Flight structure launching device and aircraft launching system

Abstract

The invention provides a flight structure launching device and an aircraft launching system. The flight structure launching device comprises a launching platform; the rotating mechanism is rotatably arranged on the launching platform and is used for bearing a to-be-launched flight structure; the rotation driving mechanism is connected with the rotation mechanism and used for driving the rotation mechanism to rotate so as to adjust the azimuth angle of the flight structure to be launched; the rotary locking mechanism is used for locking the rotary mechanism on the launching platform; the fuel gas flow discharging and guiding structure is located on at least part of the periphery of the rotating mechanism and used for discharging and guiding fuel gas flow generated by the to-be-launched flight structure; the electrical equipment is at least connected with the slewing mechanism, and the electrical equipment has at least one function of control, driving and power supply; the rotation driving mechanism, the rotation locking mechanism, the fuel gas flow discharging and guiding structure and the electrical equipment are integrally arranged on the launching platform. According to the invention, the development cost is reduced, and the functions of the transmitting system are improved.

Description

Technical Field

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

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

[0003] For vertical thermal launch, the launch system only needs to develop a launch platform, hoist the target and flip it to a vertical state, then drop it above the launch platform, and take off in a direction perpendicular to the launch platform after the engine is ignited; however, this method will be affected by the trajectory and reduce its target distance.

[0004] The box-type rail (or box-type adapter) thermal launch is an inclined thermal launch. For the inclined thermal launch of this type of target, a motor vehicle-mounted launch is often used. The Class II chassis is used as a mobile platform, and a launch box or launch rack is installed on it. Through the multiple sets of sliders (or adapters) reserved on the target and the launch box (or launch rack) rails, the target is supported and guided before leaving the box (rack). However, this method requires the use of a Class II chassis as a launch platform, and various measurement, launch control and power supply equipment are integrated into the Class II chassis. At the same time, considering that the take-off mass of the cruise target is getting larger and larger, the adjustment of the azimuth and pitch angles are all done by electric adjustment. This vehicle-mounted launch method will result in higher costs in the development stage. Summary of the invention

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

[0006] In a first aspect, an embodiment of the present application provides a flying structure launching device, comprising: Launch platform; A slewing mechanism is rotatably disposed on the launching platform, and is used to carry the flying structure to be launched; A slewing drive mechanism connected to the slewing mechanism, the slewing drive mechanism is used to drive the slewing mechanism to rotate so as to adjust the azimuth angle of the flying structure to be launched; A slewing locking mechanism, used to lock the slewing mechanism on the launching platform; A gas flow guiding structure is located at least partially around the circumference of the rotary mechanism, and is used to guide the gas flow generated by the flight structure to be launched; An electrical device, connected at least to the slewing mechanism, having at least one of the functions 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 on the launching platform.

[0007] Optionally, the rotary drive mechanism comprises: A drive unit, mounted on the launch platform; A first transmission component is connected to the driving component, and the first transmission component has 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 rotary mechanism respectively, and the second transmission component is rotatably arranged relative to the output part; the output part moves, and in turn drives the second transmission component and the rotary mechanism to rotate relative to the launching platform.

[0008] Optionally, at least one of the following is included: The first transmission component includes a lead screw extending in a first direction, a drive nut threadedly matched with the lead screw, and a guide structure connected to the drive nut, the lead screw is rotatably mounted on the launching platform, the drive component drives the lead screw to rotate, the drive nut serves as an output part, and the guide structure is used to guide the movement of the drive nut in 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.

[0009] Optionally, at least one of the following is included: The rotary drive mechanism also 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 also includes a worm wheel and a worm, the driving component is connected to the worm to drive the worm to rotate, the worm is meshed with the turbine to drive the turbine to rotate, and the turbine is sleeved on the lead screw to drive the lead screw to rotate; The guide structure includes a slider fixedly connected to the driving nut and a guide rail arranged on the launching platform, the guide rail extends along a first direction, and the slider is slidably matched with the guide rail; The rotary drive mechanism also includes a sliding seat fixedly connected to the driving nut, and the sliding seat is provided with a plurality of guide structures arranged in sequence in the second direction.

[0010] Optionally, the flying structure launching device further comprises 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, generator set and hydraulic system are integrated in the load compartment.

[0011] Optionally, the flight structure launching device further comprises a march locking mechanism, the march locking mechanism comprising a lateral limit seat and a locking member rotatably arranged on the lateral limit seat; The lateral limit seat is installed on the load-bearing 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 limiting seat. When the locking member is in the locking position, the locking member is locked in the groove of the erecting frame by the fastener to limit the rotation of the erecting frame in the vertical plane.

