Launch device and use method of carrier rocket, and launch system

Abstract

The present application provides a launch device, a method of use, and a launch system for a carrier rocket. The launch device is used to perform a launch mission or a test mission, including: a fixed launch platform fixed at the launch site, docking with the carrier rocket during the launch mission, and docking with a movable launch platform during the test mission, including a pulling assembly; the bottom end of the movable launch platform is used to dock with the fixed launch platform, and the top end is used to dock with the carrier rocket sub-stage during the test mission; a tethered tooling is constructed so that one end is used to detachably connect to the top end of the carrier rocket sub-stage during the test mission, and the other end is detachably connected to the pulling assembly in a transmission manner; a control system is respectively communicated with the pulling assembly and the tethered tooling during the test mission, and controls the pulling assembly to adjust the preload of the pulling assembly according to the preload information fed back by the tethered tooling. The launch device provided by the present application can greatly save manpower, material resources, and time costs, and ensure the structural integrity of the rocket body.

Description

Technical Field

[0001] The present application relates to the technical field of launch and testing of carrier rockets. Specifically, the present application relates to a launch device, a method of use, and a launch system for 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, fixed launch pads are idle, and the utilization rate of fixed launch pads and related supporting facilities is low. Summary of the Invention

[0004] In response to the shortcomings of existing methods, this application proposes a launch device, usage method, and launch system for a carrier rocket to solve technical problems existing in related technologies, such as the fixed launch pad being idle when no launch mission is required, 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 for a carrier rocket, which is used to perform a launch mission or a test mission, including:

[0006] A fixed launch platform, fixed at the launch site, configured to dock with the carrier rocket during a launch mission and dock with the mobile launch platform during a test mission; the fixed launch platform includes a traction assembly;

[0007] A mobile launch platform, the bottom end of which is used to dock with the fixed launch platform, and the top end is used to dock with the carrier rocket sub-stage during the test mission;

[0008] A tethered tooling is configured such that one end is detachably connected to the top end of the launch vehicle sub-stage during a test mission, and the other end is detachably connected to the pulling assembly in a transmission manner;

[0009] 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.

[0010] In some possible embodiments, the pulling assembly includes:

[0011] The pulling mechanism is at least partially embedded in and fixed to the fixed launch platform, is in communication with the control system, and has a top end exposed from the fixed launch platform;

[0012] 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.

[0013] In some possible embodiments, the tie-down tooling includes:

[0014] Top cap tooling, which is installed on the top of the launch vehicle sub-stage;

[0015] The flexible component includes a first flexible member, a sensing element, and a second flexible member connected in sequence; an end of the first flexible member away from the sensing element is detachably connected to the top cap tooling, and an end of the second flexible member away from the sensing element is detachably connected to the support ear seat of the pulling component;

[0016] The sensor element is connected to the control system for communication, and is used to obtain the preload force and feed it back to the control system.

[0017] In some possible embodiments, the top hat tooling includes:

[0018] A cap, which is located on the top of the launch vehicle sub-stage;

[0019] The support member is fixedly connected to the top of the cap and is radially arranged, with the end thereof extending beyond the edge of the cap;

[0020] 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.

[0021] In some possible embodiments, the top hat tooling further includes:

[0022] The support base 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 base has a connecting hole;

[0023] a shackle, detachably connected to the connecting hole;

[0024] One end of the first flexible member is sleeved on the shackle.

[0025] In a second aspect, an embodiment of the present application further provides a launch system for a carrier rocket, comprising: a carrier rocket or a carrier rocket sub-stage, and a launch device for any carrier rocket provided in the first aspect above;

[0026] During the launch mission of the launch vehicle, including the fixed launch pad and docking with the carrier rocket;

[0027] During the test mission of the launch device, including the fixed launch pad, mobile launch pad, tethered tooling and 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 traction 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 traction assembly and tethered tooling of the fixed launch pad respectively.

[0028] In a third aspect, an embodiment of the present application further provides a method for using the launch device of any carrier rocket provided in the first aspect, comprising:

[0029] During the launch vehicle test mission, the movable launch platform is docked on top of the fixed launch platform;

[0030] docking the carrier rocket sub-stage on top of the mobile launch pad;

[0031] One end of the tethered tooling is detachably connected to the top of the carrier rocket sub-stage, and the other end of the tethered tooling is detachably connected to the pulling assembly of the fixed launch platform;

[0032] 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 platform.

