Flight Structure Launcher and Aircraft Launch System

Abstract

The present application provides a flight structure launching device and an aircraft launching system. The flight structure launching device includes: a launching platform; a slewing mechanism rotatably disposed on the launching platform, the slewing mechanism being used to carry the flight structure to be launched; a slewing driving mechanism connected to the slewing mechanism, the slewing driving mechanism being used to drive the slewing mechanism to rotate so as to adjust the azimuth angle of the flight structure to be launched; a slewing locking mechanism for locking the slewing mechanism on the launching platform; a gas flow guiding structure located at at least a part of the outer periphery of the slewing mechanism, the gas flow guiding structure being used to guide the gas flow generated by the flight structure to be launched; electrical equipment connected to at least the slewing mechanism, the electrical equipment having at least one function of control, driving, and power supply; the slewing driving mechanism, the slewing locking mechanism, the gas flow guiding structure, and the electrical equipment are integrally arranged on the launching platform. The present application realizes the reduction of the research and development cost and the improvement of the functions of the launching system.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology. Specifically, the present application relates to a flight structure launching device and an aircraft launching system. Background Art

[0002] Currently, the requirements for the flight speed and flight distance of cruise targets are increasing day by day, resulting in an increasingly large take-off mass. In response to this situation, new targets mostly adopt vertical thermal launch or box-type guide rail (or box-type adapter) thermal launch.

[0003] For vertical thermal launch, its launch system only needs to develop a launch pad, hoist and flip the target to a vertical state, and then place it above the launch pad. After the engine ignites, it takes off in a direction perpendicular to the launch pad; however, this method will reduce the target supply distance due to the influence of the ballistic trajectory.

[0004] Box-type guide rail (or box-type adapter) thermal launch is inclined thermal launch. For the inclined thermal launch of this type of target, it often adopts a motor vehicle-mounted type launch. The second-class chassis is used as a mobile platform, and a launch box or launch rack is installed on it. Through multiple groups of sliders (or adapters) reserved on the target and the guide rails of the launch box (or launch rack), the support and guidance before the target leaves the box (rack) are realized; however, this method requires the use of a second-class chassis as a launch platform, integrating various measurement, launch control, and power supply equipment onto the second-class chassis. At the same time, considering the increasingly large take-off mass of cruise targets, the adjustment of the azimuth angle and elevation angle is electrically adjusted, and this vehicle-mounted launch method will result in a higher cost during the research and development stage. Summary of the Invention

[0005] In view of the shortcomings of the existing methods, the present application proposes a flight structure launching device and an aircraft launching system to solve the technical problems of high launch cost during the research and development stage of inclined launch of cruise targets and loss of target supply distance in vertical launch in related technologies.

[0006] In a first aspect, an embodiment of the present application provides a flight structure launching device, including:

[0007] A launch platform;

[0008] A slewing mechanism rotatably arranged on the launch platform, and the slewing mechanism is used to carry the flight structure to be launched;

[0009] A slewing drive mechanism connected to the slewing mechanism, and the slewing drive mechanism is used to drive the slewing mechanism to rotate to adjust the azimuth angle of the flight structure to be launched;

[0010] A slewing locking mechanism for locking the slewing mechanism on the launch platform;

[0011] The gas flow guiding structure is located at at least a part of the outer periphery of the slewing mechanism, and is used for guiding the gas flow generated by the flight structure to be launched.

[0012] The electrical equipment is at least connected to the slewing mechanism, and has at least one of the functions of control, driving and power supply.

[0013] The slewing drive mechanism, the slewing locking mechanism, the gas flow guiding structure and the electrical equipment are integrally arranged on the launch platform.

[0014] Optionally, the slewing drive mechanism includes:

[0015] The driving component is installed on the launch platform.

[0016] The first transmission component is connected to the driving component, and the first transmission component has an output part movably arranged in the first direction; under the drive of the driving component, the output part moves relative to the launch platform.

[0017] The second transmission component is respectively connected to the output part and the slewing mechanism, and the second transmission component is rotatably arranged relative to the output part; when the output part moves, it drives the second transmission component and the slewing mechanism to rotate relative to the launch platform in sequence.

[0018] Optionally, it includes at least one of the following:

[0019] The first transmission component includes a lead screw extending in the first direction, a driving nut threadedly engaged with the lead screw, and a guiding structure connected to the driving nut. The lead screw is rotatably installed on the launch platform, the driving component drives the lead screw to rotate, the driving nut serves as the output part, and the guiding structure is used for guiding the movement of the driving nut in the first direction.

[0020] The second transmission component includes a link structure and an adapter seat. One end of the link structure is pivotally connected to the output part, and the other end is pivotally connected to the adapter seat. The adapter seat is fixedly connected to the slewing mechanism.

[0021] The driving component includes a handwheel.

[0022] Optionally, it includes at least one of the following:

[0023] The slewing drive mechanism further includes a first mounting seat and a second mounting seat fixedly installed on the launch platform. Both ends of the lead screw are respectively rotatably connected to the first mounting seat and the second mounting seat.

[0024] The first transmission component further includes a worm gear and a worm. The driving component is connected to the worm to drive the worm to rotate. The worm is engaged with the worm gear to drive the worm gear to rotate. The worm gear is sleeved on the lead screw to drive the lead screw to rotate.

[0025] The guiding structure includes a slider fixedly connected to the driving nut and a guide rail provided on the launching platform. The guide rail extends in the first direction, and the slider is slidably engaged with the guide rail.

[0026] The slewing drive mechanism further includes a sliding seat fixedly connected to the driving nut, and a plurality of guiding structures are sequentially arranged on the sliding seat in the second direction.

[0027] Optionally, the flight structure launcher further includes a carrying cabin, which is detachably mounted on the launching platform.

[0028] The electrical equipment includes a control box, a generator set, and a hydraulic system. The control box is connected to at least one of the generator set, the hydraulic system, and the slewing mechanism. The generator set and the hydraulic system are respectively connected to the slewing mechanism.

[0029] The control box, the generator set, and the hydraulic system are integrated in the carrying cabin.

[0030] Optionally, the flight structure launcher further includes a marching locking mechanism, which includes a lateral limiting seat and a locking member rotatably provided on the lateral limiting seat.

[0031] The lateral limiting seat is mounted on the carrying cabin, and a limiting groove is provided on the lateral limiting seat. The limiting groove is used to cooperate with the erection frame of the slewing mechanism to limit the rotation of the erection frame in the horizontal plane.

[0032] The locking member has a locking position and an unlocking position relative to the lateral limiting seat. When the locking member is in the locking position, the locking member is locked in the groove of the erection frame through a fastener to limit the rotation of the erection frame in the vertical plane.

[0033] Optionally, it includes at least one of the following:

[0034] The opening of the limiting groove is arranged upward, and on the direction from the bottom of the limiting groove to the opening, the side wall of the limiting groove inclines outward.

[0035] The locking member includes a bolt, and the bolt is rotatably connected to the lateral limiting seat through a pin shaft. The fastener includes a nut for threadedly cooperating with the bolt.

[0036] A plurality of locking members are provided on the lateral limiting seat, and the arrangement direction of the plurality of locking members is parallel to the extending direction of the side wall of the limiting groove.

[0037] Optionally, it includes at least one of the following:

[0038] The launching platform is provided with a floor interface assembly, and the launching platform is fixed to the ground of the launching position by cooperating with or connecting to the floor interface assembly through floor bolts.

[0039] The gas flow guiding structure includes a deflector which is arranged on a partial outer peripheral side of the slewing mechanism. The top surface of the deflector is an inclined surface that slopes downward in a direction away from the slewing mechanism, and the gas flow is guided by the inclined surface.

[0040] The gas flow guiding structure includes a gas flow baffle which includes a main body bending plate and a side sealing plate. The main body bending plate is connected to the launch platform, and the side sealing plate is connected to the main body bending plate and encloses a receiving cavity for accommodating the slewing drive mechanism to prevent the gas flow from blowing onto the slewing drive mechanism.

