pulling assembly through a pin.

10. The method for using the launch device of a carrier rocket according to claim 9, characterized in that: The control system controls the pulling assembly to adjust the preload according to the preload information fed back by the mooring tooling, including: The control system obtains the initial preload information fed back by the mooring tooling, and determines whether the initial preload information meets the design requirements before the test run; if not, the pulling assembly is controlled to adjust the preload until the initial preload information fed back by the mooring tooling meets the design requirements; The control system controls the ignition test of the launch vehicle sub-stage, obtains real-time preload information fed back by the tethered tooling during the test, and determines whether the deviation between the real-time preload information and the design preload parameter of the launch vehicle sub-stage under test is within a specified range; if so, determines that the real-time preload information meets the design requirements; if not, controls the pulling assembly to adjust the preload until the real-time preload information fed back by the tethered tooling meets the design requirements.

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