[0033] In some possible embodiments, before docking the movable launch platform on top of the fixed launch platform, the method further includes:

[0034] Installing the top cap of the tethered fixture on the top of the launch vehicle sub-stage;

[0035] The first flexible member, the sensing element and the second flexible member are connected in sequence to form a flexible assembly of the tethered tooling.

[0036] In some possible embodiments, one end of the tethering tool is detachably connected to the top end of the launch vehicle sub-stage, and the other end of the tethering tool is detachably connected to the pulling assembly of the fixed launch pad, including:

[0037] Removably connecting the end of the first flexible member away from the sensing element to the top hat fixture via a shackle;

[0038] 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.

[0039] 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:

[0040] 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 control system controls the pulling assembly to adjust the preload until the initial preload information fed back by the mooring tooling meets the design requirements.

[0041] The control system controls the ignition test of the carrier rocket 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 carrier rocket sub-stage under test is within the specified range; if so, it is determined that the real-time preload information meets the design requirements; if not, the pulling assembly is controlled to adjust the preload until the real-time preload information fed back by the tethered tooling meets the design requirements.

[0042] The beneficial technical effects brought about by the technical solutions provided in the embodiments of the present application include:

[0043] During a launch mission, the embodiment of the present application directly docks a complete carrier rocket on a fixed launch pad, eliminating the need for a mobile launch pad. The launch device provided by the embodiment of the present application is capable of performing both carrier rocket launch missions and carrier rocket sub-stage test missions, thereby improving the utilization rate of related supporting facilities such as fixed launch pads.

[0044] 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's execution of the launch mission. There is no need to repeatedly disassemble and assemble the relevant supporting structures for performing the test mission when switching the mission to be performed, which can save the manpower and material costs of performing the mission and improve the efficiency of performing the mission.

[0045] The cost of adding a traction assembly to the embodiment of the present application is far less than the cost of building a fixed launch platform. Compared to the construction cost of a new sub-stage test platform, the cost of adding a traction assembly to the fixed launch platform in the embodiment of the present application is also lower. The mobile launch platform and mooring tooling are both supporting facilities for the test mission and do not require separate development. Therefore, the embodiment of the present application can significantly save manpower, material resources, and time costs.

[0046] The embodiment of the present application can dock with different specifications of carrier rocket sub-stages by docking with different mobile launch platforms, thereby expanding the scope of application.

[0047] The carrier rocket 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 carrier rocket sub-stage fed back by the tethered tooling, and applies a pulling force (or vertical component) opposite to the impact force (generated after the carrier rocket sub-stage is ignited) to the carrier rocket sub-stage, thereby offsetting part of the impact force acting on the carrier rocket sub-stage body itself during the test run, thereby reducing the degree of deformation of the carrier rocket sub-stage body, thereby ensuring the structural integrity of the body.

[0048] Additional aspects and advantages of the present application will be given in part in the following description, which will become apparent from the following description, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0049] 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:

[0050] Figure 1 A schematic diagram of the structure of a launch system during a test mission provided by an embodiment of the present application;

[0051] Figure 2A schematic structural diagram of a tethered tooling for a launch device provided in an embodiment of the present application;

[0052] Figure 3 for Figure 2 A partial enlarged schematic diagram of point Ⅰ in the middle;

[0053] Figure 4 for Figure 2 A partial enlarged schematic diagram of point II in the middle;

[0054] Figure 5 A schematic structural diagram of a fixed launch platform of a launch device provided in an embodiment of the present application;

[0055] Figure 6 for Figure 5 A partial enlarged schematic diagram of point III in the middle;

[0056] Figure 7 A flowchart of a method for using a transmitting device provided in an embodiment of the present application;

[0057] Figure 8 A schematic diagram of a flow chart of a control system adjusting a preload force in a method for using a launch device provided in an embodiment of the present application.

[0058] Reference numerals:

[0059] 100-launching device;

[0060] 10-Fixed launch platform; 11-Pulling assembly; 111-Pulling mechanism; 112-Support lug seat;

[0061] 20-Active launch pad;

[0062] 30-tethered tooling;

[0063] 31-top hat workwear;

[0064] 311-cap; 312-support member; 313-support seat; 314-shackle;

[0065] 32-flexible component;

[0066] 321 - first flexible member; 322 - sensing element; 323 - second flexible member; 324 - pin;

[0067] 40-control system;

[0068] 200-launch vehicle sub-stage. DETAILED DESCRIPTION

[0069] The following describes the embodiments of the present application in conjunction with the accompanying drawings. It should be understood that the embodiments described below in conjunction with the accompanying 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.