[0041] Optionally, the slewing locking mechanism includes a slewing locking seat connected to the launch platform.

[0042] A plurality of locking holes are provided on the slewing locking seat, and the plurality of locking holes are arranged at intervals in sequence around the rotation axis of the slewing mechanism. An assembly hole is provided on the slewing table of the slewing mechanism, and a fastener is used to pass through the locking hole and the assembly hole to fixedly connect the slewing locking seat and the slewing table.

[0043] Optionally, it includes at least one of the following:

[0044] A plurality of slewing locking seats are provided, and the plurality of slewing locking seats are arranged at intervals along the circumferential direction of the slewing table.

[0045] A plurality of assembly holes are provided on the slewing table and are arranged at intervals in sequence around the rotation axis of the slewing table.

[0046] The slewing locking mechanism further includes an auxiliary slewing locking structure which includes a main body mounting seat installed on the launch platform, an adjusting member movably arranged on the main body mounting seat, a support seat installed at one end of the adjusting member, and a driving member installed at the other end of the adjusting member. The adjusting member is driven to move by the driving member, the support seat is connected to the adjusting member by a ball joint, and the support seat is used to abut against the slewing table.

[0047] In a second aspect, an embodiment of the present application provides an aircraft launch system, including:

[0048] The flight structure launch device as described above;

[0049] An aircraft, which is placed as a flight structure to be launched in the launch box of the slewing mechanism of the flight structure launch device.

[0050] The beneficial technical effects brought by the technical solution provided by the embodiment of the present application include:

[0051] In the embodiments of the present application, a rotary mechanism is used to carry a flight structure to be launched (such as an aircraft). The rotary mechanism is rotatably arranged relative to the launch platform. By rotating the rotary mechanism, the flight structure to be launched can be driven to rotate relative to the launch platform, thereby adjusting the azimuth angle of the flight structure to be launched. The rotary drive mechanism is connected to the rotary mechanism. By means of the rotary drive mechanism, the rotary mechanism can be driven to rotate, thereby driving the flight structure to be launched to rotate, achieving the purpose of adjusting the azimuth angle of the flight structure to be launched. The rotary locking mechanism can lock the rotary mechanism on the launch platform, thereby fixing the flight structure to be launched at the target azimuth angle. A gas flow guiding structure is arranged on at least part of the outer periphery of the rotary mechanism, so that the gas flow generated by the flight structure to be launched can be guided through the gas flow guiding structure. The electrical equipment provides at least one of the functions of control, drive, and power supply to the rotary mechanism at least.

[0052] In the embodiments of the present application, the rotary drive mechanism, the rotary locking mechanism, the gas flow guiding structure, and the electrical equipment are integrated on the launch platform, adopting a highly integrated design. The functions such as the installation of hydraulic and electrical equipment, azimuth angle adjustment, rotary locking and unlocking, and gas flow guiding are integrated into the launch platform, which not only reduces the research and development cost but also improves the functions of the launch system. Moreover, in the embodiments of the present application, by setting the rotary mechanism, the azimuth angle of the flight structure to be launched can be adjusted. Therefore, the flight structure launch device provided by the embodiments of the present application solves the difficulties in aspects such as high launch cost in the research and development stage of inclined launch of cruise targets and loss of target supply distance in vertical launch.

[0053] Some of the additional aspects and advantages of the present application will be given in the following description, which will become apparent from the following description or be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] The above-mentioned and / or additional aspects and advantages of the present application will become apparent and easy to understand from the following description of the embodiments in conjunction with the drawings, where:

[0055] Figure 1 is a schematic structural diagram of a flight structure launch device provided by an embodiment of the present application;

[0056] Figure 2 is a partial schematic structural diagram of a flight structure launch device provided by an embodiment of the present application (the rotary mechanism is not shown);

[0057] Figure 3 is a schematic structural diagram of the launch platform of a flight structure launch device provided by an embodiment of the present application;

[0058] Figure 4 is a schematic structural diagram of the rotary drive mechanism of a flight structure launch device provided by an embodiment of the present application;

[0059] Figure 5 Schematic diagram of the structure of the electrical equipment of a flight structure launcher provided by an embodiment of the present application;

[0060] Figure 6 Schematic diagram of the structure of the carrying cabin of a flight structure launcher provided by an embodiment of the present application;

[0061] Figure 7 Schematic diagram of the structure of the marching locking mechanism of a flight structure launcher provided by an embodiment of the present application;

[0062] Figure 8 Schematic diagram of the structure of the deflector of a flight structure launcher provided by an embodiment of the present application;

[0063] Figure 9 Schematic diagram of the structure of the gas flow baffle of a flight structure launcher provided by an embodiment of the present application;

[0064] Figure 10 Schematic diagram of the structure of the rotary locking seat of a flight structure launcher provided by an embodiment of the present application;

[0065] Figure 11 Schematic diagram of the structure of the auxiliary rotary locking structure of a flight structure launcher provided by an embodiment of the present application.

[0066] Reference numerals:

[0067] 1, Launching platform;

[0068] 1-1, Truss main body; 1-2, Lifting lug; 1-3, Floor interface assembly; 1-4, Leveling leg interface assembly; 1-5, Auxiliary rotary locking structure installation assembly; 1-6, Rotary locking seat installation block; 1-7, Deflector installation seat; 1-8, Slewing bearing installation seat; 1-9, Rotary drive mechanism installation seat; 1-10, Control box installation block; 1-11, Generator set installation block; 1-12, Hydraulic system installation block; 1-13, Carrying cabin installation block; 1-14, Tightening block; 1-15, Tarpaulin fixing block; 118, Wiring groove;

[0069] 2, Deflector;

[0070] 2-1, Front baffle; 2-2, Sealing plate; 2-3, Bottom mounting plate; 2-4, First reinforcing rib; 2-5, Second reinforcing rib;

[0071] 3, Carrying cabin;

[0072] 3-1, Carrying cabin main body; 3-2, Hoisting seat; 3-3, Marching locking mechanism installation seat; 3-4, Mounting feet;

[0073] 4, Rotary locking seat;

[0074] 4-1. Upper mounting plate; 4-2. Lower fixing plate; 4-3. Intermediate support plate; 4-4. Side rib plate;

[0075] 5. Auxiliary slewing locking structure;

[0076] 5-1. Main body mounting seat; 5-2. Adjusting member; 5-3. Support seat; 5-4. Ball head sealing plate; 5-5. Driving member; 5-6. Limit top plate; 5-7. Locking nut;

[0077] 6. Gas flow baffle;

[0078] 6-1. Main body bending plate; 6-2. Side sealing plate; 6-3. Main body reinforcing rib;

[0079] 7. Marching locking mechanism;

[0080] 7-1. Lateral limit seat; 7-2. Pin shaft; 7-3. Locking member;

[0081] 8. Leveling support leg;

[0082] 9. Tool box;

[0083] 10. Slewing drive mechanism;

[0084] 8-1. First mounting seat; 8-2. Second mounting seat; 8-3. Sliding seat; 8-4. Lead screw; 8-5. Adapter ear; 8-6. Limit pin shaft; 8-7. Adapter seat; 8-8. Slide block; 8-9. Guide rail; 8-10. Link structure;

[0085] 11. Control box; 12. Generator set; 13. Hydraulic system;

[0086] 14. Slewing bearing;

[0087] 15. Slewing platform; 16. Erection frame; 17. Hydraulic cylinder; 18. Launch box. Detailed implementation manners

[0088] The embodiments of the present application will be described below with reference to the accompanying drawings in the present application. 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.

[0089] Those skilled in the art can understand that, unless specifically stated otherwise, the terms "the" and "said" used herein may also include the plural form. It should be further understood that the term "comprising" used in the specification of the present application means the presence of the described features, integers, steps, operations, and / or components, but does not exclude the presence of other features, information, data, steps, operations, components, and / or combinations thereof supported by the art. The term "and / or" used herein means at least one of the items defined by the term. For example, "A and / or B" can be implemented as "A", or "B", or "A and B".