[0012] Optionally, at least one of the following is included: The opening of the limiting groove is arranged upward, and the side wall of the limiting groove is 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 through a pin, and the fastener includes a nut for matching with the bolt thread; A plurality of locking members are arranged on the lateral limiting seat, and the arrangement direction of the plurality of locking members is parallel to the extension direction of the side wall of the limiting groove.

[0013] Optionally, at least one of the following is included: 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 the engagement or connection of the ground anchor bolts with the ground anchor interface assembly; The gas flow guiding structure includes a guide, which is arranged on a part of the outer periphery of the rotary mechanism, and the top surface of the guide is an inclined surface inclined downward in a direction away from the rotary mechanism, and the gas flow is guided by 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 launching platform, and the side sealing plate is connected to the main body bending plate to form an accommodating cavity for accommodating the rotary drive mechanism to prevent the gas flow from blowing onto the rotary drive mechanism.

[0014] Optionally, the slewing locking mechanism includes a slewing locking seat connected to the launching platform; The rotary locking seat is provided with a plurality of locking holes, which are arranged in sequence and at intervals around the rotation axis of the rotary mechanism. The rotary table of the rotary mechanism is provided with an assembly hole. The rotary locking seat and the rotary table are fixedly connected by fasteners passing through the locking holes and the assembly holes.

[0015] Optionally, at least one of the following is included: A plurality of rotary locking seats are provided, and the plurality of rotary locking seats are arranged at intervals along the circumference of the rotary table; The turntable is provided with a plurality of assembly holes which are arranged in sequence and at intervals around the rotation axis of the turntable; The rotary locking mechanism also includes an auxiliary rotary locking structure, which includes a main mounting seat installed on the launching platform, an adjusting member movably arranged on the main mounting seat, a supporting 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 supporting seat is connected to the ball head of the adjusting member, and the supporting seat is used to abut against the turntable.

[0016] In a second aspect, an embodiment of the present application provides an aircraft launch system, including: A flying structure launching device as described above; The aircraft, as a flying structure to be launched, is placed in a launching box of a rotating mechanism of a flying structure launching device.

[0017] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include: In an embodiment of the present application, a flight structure to be launched (such as an aircraft) is carried by a slewing mechanism, and the slewing mechanism is rotatably arranged relative to a launch platform. By rotating the slewing mechanism, the flight structure to be launched can be driven to rotate relative to the launch platform, thereby adjusting the azimuth of the flight structure to be launched. A slewing drive mechanism is connected to the slewing mechanism, and the slewing drive mechanism can drive the slewing mechanism to rotate, thereby driving the flight structure to be launched to rotate, and achieving the purpose of adjusting the azimuth of the flight structure to be launched. The slewing mechanism can be locked on the launch platform by a slewing locking mechanism, thereby fixing the flight structure to be launched at the target azimuth. A gas flow guide structure is arranged on at least part of the periphery of the slewing mechanism, so that the gas flow generated by the flight structure to be launched can be guided through the gas flow guide structure. The electrical equipment provides at least one function of control, drive and power supply to the slewing mechanism.

[0018] In the embodiment of the present application, the rotary drive mechanism, the rotary locking mechanism, the gas flow guide structure and the electrical equipment are integrated on the launch platform, and a highly integrated design is adopted to integrate the functions of hydraulic and electrical equipment installation, azimuth adjustment, rotary locking and unlocking, and gas flow guide into the launch platform, which not only reduces the development cost, but also improves the function of the launch system. In addition, in the embodiment of the present application, the azimuth angle of the flying structure to be launched is adjustable by setting a rotary mechanism. Therefore, the flying structure launch device provided in the embodiment of the present application solves the difficulties of high launch cost and loss of target distance in vertical launch in the development stage of inclined launch of cruise targets.

[0019] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which: Figure 1 A schematic structural diagram of a flying structure launching device provided in an embodiment of the present application; Figure 2 A partial structural diagram of a flying structure launching device provided in an embodiment of the present application (the rotating mechanism is not shown); Figure 3 A schematic diagram of the structure of a launch platform of a flying structure launch device provided in an embodiment of the present application; Figure 4 A schematic diagram of the structure of a rotary drive mechanism of a flying structure launching device provided in an embodiment of the present application; Figure 5 A schematic diagram of the structure of an electrical device of a flying structure launching device provided in an embodiment of the present application; Figure 6 A schematic diagram of the structure of a carrier cabin of a flying structure launching device provided in an embodiment of the present application; Figure 7 A schematic structural diagram of a march locking mechanism of a flying structure launching device provided in an embodiment of the present application; Figure 8 A schematic structural diagram of a deflector for a flying structure launching device provided in an embodiment of the present application; Fig. 9 A schematic diagram of the structure of a gas flow baffle of a flying structure launching device provided in an embodiment of the present application; Fig.10 A schematic diagram of the structure of a rotary locking seat of a flying structure launching device provided in an embodiment of the present application; Fig.11 A schematic structural diagram of an auxiliary rotary locking structure of a flying structure launching device provided in an embodiment of the present application.