[0070] Those skilled in the art will understand that, unless otherwise stated, the terms "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of this 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 their combinations 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" can be implemented as "A", or as "B", or as "A and B".

[0071] In order to make the objectives, technical solutions and advantages of this application clearer, the implementation methods of this application will be further described in detail below with reference to the accompanying drawings.

[0072] 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 and docks with the carrier rocket to complete 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.

[0073] In the prior art, fixed launch pads are converted to launch vehicle sub-stage test platforms by installing safety devices, allowing them to perform launch missions or test missions. However, the safety devices must be removed during launch missions to avoid disrupting the mission. Consequently, extensive disassembly and assembly work is required before and after switching missions, significantly consuming manpower, material resources, and time.

[0074] Furthermore, the safety ropes can only provide a fixed tension to prevent the launch vehicle stage from tipping over, leaving them in a slack state. After the test ignition, the launch vehicle stage's body deforms under different operating conditions, and the ropes are unable to provide pre-tension, potentially leading to severe deformation and structural failure.

[0075] The launch device, usage method, and launch system of the carrier rocket provided in this application are intended to solve the above-mentioned technical problems of related technologies.

[0076] 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-mentioned technical problems with specific embodiments. It should be noted that the following embodiments can refer to, draw on, or combine with each other, and the same terms, similar features, and similar implementation steps in different embodiments will not be repeated.

[0077] The embodiment of the present application provides a launch device 100 of a carrier rocket for performing 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 tool 30 and a control system 40.

[0078] 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 dock with the movable launch platform 20 during a test mission. The fixed launch platform 10 includes a pulling assembly 11 .

[0079] The bottom end of the movable launch platform 20 is used to dock with the fixed launch platform 10, and the top end is used to dock with the carrier rocket sub-stage 200 during the test mission.

[0080] The tethering tool 30 is constructed so that one end is used to be detachably connected 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.

[0081] During the test run, the control system 40 is in communication with the pulling assembly 11 and the mooring fixture 30 , 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 .

[0082] In this embodiment, during the execution of the test mission, the mobile launch platform 20 and the carrier rocket sub-stage 200 can be stacked in sequence 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 execution of the launch mission, the complete carrier rocket is directly docked on the fixed launch platform 10 without the need to install the mobile launch platform 20. The launch device 100 provided in the embodiment of the present application has the function of executing 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 related supporting facilities such as the fixed launch platform 10.

[0083] 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.

[0084] Furthermore, the cost of adding the pull assembly 11 to the fixed launch platform 10 is far less than the cost of constructing a new sub-stage test platform. The cost of adding the pull assembly 11 to the fixed launch platform 10 is also lower than the cost of constructing a new sub-stage test platform. The mobile launch platform 20 and mooring fixture 30 are both supporting facilities for the test mission and do not require separate development. Therefore, the present embodiment can significantly save manpower, material resources, and time costs.

[0085] Moreover, by docking with different movable launch platforms 20, it is possible to dock with launch vehicle sub-stages 200 of different specifications, thereby expanding the scope of application.

[0086] In addition, 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 pre-tightening force based on the pre-tightening force information applied to the carrier rocket 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 ignition of the carrier rocket sub-stage 200) to the carrier rocket sub-stage 200, thereby offsetting part of the impact force acting on the carrier rocket sub-stage 200 body itself during the test run, thereby reducing the degree of deformation of the carrier rocket sub-stage 200 body, thereby ensuring the structural integrity of the body.

[0087] In some possible embodiments, such as Figure 5 and Figure 6 As shown, the pulling assembly 11 includes a pulling mechanism 111 and a lug seat 112 .

[0088] The pulling mechanism 111 is at least partially embedded in and fixed inside the fixed launching platform 10 , is in communication with the control system 40 , and has a top end exposed from the fixed launching platform 10 .

[0089] 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 commissioning task.

[0090] In this embodiment, the pulling mechanism 111 is at least partially embedded and fixed within the body of the fixed launch platform 10, occupying substantially no launch space on the surface of the fixed launch platform 10. This substantially does not affect the launch mission and avoids disassembly and assembly of the pulling mechanism 111 during mission changes, thereby saving costs and improving efficiency. The support lug 112 is relatively small and fixed to the top of the pulling mechanism 111. It extends above the surface of the fixed launch platform 10, facilitating connection with the mooring fixture 30. The pulling mechanism 111 applies a preload to the mooring fixture 30 via the support lug 112.