[0090] To make the objectives, technical solutions, and advantages of the present application clearer, the embodiments of the present application will be further described in detail below with reference to the accompanying drawings.

[0091] In view of the problems in the related art that the vertical thermal emission method is affected by the ballistic trajectory and reduces its target supply distance, and the thermal emission of the box-type guide rail (or box-type adapter) often adopts a motor vehicle-mounted type of launch, which requires the use of a Class II chassis as the launch platform, and various launch measurement, control, and power supply devices are integrated onto the Class II chassis, and this vehicle-mounted launch method results in relatively high costs during the research and development stage, etc., the present application provides a flight structure launch device and an aircraft launch system, aiming to solve at least one of the above technical problems in the related art.

[0092] The technical solutions of the present application and how the technical solutions of the present application solve the above technical problems will be described in detail below with specific embodiments. It should be noted that the following embodiments can be referenced, learned from, or combined with each other. For the same terms, similar features, and similar implementation steps in different embodiments, they will not be described repeatedly.

[0093] An embodiment of the present application provides a flight structure launch device. The structural schematic diagram of the flight structure launch device is as shown in Figure 1 and Figure 2 and includes: a launch platform 1, a slewing mechanism, a slewing drive mechanism 10, a slewing locking mechanism, a gas flow guiding structure, and electrical equipment.

[0094] The slewing mechanism is rotatably arranged on the launch platform 1. The slewing mechanism is used to carry the flight structure to be launched. The slewing drive mechanism 10 is connected to the slewing mechanism. The slewing drive mechanism 10 is used to drive the slewing mechanism to rotate to adjust the azimuth angle of the flight structure to be launched. The slewing locking mechanism is used to lock the slewing mechanism on the launch platform 1. The gas flow guiding structure is located at least partially on the outer periphery of the slewing mechanism. The gas flow guiding structure is used to guide the gas flow generated by the flight structure to be launched. The electrical equipment is at least connected to the slewing mechanism. The electrical equipment has at least one of the functions of control, drive, and power supply. The slewing drive mechanism 10, the slewing locking mechanism, the gas flow guiding structure, and the electrical equipment are integrally arranged on the launch platform 1.

[0095] In the embodiment of the present application, a rotating mechanism is used to carry the flight structure to be launched (such as an aircraft). The rotating mechanism is rotatably arranged relative to the launch platform 1. By rotating the rotating mechanism, the flight structure to be launched can be driven to rotate relative to the launch platform 1, so as to adjust the azimuth angle of the flight structure to be launched. The rotary drive mechanism 10 is connected to the rotary mechanism. By the rotary drive mechanism 10, the rotary mechanism can be driven to rotate, so as to drive the flight structure to be launched to rotate, and the purpose of adjusting the azimuth angle of the flight structure to be launched is achieved. The rotary locking mechanism can lock the rotary mechanism on the launch platform 1, so as to fix the flight structure to be launched at the target azimuth angle. A gas flow guiding structure is arranged on at least part of the outer periphery of the rotary mechanism, so that the gas flow generated by the flight structure to be launched can be guided through the gas flow guiding structure. The electrical equipment provides at least one of the functions of control, drive and power supply to the rotary mechanism at least.

[0096] In the embodiment of the present application, the rotary drive mechanism 10, the rotary locking mechanism, the gas flow guiding structure and the electrical equipment are integrated on the launch platform 1. Adopting a highly integrated design, functions such as installation of hydraulic and electrical equipment, azimuth angle adjustment, rotary locking and unlocking, and gas flow guiding are integrated into the launch platform, which not only reduces the research and development cost, but also improves the functions of the launch system. And in the embodiment of the present application, by setting the rotary mechanism, the azimuth angle of the flight structure to be launched is adjustable. Therefore, the flight structure launch device provided by the embodiment of the present application solves the difficulties in aspects such as high launch cost in the research and development stage of inclined launch of cruise targets and loss of target supply distance in vertical launch.

[0097] Optionally, as Figure 2 and Figure 4 shown, in the embodiment of the present application, the rotary drive mechanism 10 includes a drive component, a first transmission component and a second transmission component. The drive component is installed on the launch platform 1; the first transmission component is connected to the drive component, and the first transmission component has an output part movably arranged along a first direction; under the drive of the drive component, the output part moves relative to the launch platform 1; the second transmission component is respectively connected to the output part and the rotary mechanism, and the second transmission component is rotatably arranged relative to the output part; when the output part moves, the second transmission component and the rotary mechanism are driven to rotate relative to the launch platform 1 in sequence.

[0098] In the embodiment of the present application, the drive component, the first transmission component, the second transmission component and the rotary mechanism are connected in sequence. The drive component can drive the output part of the first transmission component to move relative to the launch platform 1 in the first direction. The output part is rotatably connected to the second transmission component. When the output part moves, the second transmission component is driven to rotate relative to the launch platform 1, so that the second transmission component can drive the rotary mechanism to rotate, thereby driving the flight structure to be launched to rotate, and realizing azimuth angle adjustment.

[0099] Optionally, as Figure 4 shown, in the embodiment of the present application, the first transmission component includes a lead screw 8-4 extending along a first direction, a driving nut threadedly engaged with the lead screw 8-4, and a guiding structure connected to the driving nut. The lead screw 8-4 is rotatably mounted on the launching platform 1. The driving component drives the lead screw 8-4 to rotate. The driving nut serves as an output part, and the guiding structure is used to guide the movement of the driving nut along the first direction.

[0100] In the embodiment of the present application, the lead screw 8-4 is rotatably arranged relative to the launching platform 1 and connected to the driving component, and the driving component can drive the lead screw 8-4 to rotate. The lead screw 8-4 is threadedly engaged with the driving nut, and a guiding structure is arranged to limit the movement direction of the driving nut, so that when the lead screw 8-4 rotates, the rotational movement of the lead screw 8-4 is converted into the translational movement of the driving nut. The movement of the driving nut is guided by the guiding structure to prevent the driving nut from rotating with the lead screw 8-4, thereby ensuring that the driving nut moves along the first direction.

[0101] Optionally, in the embodiment of the present application, the first transmission component further includes a worm gear and a worm. The driving component is connected to the worm to drive the worm to rotate. The worm is engaged with the worm gear to drive the worm gear to rotate. The worm gear is sleeved on the lead screw 8-4 to drive the lead screw 8-4 to rotate.

[0102] Optionally, in the embodiment of the present application, the first transmission component adopts a screw jack.

[0103] Optionally, as Figure 4 shown, in the embodiment of the present application, the slewing drive mechanism 10 further includes a first mounting seat 8-1 and a second mounting seat 8-2 fixedly mounted on the launching platform 1. Two ends of the lead screw 8-4 are respectively rotatably connected to the first mounting seat 8-1 and the second mounting seat 8-2.

[0104] Optionally, in the embodiment of the present application, the lead screw 8-4 is respectively rotatably connected to the first mounting seat 8-1 and the second mounting seat 8-2 through bearings. The extending direction of the lead screw 8-4 is parallel to the first direction, that is, parallel to the arrangement direction of the first mounting seat 8-1 and the second mounting seat 8-2.

[0105] Optionally, as Figure 4 shown, in the embodiment of the present application, the guiding structure includes a slider 8-8 fixedly connected to the driving nut and a guide rail 8-9 arranged on the launching platform 1. The guide rail 8-9 extends along the first direction, and the slider 8-8 is slidably engaged with the guide rail 8-9. The rotation of the lead screw 8-4 applies a force to the driving nut. The driving nut is connected to the slider 8-8, restricting the circumferential movement of the driving nut around the lead screw 8-4 and converting it into a linear movement. The slider 8-8 is slidably engaged with the guide rail 8-9, and both the driving nut and the slider 8-8 move along the guide rail 8-9 to achieve the guiding effect.