[0021] Reference numerals: 1. Launch platform; 1-1, quilting frame body; 1-2, lifting ear; 1-3, anchor interface assembly; 1-4, leveling leg interface assembly; 1-5, auxiliary slewing locking structure installation assembly; 1-6, slewing locking seat installation block; 1-7, deflector installation seat; 1-8, slewing bearing installation seat; 1-9, slewing drive mechanism installation seat; 1-10, control box installation block; 1-11, generator set installation block; 1-12, hydraulic system installation block; 1-13, load compartment installation block; 1-14, tensioning block; 1-15, tarpaulin fixing block; 118, wiring trough; 2. Deflector; 2-1, front baffle; 2-2, sealing plate; 2-3, bottom mounting plate; 2-4, first reinforcing rib; 2-5, second reinforcing rib; 3. Carrying cabin; 3-1, cabin body; 3-2, lifting seat; 3-3, march locking mechanism mounting seat; 3-4, mounting feet; 4. Rotary locking seat; 4-1, upper mounting plate; 4-2, lower fixing plate; 4-3, middle supporting plate; 4-4, side rib plate; 5. Auxiliary rotation locking structure; 5-1, main body mounting seat; 5-2, adjustment member; 5-3, support seat; 5-4, ball head sealing plate; 5-5, driving member; 5-6, limit top plate; 5-7, locking nut; 6. Gas flow baffle; 6-1, main body bending plate; 6-2, side sealing plate; 6-3, main body reinforcing rib; 7. March locking mechanism; 7-1, lateral limit seat; 7-2, pin shaft; 7-3, locking piece; 8. Level the outriggers; 9. Toolbox; 10. Rotary drive mechanism; 8-1, first mounting seat; 8-2, second mounting seat; 8-3, sliding seat; 8-4, lead screw; 8-5, transfer lug; 8-6, limit pin; 8-7, transfer seat; 8-8, slider; 8-9, guide rail; 8-10, connecting rod structure; 11. Control box; 12. Generator set; 13. Hydraulic system; 14. Slewing bearing; 15. Rotating table; 16. Erecting frame; 17. Hydraulic cylinder; 18. Launching box. DETAILED DESCRIPTION

[0022] The embodiments of the present application are described below in conjunction with the drawings in the present application. It should be understood that the implementation methods described below in conjunction with the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0023] Those skilled in the art will appreciate that, unless expressly stated, the "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of the present application refers to the presence of the features, integers, steps, operations and / or components, but does not exclude the implementation of other features, information, data, steps, operations, components and / or combinations thereof supported by the technical field. The term "and / or" used herein refers to at least one of the items defined by the term, for example, "A and / or B" may be implemented as "A", or as "B", or as "A and B".

[0024] In order to make the objectives, technical solutions and advantages of the present application clearer, the implementation methods of the present application will be further described in detail below with reference to the accompanying drawings.

[0025] In view of the problems that the vertical thermal launch method existing in the related art will be affected by the ballistics and reduce its target supply distance, the box-type guide rail (or box-type adapter) thermal launch often adopts a motor vehicle-mounted launch type, which requires the use of a Class II chassis as a launch platform, and various measurement, launch control and power supply equipment are integrated into the Class II chassis. In addition, this vehicle-mounted launch method will lead to high costs in the development stage. The present application provides a flying structure launch device and an aircraft launch system, which aim to solve at least one of the above technical problems in the related art.

[0026] The following is a detailed description of the technical solution of the present application and how the technical solution of the present application solves the above technical problems with specific embodiments. It should be noted that the following implementations can refer to, draw on or combine with each other, and the same terms, similar features and similar implementation steps in different implementations will not be described repeatedly.

[0027] The present application embodiment provides a flying structure launching device. The structural schematic diagram of the flying structure launching device is as follows: Figure 1 and Figure 2 As shown, it includes: a launching platform 1, a rotating mechanism, a rotating driving mechanism 10, a rotating locking mechanism, a gas flow guiding structure and electrical equipment.