[0091] In some possible embodiments, such as Figure 2 As shown, the tethering tool 30 includes a top hat tool 31 and a flexible component 32 .

[0092] The top cap tooling 31 is provided on the top of the carrier rocket sub-stage 200 .

[0093] 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.

[0094] The sensor element 322 is in communication with the control system 40 for acquiring the preload force and feeding back the preload force to the control system 40 .

[0095] In this embodiment, during the execution of the test mission, the top cap tooling 31 is covered on the top of the carrier rocket sub-stage 200, and then connected to the support ear seat 112 of the pulling component 11 through the flexible component 32, so that the preload force applied by the pulling component 11 acts on the top of the carrier rocket sub-stage 200, that is, the top of the carrier rocket sub-stage 200 is subjected to the preload force applied by the pulling component 11, and the bottom end is subjected to the reaction force from the movable launch platform 20. The two ends of the carrier rocket sub-stage 200 are subjected to the joint force, so that the molecular structure of the carrier rocket sub-stage 200 itself remains in a relatively stable state, thereby reducing the possibility of deformation.

[0096] Optionally, the first flexible member 321 and the second flexible member 323 are both slender.

[0097] Optionally, both the first flexible member 321 and the second flexible member 323 may include steel wire ropes.

[0098] Optionally, the sensing element 322 includes a force sensor.

[0099] In some possible embodiments, such as Figure 2-Figure 4 As shown, the top hat tooling 31 includes a cover cap 311 and a support member 312 .

[0100] The cover cap 311 is disposed on the top of the launch vehicle sub-stage 200 .

[0101] The support member 312 is fixedly connected to the top of the cover cap 311 and is radially extended with its end extending beyond the edge of the cover cap 311 .

[0102] One end of the first flexible member 321 away from the sensing element 322 is detachably connected to the end of the supporting member 312 .

[0103] In this embodiment, during the execution of the test mission, the cap 311 can cover the top end of the entire carrier rocket 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 carrier rocket sub-stage 200 inside, thereby preventing the carrier rocket 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.

[0104] In some possible embodiments, such as Figure 2-Figure 4 As shown, during the commissioning task, the top hat tooling 31 further includes: a support seat 313 and a shackle 314.

[0105] The side wall of the support base 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 base 313 has a connecting hole.

[0106] The shackle 314 is detachably connected to the connecting hole.

[0107] One end of the first flexible member 321 is sleeved on the shackle 314 .

[0108] In this embodiment, the support base 313 is fixed to the peripheral wall of the cap 311 and supported by the bottom end of the support member 312, thereby strengthening the support member 312 when subjected to downward loads. The support base 313 and the first flexible member 321 are detachably connected by a shackle 314, thereby enabling a detachable connection between the top cap fixture 31 and the flexible assembly 32. This simple structure and easy operation ensure efficient installation of the tie-down fixture 30.

[0109] 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.

[0110] During the execution of the launch mission by the launch device 100, the launch platform 10 is fixed and docked with the carrier rocket.

[0111] During the test 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 communicated with the pulling assembly 11 of the fixed launch platform 10 and the tethering tool 30 respectively.

[0112] 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. The implementation principles are similar and will not be repeated here.

[0113] In this embodiment, the launch device 100 has the function of performing 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 related supporting facilities such as the fixed launch platform 10.

[0114] 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.

[0115] Furthermore, the cost of adding the pull assembly 11 to the fixed launch platform 10 is far less than the cost of constructing a new sub-stage test platform. The cost of adding the pull assembly 11 to the fixed launch platform 10 is also lower than the cost of constructing a new sub-stage test platform. The mobile launch platform 20 and mooring fixture 30 are both supporting facilities for the test mission and do not require separate development. Therefore, the present embodiment can significantly save manpower, material resources, and time costs.

[0116] Moreover, by docking with different movable launch platforms 20, it is possible to dock with launch vehicle sub-stages 200 of different specifications, thereby expanding the scope of application.

[0117] In addition, 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 pre-tightening force based on the pre-tightening force information applied to the carrier rocket 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 ignition of the carrier rocket sub-stage 200) to the carrier rocket sub-stage 200, thereby offsetting part of the impact force acting on the carrier rocket sub-stage 200 body itself during the test run, thereby reducing the degree of deformation of the carrier rocket sub-stage 200 body, thereby ensuring the structural integrity of the body.