[0106] Alternatively, as Figure 4 As shown, in the embodiment of the present application, the rotary drive mechanism 10 further includes a sliding seat 8-3 fixedly connected to the drive nut. The sliding seat 8-3 is provided with a plurality of guide structures arranged sequentially in the second direction. The sliders 8-8 of the plurality of guide structures are each fixedly connected to the sliding seat 8-3. The sliders 8-8 of the plurality of guide structures are slidably engaged with the guide rails 8-9 of the plurality of guide structures in a one-to-one correspondence.

[0107] In the embodiment of the present application, the drive nut is fixedly connected to multiple sliders 8-8 through a sliding seat 8-3, so that it can move along multiple guide rails 8-9. Multiple guide structures guide simultaneously to ensure the stability of the movement of the drive nut.

[0108] Alternatively, as Figure 4 As shown, in the embodiment of the present application, the arrangement direction of the multiple guide structures is perpendicular to the extension direction of the screw 8-4, that is, the second direction is perpendicular to the first direction.

[0109] Alternatively, as Figure 4 As shown, in this embodiment of the present application, the drive component includes a handwheel. By manually turning the handwheel, the worm, turbine, and lead screw 8-4 rotate sequentially, thereby driving the drive nut, which in turn drives the second transmission component and the rotary mechanism to adjust the azimuth of the flight structure to be launched. This convenient operation allows for azimuth adjustment without the need for power, eliminating the power consumption and cost associated with traditional electric adjustment.

[0110] Of course, in other optional embodiments of the present application, the driving component can also include a motor or other electric driving component according to actual needs and actual conditions to achieve automatic drive and improve the degree of automation and mechanization.

[0111] Optionally, in the embodiment of the present application, the rotary drive mechanism 10 further includes a transmission, which is disposed between the drive component and the first transmission component.

[0112] Optionally, in an embodiment of the present application, the handwheel is connected to the driving gear of the transmission, driving the driving gear to rotate, the driving gear is engaged with the driven gear, driving the driven gear to rotate, and the driven gear is connected to the worm, driving the worm to rotate.

[0113] Optionally, in the embodiment of the present application, the transmission may be a speed reducer or a speed increaser.

[0114] Alternatively, as Figure 4 As shown, in the embodiment of the present application, the second transmission component includes a connecting rod structure 8-10 and an adapter seat 8-7, one end of the connecting rod structure 8-10 is pivotally connected to the output part, and the other end is pivotally connected to the adapter seat 8-7, and the adapter seat 8-7 is fixedly connected to the rotating mechanism.

[0115] Optionally, as Figure 4 shown, in the embodiment of the present application, a transfer lug 8-5 is provided on the drive nut or the sliding seat 8-3. One end of the link structure 8-10 is pivotally connected to the transfer lug 8-5 through a limit pin shaft 8-6, and the other end of the transfer seat 8-7 and the link structure 8-10 is pivotally connected through another set of transfer lugs and limit pin shafts.

[0116] In the embodiment of the present application, the drive nut moves along the first direction, driving the link structure 8-10 to rotate or swing within a certain range. The transfer seat 8-7 is fixedly connected to the slewing mechanism. Driven by the link structure 8-10, the transfer seat 8-7 and the slewing mechanism rotate, thereby adjusting the azimuth angle of the flight structure to be launched.

[0117] Optionally, in the embodiment of the present application, the length of the link structure 8-10 is adjustable. By adjusting the length of the link structure 8-10, the adjustable range of the azimuth angle of the flight structure to be launched can be adjusted, improving adaptability and flexibility.

[0118] Specifically, as Figure 4 shown, in the embodiment of the present application, the first mounting seat 8-1 and the second mounting seat 8-2 of the slewing drive mechanism 10 are respectively connected to the launch platform 1. The sliding seat 8-3 is connected to the guide rail 8-9 mounted on the launch platform 1 through a slider 8-8. Both ends of the lead screw 8-4 are rotatably connected to the first mounting seat 8-1 and the second mounting seat 8-2 respectively. The drive nut is connected to the sliding seat 8-3. The sliding seat 8-3 is connected to the turntable 15 of the slewing mechanism through a transfer lug 8-5, a link structure 8-10, and a transfer seat 8-7, thereby driving the turntable 15 to rotate. The slewing drive mechanism 10 can use a hand-cranked screw jack to make the drive nut perform an axial movement along the lead screw 8-4. Through the combination of the transfer lug 8-5, the link structure 8-10, and the transfer seat 8-7, the turntable 15 is driven to rotate around the slewing bearing 14.

[0119] The embodiment of the present application adopts a link mechanism type formed by a screw jack and the combination of the sliding seat 8-3, the transfer lug 8-5, the link structure 8-10, and the transfer seat 8-7. It can realize the slewing function under large loads by hand-cranking, that is, without power supply, and the azimuth angle of the launch system can also be adjusted. The manual and portable adjustment of the azimuth angle is realized by using a screw jack in combination with a link mechanism, and the reliable locking of the turntable 15 is realized through a variety of slewing locking mechanisms. The flight structure launch device of the embodiment of the present application has the characteristics of high integration, avoiding the problems of power consumption and cost of traditional electric adjustment, simplifying the process and reducing costs.

[0120] Optionally, as Figure 2 、 Figure 5 and Figure 6As shown in the figure, in the embodiment of the present application, the flight structure launching device further includes a bearing cabin 3, which is detachably installed on the launching platform 1; the electrical equipment includes a control box 11, a generator set 12 and a hydraulic system 13. The control box 11 is connected to at least one of the generator set 12, the hydraulic system 13 and the slewing mechanism. The generator set 12 and the hydraulic system 13 are respectively connected to the slewing mechanism; the control box 11, the generator set 12 and the hydraulic system 13 are integrated in the bearing cabin 3.

[0121] In the embodiment of the present application, the control box 11, the generator set 12 and the hydraulic system 13 are all installed on the launching platform 1 and integrated in the bearing cabin 3. The launching platform 1 can be used to install hydraulic and electrical equipment such as the control box 11, the generator set 12 and the hydraulic system 13 (such as a hydraulic pump station). The bearing cabin 3 is mainly used for protecting the internal hydraulic and electrical equipment.

[0122] Optionally, as Figure 1 and Figure 5 As shown in the figure, in the embodiment of the present application, the slewing mechanism includes a slewing platform 15, an erection frame 16, a hydraulic cylinder 17 and a launching box 18.

[0123] The slewing platform 15 is rotatably connected to the launching platform 1 through a slewing bearing 14. The erection frame 16 and the hydraulic cylinder 17 are both arranged on the slewing platform 15. The launching box 18 is arranged on the erection frame 16. The flight structure to be launched can be placed in the launching box 18. The rotation of the slewing platform 15 can drive the erection frame 16, the hydraulic cylinder 17 and the launching box 18 to rotate together, so as to adjust the azimuth angle of the flight structure to be launched.

[0124] One end of the erection frame 16 is rotatably connected to the slewing platform 15. One end of the hydraulic cylinder 17 is rotatably connected to the slewing platform 15. The other end of the hydraulic cylinder 17 is rotatably connected to the other end of the erection frame 16. The hydraulic cylinder 17 is connected to the hydraulic system 13. The hydraulic system 13 drives the hydraulic cylinder 17 to rotate in the vertical plane relative to the slewing platform 15, so as to drive the erection frame 16 and the launching box 18 to rotate in the vertical plane, and further adjust the elevation angle of the flight structure to be launched.

[0125] Optionally, as Figure 5 As shown in the figure, in the embodiment of the present application, the generator set 12 is used to supply power to the electrical equipment in the flight structure launching device. The control box 11 is respectively connected to the hydraulic system 13 and other electrical equipment to control the hydraulic system 13 and other electrical equipment, such as controlling the opening or closing.

[0126] Optionally, as Figure 3 As shown in the figure, in the embodiment of the present application, a wire trough 118 is provided on the launching platform 1. The wire trough 118 is used to collect and arrange the wires between the generator set 12 and the electrical equipment, etc., which can keep it clean and beautiful.