[0028] The slewing mechanism is rotatably arranged on the launch platform 1, and the slewing mechanism is used to carry the flight structure to be launched; the slewing drive mechanism 10 is connected to the slewing mechanism, and the slewing drive mechanism 10 is used to drive the slewing mechanism to rotate so as 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 part of the periphery of the slewing mechanism, and 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, and the electrical equipment has at least one function 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 integrated and arranged on the launch platform 1.

[0029] In the embodiment of the present application, the flight structure to be launched (such as an aircraft) is carried by a slewing mechanism, and the slewing mechanism is rotatably arranged relative to the launch platform 1. By rotating the slewing mechanism, the flight structure to be launched can be driven to rotate relative to the launch platform 1, thereby adjusting the azimuth of the flight structure to be launched. The slewing drive mechanism 10 is connected to the slewing mechanism, and the slewing drive mechanism 10 can drive the slewing mechanism to rotate, thereby driving the flight structure to be launched to rotate, and achieving the purpose of adjusting the azimuth of the flight structure to be launched. The slewing mechanism can be locked on the launch platform 1 by the slewing locking mechanism, so that the flight structure to be launched is fixed at the target azimuth. A gas flow guide structure is arranged on at least part of the periphery of the slewing mechanism, so that the gas flow generated by the flight structure to be launched can be guided through the gas flow guide structure. The electrical equipment provides at least one function of control, drive and power supply to the slewing mechanism.

[0030] In the embodiment of the present application, the rotary drive mechanism 10, the rotary locking mechanism, the gas flow guide structure and the electrical equipment are integrated on the launch platform 1, and a highly integrated design is adopted to integrate the functions of hydraulic and electrical equipment installation, azimuth adjustment, rotary locking and unlocking, and gas flow guide into the launch platform, which not only reduces the development cost, but also improves the function of the launch system. In addition, in the embodiment of the present application, the azimuth angle of the flight structure to be launched is adjustable by setting a rotary mechanism. Therefore, the flight structure launch device provided in the embodiment of the present application solves the difficulties of high launch cost and loss of target distance in vertical launch in the development stage of inclined launch of cruise targets.

[0031] Alternatively, if Figure 2 and Figure 4 As shown, in the embodiment of the present application, the rotary drive mechanism 10 includes a driving component, a first transmission component and a second transmission component, the driving component is installed on the launching platform 1; the first transmission component is connected to the driving component, and the first transmission component has an output part movably arranged along a first direction; under the drive of the driving component, the output part moves relative to the launching 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; the output part moves, and in turn drives the second transmission component and the rotary mechanism to rotate relative to the launching platform 1.

[0032] In the embodiment of the present application, the driving component, the first transmission component, the second transmission component and the slewing mechanism are connected in sequence. The driving component can drive the output part of the first transmission component to move in the first direction relative to the launch platform 1, and the output part is rotatably connected to the second transmission component. The movement of the output part drives the second transmission component to rotate relative to the launch platform 1, so that the second transmission component can drive the slewing mechanism to rotate, thereby driving the flight structure to be launched to rotate, and realizing azimuth adjustment.

[0033] Alternatively, if Figure 4 As shown, in the embodiment of the present application, the first transmission component includes a lead screw 8-4 extending along the first direction, a drive nut threadedly matched with the lead screw 8-4, and a guide structure connected to the drive 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 drive nut serves as an output part, and the guide structure is used to guide the movement of the drive nut along the first direction.

[0034] In the embodiment of the present application, the lead screw 8-4 is rotatably arranged relative to the launch 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 matched with the drive nut, and a guide structure is provided to limit the movement direction of the drive nut, so that when the lead screw 8-4 rotates, the rotational movement of the lead screw 8-4 is converted into the movement of the drive nut, and the movement of the drive nut is guided by the guide structure to prevent the drive nut from rotating with the lead screw 8-4, thereby ensuring that the drive nut moves in the first direction.

[0035] Optionally, in an embodiment of the present application, the first transmission component also 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 turbine to drive the turbine to rotate, and the turbine is sleeved on the screw 8-4 to drive the screw 8-4 to rotate.

[0036] Optionally, in an embodiment of the present application, the first transmission component adopts a screw elevator.

[0037] Alternatively, if Figure 4 As shown, in the embodiment of the present application, the rotary drive mechanism 10 also includes a first mounting seat 8-1 and a second mounting seat 8-2 fixedly mounted on the launching platform 1, and 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.

[0038] Optionally, in the embodiment of the present application, the lead screw 8-4 is rotatably connected to the first mounting seat 8-1 and the second mounting seat 8-2 through bearings, respectively. The extension 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.