[0118] Based on the same inventive concept, the embodiment of the present application also provides a method for using the launch device 100 of the carrier rocket 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:

[0119] S101: During the test run of the launch device 100, the movable launch platform 20 is docked on top of the fixed launch platform 10.

[0120] S102: docking the carrier rocket sub-stage 200 on top of the movable launch pad 20.

[0121] S103: One end of the tethering tooling 30 is detachably connected to the top of the carrier rocket sub-stage 200, and the other end of the tethering tooling 30 is detachably connected to the pulling assembly 11 of the fixed launch platform 10.

[0122] 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 with the pulling assembly 11 of the fixed launch station 10 and the mooring tooling 30 .

[0123] In this embodiment, the fixed launch pad 10 is fixed at the launch site, the movable launch pad 20 that matches the size of the carrier rocket sub-stage 200 is docked with the fixed launch pad 10, the carrier rocket sub-stage 200 is docked with the movable launch pad 20, and the top of the carrier rocket sub-stage 200 is connected to the newly added pulling assembly 11 of the fixed launch pad 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 part of the impact force acting on the rocket body itself of the carrier rocket sub-stage 200 during the test run.

[0124] Moreover, the control system 40 controls the pulling assembly 11 to adjust the preload according to the preload information applied to the carrier rocket 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 carrier rocket 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 carrier rocket sub-stage 200, thereby ensuring the structural integrity of the rocket body.

[0125] It should be noted that the order of docking the mobile launch platform 20 with the fixed launch platform 10 in the above-mentioned 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.

[0126] 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 may also be included:

[0127] The top cap tooling 31 of the tethering tooling 30 is covered on the top of the carrier rocket sub-stage 200 .

[0128] The first flexible member 321 , the sensing element 322 and the second flexible member 323 are connected in sequence to form the flexible assembly 32 of the mooring tool 30 .

[0129] In this embodiment, the top of the carrier rocket 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.

[0130] In some possible embodiments, the above-mentioned step S103 of detachably connecting one end of the tethering tool 30 to the top of the carrier rocket 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 in a transmission manner includes the following steps:

[0131] 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 .

[0132] One end of the second flexible member 323 away from the sensing element 322 is transmission-connected to the ear seat 112 of the pulling assembly 11 via a pin 324 .

[0133] In this embodiment, the first flexible member 321 at one end of the sensing element 322 is detachably connected to the top cap fixture 31 via a shackle 314, and the second flexible member 323 at the other end of the sensing element 322 is detachably connected to the lug seat 112 via a pin 324. This allows the preload force applied by the pulling mechanism 111 to be transmitted sequentially through the lug seat 112, the pin 324, the second flexible member 323, the sensing element 322, and the first flexible member 321 to the top cap fixture 31, thereby acting on the top of the launch vehicle sub-stage 200. Because the sensing element 322 is disposed 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 sensing element 322, thereby allowing the sensing element 322 to acquire the force applied to the first flexible member 321 or the second flexible member 323 and transmit it to the control system 40.

[0134] In some possible embodiments, the control system 40 in step S104 controls the pulling assembly 11 to adjust the preload according to the preload information fed back by the tethering tool 30, including the following steps:

[0135] 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.

[0136] The control system 40 controls the ignition test of the carrier rocket 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 carrier rocket sub-stage 200 under test is within the specified range; if so, it is determined that the real-time preload information meets the design requirements; if not, the pulling assembly 11 is controlled to adjust the preload until the real-time preload information fed back by the tethering tooling 30 meets the design requirements.

[0137] 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 process; 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 carrier rocket sub-stage 200 is controlled to ignite and start testing the carrier rocket sub-stage 200.

[0138] 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 it receives to the control system 40 in real time. The control system 40 then 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 designed preload parameter is within a specified range. If so, the real-time preload information of the mooring fixture 30 is determined to be within a normal range, and the test run can proceed normally. If not, the preload applied by the pulling assembly 11 is controlled and adjusted so that the preload information fed back by the sensor element 322 of the mooring fixture 30 meets the design requirements, thereby 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.

[0139] By applying the embodiments of the present application, at least the following beneficial effects can be achieved:

[0140] 1. During the test run mission, the mobile launch platform 20 and the carrier rocket sub-stage 200 can be stacked in sequence 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 the need to install 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.

[0141] 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.