[0127] Optionally, as shown in Figure 6 In the embodiment of the present application, the carrying cabin 3 includes a carrying cabin main body 3-1, a hoisting seat 3-2, a marching locking mechanism mounting seat 3-3, and mounting feet 3-4. The carrying cabin main body 3-1 is mainly used for protecting the internal hydraulic and electrical equipment. Considering the compatibility design, the marching locking mechanism mounting seat 3-3 is arranged on the top of the carrying cabin main body 3-1, and the inside is strengthened to realize the installation of the marching locking mechanism 7. The carrying cabin main body 3-1 can be connected to the ground launch platform 1 by using the mounting feet 3-4 around it, and the four hoisting seats 3-2 on the top can realize the hoisting of the carrying cabin main body 3-1.

[0128] Optionally, as shown in Figure 2 and Figure 7 In the embodiment of the present application, the flight structure launch device further includes a marching locking mechanism 7. The marching locking mechanism 7 includes a lateral limiting seat 7-1 and a locking member 7-3 rotatably arranged on the lateral limiting seat 7-1; the lateral limiting seat 7-1 is installed on the carrying cabin 3, and a limiting groove is provided on the lateral limiting seat 7-1. The limiting groove is used to cooperate with the erection frame 16 of the slewing mechanism to limit the rotation of the erection frame 16 in the horizontal plane; the locking member 7-3 has a locking position and an unlocking position relative to the lateral limiting seat 7-1. When the locking member 7-3 is in the locking position, the locking member 7-3 is locked in the groove of the erection frame 16 through a fastener to limit the rotation of the erection frame 16 in the vertical plane.

[0129] In the embodiment of the present application, when the carrying cabin 3 completes the protection of the internal hydraulic and electrical equipment, the marching locking mechanism mounting seat 3-3 located at the top can be used to also serve as the installation interface for the marching locking mechanism 7.

[0130] In the embodiment of the present application, the lateral limiting seat 7-1 of the marching locking mechanism 7 is the main load-bearing structure. The limiting groove on the lateral limiting seat 7-1 is used to cooperate with the erection frame 16 to limit the erection frame 16 in the limiting groove and limit the rotation of the erection frame 16 in the horizontal plane, realizing the lateral fixation of the erection frame 16, so that the erection frame 16 cannot move in the horizontal plane; the locking member 7-3 is rotatably arranged relative to the lateral limiting seat 7-1, and the locking member 7-3 can be switched back and forth between the locking position and the unlocking position. When the locking member 7-3 rotates into the corresponding groove on the erection frame 16, when the locking member 7-3 is in the locking position, the locking member 7-3 can be locked in the groove of the erection frame 16 through a fastener to limit the rotation of the erection frame 16 in the vertical plane, realizing the up-and-down fixation of the erection frame 16, so that the erection frame 16 cannot move in the vertical plane.

[0131] Optionally, as shown in Figure 7 In the embodiment of the present application, the opening of the limiting groove is arranged upward, and on the direction from the bottom of the limiting groove to the opening, the side wall of the limiting groove inclines outward.

[0132] In the embodiment of the present application, along the direction from the bottom of the limiting groove to the opening, the side wall of the limiting groove is an inclined plane that slopes outward, and the cross-sectional area of the limiting groove gradually increases in the horizontal plane. By using the inclined plane inside the limiting groove to cooperate with the wedge block of the erection frame 16, on the one hand, the lateral fixation of the erection frame 16 can be achieved, and on the other hand, when the erection frame 16 is lowered, the inclined plane can also play a guiding role to make it more convenient for the wedge block to enter the limiting groove.

[0133] Optionally, as Figure 7 shown, in the embodiment of the present application, the locking member 7-3 includes a bolt, and the bolt is rotatably connected to the lateral limiting seat 7-1 through a pin shaft 7-2. The fastening member includes a nut for threadedly cooperating with the bolt. By rotating the loose bolt into the corresponding groove of the erection frame 16 and then tightening it with the nut, the up-and-down fixation of the erection frame 16 is achieved.

[0134] In the embodiment of the present application, through the design of the limiting groove, inclined plane and loose bolt, the marching locking function of the erection frame 16 is realized.

[0135] Optionally, as Figure 7 shown, in the embodiment of the present application, a plurality of locking members 7-3 are provided on the lateral limiting seat 7-1, and the arrangement direction of the plurality of locking members 7-3 is parallel to the extension direction of the side wall of the limiting groove.

[0136] Setting a plurality of locking members 7-3 can improve the locking effect. Arranging the plurality of locking members 7-3 in sequence along the extension direction of the side wall of the limiting groove is convenient for arrangement and operation.

[0137] It should be noted that in the embodiment of the present application, "a plurality" includes two and more than two.

[0138] Optionally, as Figure 3 shown, in the embodiment of the present application, a floor interface assembly 1-3 is provided on the launch platform 1, and the launch platform 1 is fixed to the ground of the launch site by cooperating with or connecting to the floor interface assembly 1-3 through floor bolts.

[0139] Optionally, in the embodiment of the present application, a plurality of floor interface assemblies 1-3 are provided on the launch platform 1. Floor interface assemblies 1-3 are respectively provided on both sides of the launch platform 1 in the first direction.

[0140] In the embodiment of the present application, when the launch platform 1 lands on the launch site, the launch platform 1 can be reliably fixed to the ground by cooperating with or connecting to the floor interface assemblies 1-3 on both sides through floor bolts, ensuring the stability during the launch process.

[0141] In the embodiment of the present application, the launch platform 1 is fixed on the ground, and the vehicle-mounted platform of the launch system is cancelled, and it is simplified to a ground launch platform. After the vehicle-mounted unit is no longer needed, the development cost is reduced and the function of the launch system is improved by integrating the functions of hydraulic and electrical equipment installation, azimuth adjustment, rotation locking and unlocking, ground support and gas flow guidance, thereby solving the difficulties of high launch cost and loss of target distance in the development stage of inclined launch of cruise targets and the like.

[0142] Alternatively, as Figure 3 As shown, in the embodiment of the present application, the launching platform 1 includes a cradle body 1-1, which is formed by welding a rectangular tube and a steel plate and serves as the main load-bearing structure.

[0143] Alternatively, as Figure 3 As shown, in the embodiment of the present application, the cradle body 1-1 is provided with a foot interface assembly 1-3 as an installation interface for equipment such as footings. Optionally, the foot interface assembly 1-3 is welded to a corresponding position on the cradle body 1-1.

[0144] Alternatively, as Figure 3 As shown, in the embodiment of the present application, a lifting lug 1-2 is provided on the cradle body 1-1. The lifting lug 1-2 serves as a lifting interface and can be connected to a hook of a truck crane or a traveling crane using a lifting strap to realize the lifting of the ground launch platform 1.

[0145] Alternatively, as Figure 3 As shown, in the embodiment of the present application, a tensioning block 1-14 is provided on the truss body 1-1, and the tensioning block 1-14 is used to complete the auxiliary tensioning of the ground launch platform 1. The lifting ring is screwed into the tensioning block 1-14, and then a hand winch is used to connect the lifting ring to the fixed pile reserved in the launch position and tighten it.

[0146] Alternatively, as Figure 3 As shown, in the embodiment of the present application, a leveling leg interface assembly 1-4 is provided on the truss body 1-1, and the leveling leg interface assembly 1-4 can realize the installation of the leveling leg 8, thereby completing the support and leveling of the ground launch platform 1.