[0039] Alternatively, if Figure 4 As shown, in the embodiment of the present application, the guide structure includes a slider 8-8 fixedly connected to the drive nut and a guide rail 8-9 arranged on the launch platform 1, the guide rail 8-9 extends along the first direction, and the slider 8-8 and the guide rail 8-9 are slidably matched. The lead screw 8-4 rotates to apply a force to the drive nut, and the drive nut is connected to the slider 8-8, which limits the circumferential movement of the drive nut around the lead screw 8-4 and converts it into linear movement. The slider 8-8 and the guide rail 8-9 are slidably matched, and the drive nut and the slider 8-8 both move along the guide rail 8-9 to achieve a guiding effect.

[0040] Alternatively, if 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 driving nut, and a plurality of guide structures arranged sequentially in the second direction are provided on the sliding seat 8-3. The sliders 8-8 of the plurality of guide structures are all fixedly connected to the sliding seat 8-3. The sliders 8-8 of the plurality of guide structures are slidably matched with the guide rails 8-9 of the plurality of guide structures in a one-to-one correspondence.

[0041] 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.

[0042] Alternatively, if 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 lead screw 8-4, that is, the second direction is perpendicular to the first direction.

[0043] Alternatively, if Figure 4 As shown, in the embodiment of the present application, the driving component includes a hand wheel. By turning the hand wheel, the worm, the turbine and the lead screw 8-4 can be driven to rotate in sequence, thereby driving the drive nut to move, and then driving the second transmission component and the rotary mechanism to rotate, so as to adjust the azimuth of the flight structure to be launched. The operation is convenient. That is, the azimuth adjustment can be completed without power supply, which can avoid the power consumption and cost problems of traditional electric adjustment.

[0044] Of course, in other optional embodiments of the present application, the driving component can also include a motor or other electric driving component to achieve automatic drive and improve the degree of automation and mechanization according to actual needs and conditions.

[0045] Optionally, in the embodiment of the present application, the rotary drive mechanism 10 further includes a transmission, and the transmission is disposed between the driving component and the first transmission component.

[0046] Optionally, in an embodiment of the present application, the handwheel is connected to a driving gear of the transmission to drive the driving gear to rotate, the driving gear is meshed with a driven gear to drive the driven gear to rotate, and the driven gear is connected to a worm to drive the worm to rotate.

[0047] Optionally, in the embodiment of the present application, the transmission may be a speed reducer or a speed increaser.

[0048] Alternatively, if 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.

[0049] Alternatively, if Figure 4 As 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 connecting rod structure 8-10 is pivotally connected to the transfer lug 8-5 through a limit pin 8-6, and the other end of the transfer seat 8-7 and the connecting rod structure 8-10 are pivotally connected through another set of transfer lugs and a limit pin.

[0050] In the embodiment of the present application, the driving nut moves along the first direction, driving the connecting rod structure 8-10 to rotate or swing within a certain range. The adapter seat 8-7 is fixedly connected to the rotating mechanism. Driven by the connecting rod structure 8-10, the adapter seat 8-7 and the rotating mechanism rotate, thereby adjusting the azimuth angle of the flying structure to be launched.

[0051] Optionally, in the embodiment of the present application, the length of the connecting rod structure 8-10 is adjustable. By adjusting the length of the connecting rod structure 8-10, the adjustable range of the azimuth angle of the flight structure to be launched can be adjusted to improve adaptability and flexibility.

[0052] Specifically, Figure 4 As shown, in the embodiment of the present application, the first mounting seat 8-1 and the second mounting seat 8-2 of the rotary drive mechanism 10 are respectively connected to the launch platform 1, the sliding seat 8-3 is connected to the guide rail 8-9 installed on the launch platform 1 through the slider 8-8, the two ends of the lead screw 8-4 are rotatably connected to the first mounting seat 8-1 and the second mounting seat 8-2, the driving nut is connected to the sliding seat 8-3, and the sliding seat 8-3 is connected to the turntable 15 of the rotary mechanism through the transfer lug 8-5, the connecting rod structure 8-10, and the transfer seat 8-7, thereby driving the turntable 15 to rotate. The rotary drive mechanism 10 can make the driving nut move axially along the lead screw 8-4 through a hand-cranked screw lift, and drive the turntable 15 to rotate around the slewing bearing 14 through the combination of the transfer lug 8-5, the connecting rod structure 8-10, and the transfer seat 8-7.

[0053] The embodiment of the present application adopts a connecting rod mechanism formed by a combination of a spiral elevator and a sliding seat 8-3, an adapter lug 8-5, a connecting rod structure 8-10, and an adapter seat 8-7, which can be manually cranked to achieve a rotation function under a large load, that is, no power supply is required, and the azimuth adjustment of the launch system can be completed. The spiral elevator is used in combination with a connecting rod mechanism to achieve manual and portable adjustment of the azimuth, and a reliable locking of the turntable 15 is achieved through a variety of rotation locking mechanisms. The flight structure launch device of the embodiment of the present application has the characteristics of high integration, avoiding the power consumption and cost problems of traditional electric adjustment, simplifying the process and reducing costs.