[0142] 3. The cost of adding the traction assembly 11 is far less than the cost of constructing a fixed launch platform 10. Compared to the cost of building a new sub-stage test platform, the cost of adding the traction assembly 11 to the fixed launch platform 10 in this embodiment of the 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 require separate development. Therefore, this embodiment of the application can significantly save manpower, material resources, and time costs.

[0143] 4. By docking with different movable launch platforms 20, it is possible to dock with launch vehicle sub-stages 200 of different specifications, thereby expanding the scope of application.

[0144] 5. During the test run, the carrier rocket sub-stage 200 is subjected to different impact forces due to changes in propellant consumption. The control system 40 controls the pulling assembly 11 to adjust and implement the preload force based on the preload force information applied to the carrier rocket sub-stage 200 fed back by the tethering tooling 30, thereby applying a pulling force (or vertical component) 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 carrier rocket sub-stage 200 body itself during the test run, thereby reducing the degree of deformation of the carrier rocket sub-stage 200 body, thereby ensuring the structural integrity of the body.

[0145] 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 device or component referred to 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.

[0146] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature specified as "first" or "second" may explicitly or implicitly include one or more of such features. Throughout this application, unless otherwise specified, "plurality" means two or more.

[0147] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to direct connections, indirect connections through an intermediate medium, or internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0148] 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.

[0149] The above is only part of the implementation methods 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 solution of the present application, other similar implementation methods based on the technical ideas of the present application also fall 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 a launch mission and dock with the mobile launch platform during a test mission; the fixed launch platform includes a pulling 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 sub-stage during the test mission; A tethered tooling is configured such that one end is detachably connected to the top end of the carrier rocket sub-stage during a test mission, and the other end is detachably connected to the pulling assembly in a transmission manner; a control system, which is in communication with the pulling assembly and the mooring fixture during the test run, and controls the pulling assembly to adjust the preload of the pulling assembly according to preload information fed back by the mooring fixture; The pulling assembly includes: a pulling mechanism and a lug seat; the pulling mechanism is at least partially embedded in and fixed inside the fixed launch platform, is in communication with the control system, and has a top end exposed from the fixed launch 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 test mission; The tethering tooling includes: a top cap tooling and a flexible component; the top cap tooling is covered on the top of the launch vehicle sub-stage; the flexible component includes a first flexible part, a sensing element and a second flexible part connected in sequence; the end of the first flexible part away from the sensing element is detachably connected to the top cap tooling, and the end of the second flexible part away from the sensing element is detachably connected to the support ear seat of the pulling component; the sensing element is communicatively connected to the control system for obtaining the preload force and feeding it back to the control system.

2. The launch device of a carrier rocket according to claim 1, characterized in that: The top hat tooling comprises: a cover cap, arranged on the top of the carrier rocket sub-stage; A support member, fixedly connected to the top of the cap, is radially arranged, and has an end 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.

3. The launch device of a carrier rocket according to claim 2, characterized in that: The top hat tooling also includes: A support base, the side walls of which are 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 base has a connecting hole; a shackle, detachably connected to the connecting hole; One end of the first flexible member is sleeved on the shackle.

4. A launch system for a carrier rocket, characterized in that: include: A carrier rocket or a carrier rocket sub-stage, and a launch device for the carrier rocket according to any one of claims 1 to 3; During the launch mission of the launch device, including the fixed launch platform, 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 pulling 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 communicated with the traction assembly of the fixed launch platform and the tethered tool respectively.

5. A method for using the launch device of a carrier rocket according to any one of claims 1 to 3, characterized in that: include: During the test run of the launch device, the movable launch platform is docked on top of the fixed launch platform; docking the carrier rocket sub-stage on top of the movable launch pad; Removably connecting one end of the tethered tool to the top of the carrier rocket sub-stage, and removably connecting the other end of the tethered tool 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 with the pulling component of the fixed launch platform and the mooring tooling.

6. The method for using the launch device of a carrier rocket according to claim 5, characterized in that: Before docking the mobile launch pad on top of the fixed launch pad, it also includes: Installing the top cap of the tethering tooling on the top of the carrier rocket 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.

7. The method for using the launch device of a carrier rocket according to claim 6, 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 sensing element is transmission-connected to the ear seat of the pulling assembly through a pin.

8. The method for using the launch device of a carrier rocket according to claim 7, 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 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, controls the pulling assembly 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 carrier rocket 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 carrier rocket 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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