[0147] Alternatively, as Figure 3As shown in the figure, in the embodiment of the present application, on the truss main body 1-1, there are an auxiliary slewing locking structure mounting assembly 1-5, a slewing locking seat mounting block 1-6, a deflector mounting seat 1-7, a slewing bearing mounting seat 1-8, a slewing drive mechanism mounting seat 1-9, a control box mounting block 1-10, a generator set mounting block 1-11, a hydraulic system mounting block 1-12, a carrying cabin mounting block 1-13, etc., which are respectively used as the mounting interfaces for equipment such as an auxiliary slewing locking structure 5, a slewing locking seat 4, a deflector 2, a slewing bearing 14, a slewing drive mechanism 10, a control box 11, a generator set 12, a hydraulic system 13, a carrying cabin 3, etc. Optionally, the auxiliary slewing locking structure mounting assembly 1-5, the slewing locking seat mounting block 1-6, the deflector mounting seat 1-7, the slewing bearing mounting seat 1-8, the slewing drive mechanism mounting seat 1-9, the control box mounting block 1-10, the generator set mounting block 1-11, the hydraulic system mounting block 1-12, the carrying cabin mounting block 1-13, etc. are all obtained by machining after welding steel plates to the truss main body 1-1, so as to serve as the mounting reference for each component or mechanism.

[0148] Optionally, as Figure 3 shown, in the embodiment of the present application, on the truss main body 1-1, there is a tarpaulin fixing block 1-15, which can be used to tighten the tarpaulin during transportation. Optionally, the tarpaulin fixing block 1-15 is of a "T" shape.

[0149] Optionally, as Figure 2 and Figure 8 shown, in the embodiment of the present application, the gas flow guiding structure includes a deflector 2, the deflector 2 is arranged on a partial outer peripheral side of the slewing mechanism, and the top surface of the deflector 2 is an inclined surface that slopes downward in a direction away from the slewing mechanism, and the gas flow is guided through the inclined surface.

[0150] In the embodiment of the present application, when the target is erected to a large elevation angle, the tail nozzle is directly facing the surface of the deflector 2, and the gas flow can be guided by the inclined surface of the deflector 2 to effectively control the jet attitude of the gas.

[0151] Optionally, as Figure 2 and Figure 8 shown, in the embodiment of the present application, the deflector 2 is formed by welding steel plates and is installed at the rear side of the ground launch platform 1 (i.e., the tail, that is, on one side in the second direction, and the deflector 2 and the carrying cabin 3 are distributed along the second direction). The deflector 2 at the tail plays a role in guiding the gas flow at a large elevation angle.

[0152] Optionally, as Figure 8As shown, in the embodiment of the present application, the deflector 2 includes a front baffle 2-1, a sealing plate 2-2, a bottom mounting plate 2-3, a first reinforcing rib 2-4 and a second reinforcing rib 2-5. The bottom mounting plate 2-3 is connected to the launch platform 1. The first reinforcing rib 2-4 and the second reinforcing rib 2-5 can improve the structural strength and impact resistance of the top surface of the deflector 2 for discharging the gas flow.

[0153] Alternatively, as Figure 2 and Figure 9 As shown, in this embodiment of the present application, the gas flow guide structure includes a gas flow baffle 6, which includes a main body bent plate 6-1 and side sealing plates 6-2. The main body bent plate 6-1 is connected to the launch platform 1, and the side sealing plates 6-2 are connected to the main body bent plate 6-1 and enclose a receiving chamber for accommodating the rotary drive mechanism 10 to prevent the gas flow from blowing into the rotary drive mechanism 10. The gas flow baffle 6 provides shielding and protection for the rotary drive mechanism 10. The side sealing plates 6-2 prevent the gas flow from blowing into the rotary drive mechanism 10 from the sides.

[0154] Alternatively, as Figure 9 As shown, in this embodiment of the present application, the main bending plate 6-1 includes a top sealing plate, a middle plate, and a bottom plate, which are sequentially connected to form a bent plate structure with a "Z" cross-section. The side sealing plates 6-2 are respectively connected to the top sealing plate and the middle plate to form an accommodating cavity. The rotary drive mechanism 10 is located within the accommodating cavity. The side sealing plates 6-2, the top sealing plate, and the middle plate respectively protect the rotary drive mechanism 10 from the side and top, preventing it from being blown by the gas flow.

[0155] Alternatively, as Figure 9 As shown, in this embodiment of the present application, the gas flow baffle 6 is connected to the ground launch platform 1 using light holes and bolts in the bottom plate of the main body bent plate 6-1. The gas flow baffle 6 also includes main body reinforcement ribs 6-3, which are connected to the middle plate and the bottom plate respectively and are located on the side of the middle plate facing away from the accommodating cavity. The main body reinforcement ribs 6-3 provide reinforcement and improve the structural strength of the gas flow baffle 6.

[0156] Alternatively, as Figure 2 and Figure 10 As shown, in the embodiment of the present application, the rotary locking mechanism includes a rotary locking seat 4 connected to the launch platform 1; the rotary locking seat 4 is provided with a plurality of locking holes, and the plurality of locking holes are arranged in sequence and spaced apart around the rotation axis of the rotary mechanism, and the rotary table 15 of the rotary mechanism is provided with an assembly hole, and the rotary locking seat 4 and the rotary table 15 are fixedly connected by fasteners passing through the locking holes and the assembly holes.

[0157] In the embodiment of the present application, the rotary locking seat 4 is installed on the launch platform 1. After the rotary table 15 is rotated to the target azimuth angle, a fastener can be selectively used to cooperate or connect with one of a plurality of locking holes and an assembly hole, so as to fixedly connect the rotary table 15 and the rotary locking seat 4 together, realizing reliable rotary locking of the rotary table 15 and the rotary locking seat 4, thereby locking the rotary table 15 at the target azimuth angle.

[0158] Optionally, as Figure 10 shown, in the embodiment of the present application, the rotary locking seat 4 includes an upper mounting plate 4-1, a lower fixing plate 4-2, an intermediate support plate 4-3 and side rib plates 4-4. The rotary locking seat 4 can be connected to the ground launch platform 1 by using the lower fixing plate 4-2 to achieve reliable overall fixation. The locking holes are arranged on the upper mounting plate 4-1. The intermediate support plate 4-3 supports the upper mounting plate 4-1, and the side rib plates 4-4 are respectively connected to the upper mounting plate 4-1, the lower fixing plate 4-2 and the intermediate support plate 4-3, improving the structural strength.

[0159] Optionally, as Figure 10 shown, in the embodiment of the present application, the locking holes are threaded holes and the assembly holes are light holes. A threaded hole is opened on the upper mounting plate 4-1 at every fixed angle, and a plurality of threaded holes are arranged at intervals in sequence around the rotation axis of the rotary table 15. The plurality of threaded holes are distributed on an arc centered on the rotation center of the rotary table 15. A bolt is passed through the corresponding light hole on the rotary table 15 and threadedly connected to the threaded hole to achieve reliable rotary locking of the rotary table 15 and the rotary locking seat 4.

[0160] Optionally, as Figure 2 shown, in the embodiment of the present application, a plurality of rotary locking seats 4 are provided, and the plurality of rotary locking seats 4 are arranged at intervals along the circumferential direction of the rotary table 15. The rotary table 15 can be locked by a plurality of rotary locking seats 4 at the same time to achieve a more reliable rotary locking effect.

[0161] Optionally, as Figure 2 shown, in the embodiment of the present application, the number of the rotary locking seats 4 is two, and the two rotary locking seats 4 are respectively located on both sides of the rotary table 15 along the first direction.

[0162] Optionally, as Figure 1 shown, in the embodiment of the present application, a plurality of assembly holes arranged at intervals in sequence around the rotation axis of the rotary table 15 are provided on the rotary table 15. A plurality of locking holes correspond one by one to several of the plurality of assembly holes.

[0163] Optionally, as Figure 1 shown, in the embodiment of the present application, a circle of assembly holes arranged at intervals in sequence around the rotation axis of the rotary table 15 are provided on the rotary table 15. The plurality of assembly holes are distributed on an arc centered on the rotation center of the rotary table 15.