[0054] Alternatively, if Figure 2 , Figure 5 and Figure 6As shown, in the embodiment of the present application, the flying structure launching device also includes a carrying cabin 3, which is detachably mounted 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, and 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 carrying cabin 3.

[0055] 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 launch platform 1 and integrated in the carrying cabin 3. The launch platform 1 can realize the installation of 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 carrying cabin 3 is mainly used for the protection of internal hydraulic and electrical equipment.

[0056] Alternatively, if Figure 1 and Figure 5 As shown, in the embodiment of the present application, the slewing mechanism includes a slewing platform 15 , a vertical frame 16 , a hydraulic cylinder 17 and a launching box 18 .

[0057] The turntable 15 is rotatably connected to the launching platform 1 through the slewing bearing 14. The erection frame 16 and the hydraulic cylinder 17 are both arranged on the turntable 15. The launching box 18 is arranged on the erection frame 16. The flying structure to be launched can be placed in the launching box 18. The rotation of the turntable 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 flying structure to be launched.

[0058] One end of the erection frame 16 is rotatably connected to the turntable 15, one end of the hydraulic cylinder 17 is rotatably connected to the turntable 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, and the hydraulic system 13 drives the hydraulic cylinder 17 to rotate in a vertical plane relative to the turntable 15, thereby driving the erection frame 16 and the launching box 18 to rotate in the vertical plane, and then adjusting the pitch angle of the flight structure to be launched.

[0059] Alternatively, if Figure 5 As shown, in the embodiment of the present application, the generator set 12 is used to supply power to the electrical equipment in the flight structure launch 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 opening or closing.

[0060] Alternatively, if Figure 3 As shown, in the embodiment of the present application, a wiring groove 118 is provided on the launch platform 1, and the wiring groove 118 is used to store and organize the wires between the generator set 12 and the electrical equipment, etc., so as to keep it neat and beautiful.

[0061] Alternatively, if Figure 6 As shown, in the embodiment of the present application, the load-bearing cabin 3 includes a load-bearing cabin body 3-1, a hoisting seat 3-2, a march locking mechanism mounting seat 3-3 and mounting legs 3-4. The load-bearing cabin body 3-1 is mainly used for the protection of internal hydraulic and electrical equipment. Considering the compatible design, the march locking mechanism mounting seat 3-3 is set to the top of the load-bearing cabin body 3-1, and the interior is strengthened to realize the installation of the march locking mechanism 7. The load-bearing cabin body 3-1 can be connected to the ground launch platform 1 using the mounting legs 3-4 around it, and the four hoisting seats 3-2 on the top can realize the hoisting of the load-bearing cabin body 3-1.

[0062] Alternatively, if Figure 2 and Figure 7 As shown, in the embodiment of the present application, the flying structure launching device also includes a marching locking mechanism 7, which includes a lateral limit seat 7-1 and a locking member 7-3 rotatably arranged on the lateral limit seat 7-1; the lateral limit seat 7-1 is installed on the carrying cabin 3, and a limit groove is provided on the lateral limit seat 7-1, and the limit 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 limit 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 by a fastener to limit the rotation of the erection frame 16 in the vertical plane.

[0063] In the embodiment of the present application, the load-bearing cabin 3 can utilize the installation interface of the march locking mechanism 7 while utilizing the march locking mechanism mounting seat 3 - 3 located at the top while completing the protection of the internal hydraulic and electrical equipment.

[0064] In the embodiment of the present application, the lateral limit seat 7-1 of the marching locking mechanism 7 is the main load-bearing structure, and the limit groove on the lateral limit seat 7-1 cooperates with the erecting frame 16 to limit the erecting frame 16 in the limit groove, thereby limiting the rotation of the erecting frame 16 in the horizontal plane, and realizing lateral fixation of the erecting frame 16, so that the erecting frame 16 cannot move in the horizontal plane; the locking member 7-3 is rotatably arranged relative to the lateral limit seat 7-1, and the locking member 7-3 can switch back and forth between the locking position and the unlocking position. When the locking member 7-3 is rotated to the corresponding groove on the erecting 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 erecting frame 16 by the fastener, thereby limiting the rotation of the erecting frame 16 in the vertical plane, thereby realizing the up and down fixation of the erecting frame 16, so that the erecting frame 16 cannot move in the vertical plane.

[0065] Alternatively, if Figure 7 As shown, in the embodiment of the present application, the opening of the limiting groove is arranged upward, and in the direction where the bottom of the limiting groove points to the opening, the side wall of the limiting groove is inclined outward.

[0066] In the embodiment of the present application, the side wall of the limiting groove is an outwardly inclined surface along the bottom of the limiting groove pointing to the direction of the opening, and the cross-sectional area of ​​the limiting groove in the horizontal plane gradually increases. The inclined surface inside the limiting groove cooperates with the wedge block of the erecting frame 16, on the one hand, the erecting frame 16 can be fixed in the lateral direction, and on the other hand, the inclined surface can also play a certain guiding role when the erecting frame 16 is lowered, so that the wedge block can enter the limiting groove more conveniently.

[0067] Alternatively, if Figure 7 As shown, in the embodiment of the present application, the locking member 7-3 includes a bolt, which is rotatably connected to the lateral limit seat 7-1 through a pin shaft 7-2, and the fastener includes a nut for threadedly cooperating with the bolt. By rotating the movable bolt into the groove corresponding to the erecting frame 16 and then tightening it with the nut, the erecting frame 16 is fixed up and down.

[0068] The embodiment of the present application realizes the march locking function of the erecting frame 16 through the design of the limit groove, the inclined surface and the movable bolt.

[0069] Alternatively, if Figure 7 As 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.

[0070] The locking effect can be improved by providing a plurality of locking members 7-3. The plurality of locking members 7-3 are sequentially distributed along the extension direction of the side wall of the limiting groove, which is convenient for arrangement and operation.

[0071] It should be noted that, in the embodiments of the present application, a plurality includes two and more than two.

[0072] Alternatively, if Figure 3 As shown, in the embodiment of the present application, a ground anchor interface assembly 1-3 is provided on the launch platform 1, and the launch platform 1 is fixed on the ground of the launch position by means of anchor bolts cooperating or connecting with the ground anchor interface assembly 1-3.

[0073] Optionally, in the embodiment of the present application, a plurality of ground anchor interface components 1-3 are provided on the launch platform 1. Ground anchor interface components 1-3 are provided on both sides of the launch platform 1 in the first direction.

[0074] In the embodiment of the present application, after the launch platform 1 falls to the launch site, the anchor bolts can be used to cooperate or connect with the anchor interface components 1-3 on both sides to reliably fix the launch platform 1 to the ground to ensure the stability of the launch process.

[0075] In the embodiment of the present application, the launch platform 1 is fixed on the ground, 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 functions such as 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 vertical launch during the development stage of inclined launch of cruise targets.

[0076] Alternatively, if Figure 3 As shown, in the embodiment of the present application, the launching platform 1 includes a lattice body 1-1, which is formed by welding a rectangular tube and a steel plate and is the main load-bearing structure.

[0077] Alternatively, if Figure 3 As shown, in the embodiment of the present application, a ground pin interface component 1-3 is provided on the lattice main body 1-1, which serves as an installation interface for equipment such as ground pins. Optionally, the ground pin interface component 1-3 is welded to a corresponding position on the lattice main body 1-1.

[0078] Alternatively, if Figure 3 As shown, in the embodiment of the present application, a lifting lug 1-2 is provided on the cradle body 1-1, and the lifting lug 1-2 serves as a lifting interface, and can be connected to a hook of a truck crane or a crane by a lifting belt to realize the lifting of the ground launch platform 1.

[0079] Alternatively, if 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 with the fixed pile reserved in the launch position and tighten it.

[0080] Alternatively, if 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 to complete the ground support and leveling of the ground launch platform 1.

[0081] Alternatively, if Figure 3As shown, in the embodiment of the present application, an auxiliary rotary locking structure mounting assembly 1-5, a rotary locking seat mounting block 1-6, a deflector mounting seat 1-7, a rotary bearing mounting seat 1-8, a rotary 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 load-bearing cabin mounting block 1-13, etc. are provided on the quilting frame body 1-1, which respectively serve as mounting interfaces for equipment such as the auxiliary rotary locking structure 5, the rotary locking seat 4, the deflector 2, the rotary bearing 14, the rotary drive mechanism 10, the control box 11, the generator set 12, the hydraulic system 13, and the load-bearing cabin 3. 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 load-bearing cabin mounting block 1-13, etc. are all obtained by welding steel plates to the lattice body 1-1 and then machining to serve as the installation reference for each component or mechanism.