[0164] Optionally, as shown in Figure 2 and Figure 11 In the embodiment of the present application, the slewing locking mechanism further includes an auxiliary slewing locking structure 5. The auxiliary slewing locking structure 5 includes a main body mounting seat 5-1 installed on the launch platform 1, an adjusting member 5-2 movably arranged on the main body mounting seat 5-1, a support seat 5-3 installed at one end of the adjusting member 5-2, and a driving member 5-5 installed at the other end of the adjusting member 5-2. By driving the adjusting member 5-2 to move through the driving member 5-5, the support seat 5-3 is connected to the adjusting member 5-2 by a ball joint, and the support seat 5-3 is used to abut against the slewing table 15.

[0165] In the embodiment of the present application, the auxiliary slewing locking structure 5 is connected to the ground launch platform 1 by the light holes on both sides of the main body mounting seat 5-1. The adjusting member 5-2 is movably arranged relative to the main body mounting seat 5-1. By driving the adjusting member 5-2 to move through the driving member 5-5, the extension and retraction of the adjusting member 5-2 relative to the main body mounting seat 5-1 are realized. One end of the adjusting member 5-2 is connected to the support seat 5-3 by a ball joint, so that the support seat 5-3 can rotate with multiple degrees of freedom relative to the end of the adjusting member 5-2. The support seat 5-3 can abut against the slewing table 15. The ball joint connection method can adapt to the adjustment of the azimuth angle of the slewing table 15. By extending the adjusting member 5-2 and the support seat 5-3 abutting against the side surface of the slewing table 15, the reliable auxiliary locking of the slewing table 15 and the above equipment is realized, and the slewing table 15 is further locked at the target azimuth angle.

[0166] Optionally, as shown in Figure 11 In the embodiment of the present application, the adjusting member 5-2 is a screw rod, and the screw rod is in threaded cooperation with the main body mounting seat 5-1. By rotating the screw rod, the extension and retraction of the screw rod relative to the main body mounting seat 5-1 are realized. One end of the screw rod is connected to the support seat 5-3 by a ball joint connection method, so that the support seat 5-3 can adapt to the adjustment of the azimuth angle of the slewing table 15 and abut against the side surface of the slewing table 15, thereby realizing the reliable auxiliary locking of the slewing table 15 and the above equipment.

[0167] Optionally, as shown in Figure 11 In the embodiment of the present application, the ball head at the end of the screw rod is connected to the support seat 5-3 through a ball head sealing plate 5-4.

[0168] Optionally, as shown in Figure 11 In the embodiment of the present application, the driving member 5-5 includes a handwheel, and the handwheel is fixedly connected to the end of the screw rod away from the support seat 5-3. Optionally, the handwheel is detachably connected to the screw rod. A limit top plate 5-6 and a locking nut 5-7 are arranged on the side of the handwheel away from the support seat 5-3. The limit top plate 5-6 is used to prevent the handwheel from disengaging from the screw rod, and the locking nut 5-7 is used to fix the handwheel on the screw rod.

[0169] The flight structure launching device provided by the embodiment of the present application is composed of a launching platform 1, a deflector 2, a carrying cabin 3, a rotary locking seat 4, an auxiliary rotary locking structure 5, a gas flow baffle 6, a marching locking mechanism 7, leveling legs 8, a toolbox 9, a rotary driving mechanism 10, etc., and is mainly used to provide an installation carrier for the rotary table 15, erection frame 16 and launch box 18 of the target launching system.

[0170] Optionally, as Figure 2 shown, in the embodiment of the present application, the leveling legs 8 can be hydraulic leveling legs or other retractable structures such as jacks. The toolbox 9 is used to store operating tools (such as wrenches), spare parts, consumables, etc.

[0171] The working process of the flight structure launching device provided by the embodiment of the present application is as follows:

[0172] (1) Place the ground launching platform 1 at the predetermined launching position, and use anchor bolts to firmly fix the ground launching platform 1 to the ground;

[0173] (2) Unlock the loose joint bolts of the marching locking mechanism 7 and turn them to the unlocked position parallel to the upper surface of the carrying cabin 3;

[0174] (3) Unlock the rotary table 15 from the rotary locking mechanism (remove the bolts connecting the rotary table 15 and the rotary locking seat 4, so that the support seat 5-3 of the auxiliary rotary locking structure 5 no longer presses against the side of the rotary table 15), and make the rotary table 15 in a free state;

[0175] (4) Use the leveling legs 8 to support the ground launching platform 1 and adjust the transverse tilt angle and longitudinal tilt angle;

[0176] (5) Rotate the rotary table 15 around the slewing bearing 14 by operating the screw jack of the hand-cranked rotary driving mechanism 10 to reach the azimuth angle required for launching (i.e., the target azimuth angle);

[0177] (6) After rotating to the position, lock the rotary table 15 and the rotary locking mechanism reliably (tighten the bolts connecting the rotary table 15 and the rotary locking seat 4, and rotate the handwheel of the auxiliary rotary locking structure 5 to make the support seat 5-3 press against the side of the rotary table 15), and realize the locking of the rotary mechanism;

[0178] (7) Open the cabin door of the carrying cabin 3, and operate the internal equipment such as the control box 11, generator set 12, and hydraulic system 13 as needed to realize operations such as power supply and erection;

[0179] (8) After completing the pre-launch preparation work, cut off the power of each device, close the cabin door, and evacuate the personnel.

[0180] The flight structure launch device provided by the embodiment of the present application can be applied to the ground launch of multi-functional cruise targets, and further can be applied to the ground launch of hypersonic targets.

[0181] Based on the same inventive concept, the embodiment of the present application provides an aircraft launch system, which includes: an aircraft and the flight structure launch device as described above. The aircraft is placed in the launch box 18 of the slewing mechanism of the flight structure launch device as the flight structure to be launched.

[0182] It should be noted that since the aircraft launch system in the embodiment of the present application includes the flight structure launch device in the embodiment of the present application, therefore, the aircraft launch system in the embodiment of the present application also has the above beneficial effects of the flight structure launch device in the embodiment of the present application, which will not be elaborated here.

[0183] Optionally, in the embodiment of the present application, the aircraft includes but is not limited to cruise targets, aircraft, spacecraft, rockets, etc.

[0184] Applying the embodiment of the present application can at least achieve the following beneficial effects:

[0185] In the embodiment of the present application, the slewing mechanism bears the flight structure to be launched (such as an aircraft). The slewing mechanism is rotatably arranged relative to the launch platform. By rotating the slewing mechanism, the flight structure to be launched can be driven to rotate relative to the launch platform, so as to adjust the azimuth angle of the flight structure to be launched. The slewing drive mechanism is connected to the slewing mechanism. By the slewing drive mechanism, the slewing mechanism can be driven to rotate, so as to drive the flight structure to be launched to rotate, and the purpose of adjusting the azimuth angle of the flight structure to be launched is achieved. The slewing locking mechanism can lock the slewing mechanism on the launch platform, so as to fix the flight structure to be launched at the target azimuth angle. A gas flow guiding structure is arranged on at least part of the outer periphery of the slewing mechanism, so that the gas flow generated by the flight structure to be launched can be discharged through the gas flow guiding structure. The electrical equipment provides at least one of the functions of control, drive and power supply to the slewing mechanism at least.

[0186] In the embodiment of the present application, the slewing drive mechanism, the slewing locking mechanism, the gas flow guiding structure and the electrical equipment are integrated on the launch platform, adopting a highly integrated design. The functions of installing hydraulic and electrical equipment, adjusting the azimuth angle, slewing locking and unlocking, and gas flow guiding are integrated into the launch platform, which not only reduces the research and development cost, but also improves the functions of the launch system. And in the embodiment of the present application, by setting the slewing mechanism, the azimuth angle of the flight structure to be launched is adjustable. Therefore, the flight structure launch device provided by the embodiment of the present application solves the difficulties in aspects such as high launch cost in the research and development stage of inclined launch of cruise targets and loss of target supply distance in vertical launch.

[0187] Those skilled in the art of the present application can understand that the various operations, methods, steps, measures, and solutions in the processes discussed in the present application can be alternated, changed, combined, or deleted. Further, other steps, measures, and solutions in the various operations, methods, and processes discussed in the present application can also be alternated, changed, rearranged, decomposed, combined, or deleted. Further, the steps, measures, and solutions in the relevant technologies that are the same as those disclosed in the various operations, methods, and processes in the present application can also be alternated, changed, rearranged, decomposed, combined, or deleted.

[0188] In the description of the present application, the directions or positional relationships indicated by the words "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are the exemplary directions or positional relationships based on the drawings, which are for the convenience of describing or simplifying the embodiments of the present application, rather than indicating or implying that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to the present application.

[0189] The terms "first" and "second" are only used for descriptive purposes, and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present application, unless otherwise specified, the meaning of "a plurality" is two or more.

[0190] In the description of the present application, it should be noted that unless otherwise clearly specified and defined, the terms "installed", "connected", and "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be directly connected, or indirectly connected through an intermediate medium, and it may be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0191] In the description of this specification, the specific features, structures, materials, or characteristics may be combined in a suitable manner in any one or more embodiments or examples.

[0192] The above are only some embodiments of the present application. It should be noted that for those of ordinary skill in the art of the present application, without departing from the technical concept of the solution of the present application, other similar implementation means based on the technical idea of the present application also belong to the protection scope of the embodiments of the present application.

Claims

1. A flight structure launching device, characterized in that, include: launch platform; a slewing mechanism, rotatably disposed on the launch platform, the slewing mechanism being used to carry the flying structure to be launched; a rotary drive mechanism connected to the rotary mechanism, the rotary drive mechanism being used to drive the rotary mechanism to rotate so as to adjust the azimuth angle of the flying structure to be launched; A rotation locking mechanism, used to lock the rotation mechanism on the launch platform; a gas flow guiding structure, located at least partially around the outer periphery of the rotary mechanism, the gas flow guiding structure being used to guide the gas flow generated by the flight structure to be launched; an electrical device connected to at least the slewing mechanism, the electrical device having at least one function of control, drive and power supply; The rotary drive mechanism, the rotary locking mechanism, the gas flow guide structure and the electrical equipment are integrated and arranged on the launch platform; The rotary drive mechanism comprises: A driving component, mounted on the launching platform; a first transmission component connected to the driving component, the first transmission component having an output portion movably arranged along a first direction; under the drive of the driving component, the output portion moves relative to the launching platform; The second transmission component is connected to the output part and the rotating mechanism respectively. The second transmission component is rotatably arranged relative to the output part. The output part moves, thereby driving the second transmission component and the rotating mechanism to rotate relative to the launching platform in turn.

2. The flight structure launching device according to claim 1, characterized in that Include at least one of the following: The first transmission component includes a lead screw extending along the first direction, a drive nut threadedly engaged with the lead screw, and a guide structure connected to the drive nut, wherein the lead screw is rotatably mounted on the launch platform, the drive component drives the lead screw to rotate, the drive nut serves as the output part, and the guide structure is used to guide the movement of the drive nut along the first direction; The second transmission component includes a connecting rod structure and a transfer seat, one end of the connecting rod structure is pivotally connected to the output part, and the other end is pivotally connected to the transfer seat, and the transfer seat is fixedly connected to the rotary mechanism; The driving component includes a hand wheel.

3. The flight structure launching device according to claim 2, characterized in that, Include at least one of the following: The rotary drive mechanism further includes a first mounting seat and a second mounting seat fixedly mounted on the launch platform, and two ends of the lead screw are rotatably connected to the first mounting seat and the second mounting seat respectively; The first transmission component further includes a worm wheel and a worm, the driving component is connected to the worm to drive the worm to rotate, the worm is engaged with the worm wheel to drive the worm wheel to rotate, and the worm wheel is sleeved on the lead screw to drive the lead screw to rotate; The guide structure includes a slider fixedly connected to the drive nut and a guide rail provided on the launching platform, the guide rail extending along the first direction, and the slider slidingly engaging with the guide rail; The rotary drive mechanism further includes a sliding seat fixedly connected to the drive nut, and the sliding seat is provided with a plurality of the guide structures sequentially arranged in the second direction.

4. The flying structure launching device according to any one of claims 1 to 3, characterized in that: It also includes a carrying cabin, which is detachably mounted on the launching platform; The electrical equipment includes a control box, a generator set and a hydraulic system, the control box is connected to at least one of the generator set, the hydraulic system and the slewing mechanism, and the generator set and the hydraulic system are respectively connected to the slewing mechanism; The control box, the generator set and the hydraulic system are integrated in the load compartment.

5. The flight structure launching device according to claim 4, characterized in that, It also includes a march locking mechanism, which includes a lateral limit seat and a locking member rotatably arranged on the lateral limit seat; The lateral limit seat is installed on the carrying cabin, and a limit groove is provided on the lateral limit seat, and the limit groove is used to cooperate with the erection frame of the slewing mechanism to limit the rotation of the erection frame in the horizontal plane; The locking member has a locking position and an unlocking position relative to the lateral limit seat. When the locking member is in the locking position, the locking member is locked in the groove of the erecting frame by a fastener to limit the rotation of the erecting frame in a vertical plane.

6. The flying structure launching device according to claim 5, characterized in that: Include at least one of the following: The opening of the limiting groove is arranged upward, and the sidewalls of the limiting groove are inclined outward in the direction in which the bottom of the limiting groove points to the opening; The locking member includes a bolt, which is rotatably connected to the lateral limit seat via a pin, and the fastener includes a nut for threaded engagement with the bolt; A plurality of locking members are provided on the lateral limiting seat, and an arrangement direction of the plurality of locking members is parallel to an extension direction of the side wall of the limiting groove.

7. The flying structure launching device according to any one of claims 1 to 3, characterized in that: Include at least one of the following: The launch platform is provided with a ground anchor interface assembly, and the launch platform is fixed on the ground of the launch position by means of anchor bolts cooperating with or connecting with the ground anchor interface assembly; The gas flow diversion structure includes a diverter, which is arranged on a portion of the outer periphery of the rotary mechanism. The top surface of the diverter is an inclined surface that is inclined downward in a direction away from the rotary mechanism, and the gas flow is diverted through the inclined surface. The gas flow guide structure includes a gas flow baffle, which includes a main body bending plate and a side sealing plate. The main body bending plate is connected to the launch platform, and the side sealing plate is connected to the main body bending plate and forms an accommodating cavity for accommodating the rotary drive mechanism to prevent the gas flow from blowing onto the rotary drive mechanism.

8. The flying structure launching device according to any one of claims 1 to 3, characterized in that: The rotation locking mechanism includes a rotation locking seat connected to the launch platform; The rotary locking seat is provided with a plurality of locking holes, and the plurality of locking holes are arranged in sequence and spaced apart around the rotation axis of the rotary mechanism. The rotary table of the rotary mechanism is provided with an assembly hole, and the rotary locking seat and the rotary table are fixedly connected by fasteners passing through the locking holes and the assembly holes.

9. The flight structure launching device according to claim 8, characterized in that, Include at least one of the following: There are multiple rotation locking seats, and the multiple rotation locking seats are arranged at intervals along the circumference of the turntable; The turntable is provided with a plurality of assembly holes which are sequentially spaced around the rotation axis of the turntable; The swing locking mechanism further includes an auxiliary swing locking structure, which includes a main body mounting seat installed on the launch platform, an adjusting member movably arranged on the main body mounting seat, a support seat installed at one end of the adjusting member, and a driving member installed at the other end of the adjusting member. The adjusting member is driven to move by the driving member. The support seat is connected to the adjusting member by a ball joint, and the support seat is used to abut against the turntable.

10. An aircraft launch system, characterized in that: Comprising: The flight structure launching device according to any one of claims 1 to 9; An aircraft, which is a flight structure to be launched and is placed in the launch box of the swing mechanism of the flight structure launching device.

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