[0082] Alternatively, if Figure 3 As shown, in the embodiment of the present application, a tarpaulin fixing block 1-15 is provided on the tarpaulin main body 1-1, which can be used to tighten the tarpaulin during transportation. Optionally, the tarpaulin fixing block 1-15 is a "T"-shaped structure.

[0083] Alternatively, if Figure 2 and Figure 8 As shown, in the embodiment of the present application, the gas flow diversion structure includes a diverter 2, which is arranged on a partial outer peripheral side of the rotating mechanism. The top surface of the diverter 2 is an inclined surface inclined downward in a direction away from the rotating mechanism, and the gas flow is diverted through the inclined surface.

[0084] In the embodiment of the present application, when the target is erected to a large elevation angle, the tail nozzle is directly opposite to the surface of the deflector 2, and the gas flow can be discharged using the inclined surface of the deflector 2, thereby effectively controlling the jet posture of the gas.

[0085] Alternatively, if Figure 2 and Figure 8 As shown, in the embodiment of the present application, the deflector 2 is made of welded steel plates and installed on the rear side of the ground launch platform 1 (i.e., the tail, that is, on the side of the second direction, the deflector 2 and the carrying cabin 3 are distributed along the second direction), and the deflector 2 at the tail plays a role in realizing the gas flow diversion at a large elevation angle.

[0086] Alternatively, if 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.

[0087] Alternatively, if Figure 2 and Fig. 9 As shown, in the embodiment of the present application, the gas flow guide structure includes a gas flow baffle 6, and the gas flow baffle 6 includes a main body bending plate 6-1 and a side sealing plate 6-2. The main body bending plate 6-1 is connected to the launch platform 1, and the side sealing plate 6-2 is connected to the main body bending plate 6-1 and encloses a receiving cavity for accommodating the rotary drive mechanism 10 to prevent the gas flow from blowing to the rotary drive mechanism 10. The gas flow baffle 6 plays a role of shielding and protecting the rotary drive mechanism 10. The side sealing plate 6-2 can prevent the gas flow from blowing to the rotary drive mechanism 10 from the side.

[0088] Alternatively, if Fig. 9 As shown, in the 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 connected in sequence to form a bending plate structure with a "Z"-shaped cross section. The side sealing plates 6-2 are respectively connected to the top sealing plate and the middle plate to form a receiving cavity, and the rotary drive mechanism 10 is located in the receiving cavity. The side sealing plates 6-2, the top sealing plate and the middle plate protect the rotary drive mechanism 10 from the side and the top respectively to prevent it from being blown by the gas flow.

[0089] Alternatively, if Fig. 9 As shown, in the embodiment of the present application, the gas flow baffle 6 is connected to the ground launch platform 1 by using the light holes and bolts on the bottom plate of the main body bending plate 6-1. The gas flow baffle 6 also includes a main body reinforcing rib 6-3, which is respectively connected to the middle plate and the bottom plate and is located on the side of the middle plate away from the accommodating cavity. The main body reinforcing rib 6-3 plays a reinforcing role and can improve the structural strength of the gas flow baffle 6.

[0090] Alternatively, if Figure 2 and Fig.10 As shown, in the embodiment of the present application, the slewing locking mechanism includes a slewing locking seat 4 connected to the launching platform 1; a plurality of locking holes are provided on the slewing locking seat 4, and the plurality of locking holes are arranged in sequence and spaced apart around the rotation axis of the slewing mechanism; an assembly hole is provided on the slewing table 15 of the slewing mechanism, and the slewing locking seat 4 and the slewing table 15 are fixedly connected by fasteners passing through the locking holes and the assembly holes.

[0091] In the embodiment of the present application, the swivel locking seat 4 is installed on the launching platform 1. When the turntable 15 is rotated to the target azimuth, the fasteners can be selectively matched or connected with one locking hole and an assembly hole among the multiple locking holes to fix the turntable 15 and the swivel locking seat 4 together, thereby achieving reliable swivel locking of the turntable 15 and the swivel locking seat 4, and locking the turntable 15 at the target azimuth.

[0092] Alternatively, if Fig.10 As shown, in the embodiment of the present application, the slewing locking seat 4 includes an upper mounting plate 4-1, a lower fixing plate 4-2, an intermediate support plate 4-3 and a side rib plate 4-4. The slewing locking seat 4 can be connected to the ground launch platform 1 using the lower fixing plate 4-2 to achieve reliable fixation of the whole. The locking hole is set on the upper mounting plate 4-1. The intermediate support plate 4-3 supports the upper mounting plate 4-1, and the side rib plate 4-4 is respectively connected to the upper mounting plate 4-1, the lower fixing plate 4-2, and the intermediate support plate 4-3, thereby improving the structural strength.

[0093] Alternatively, if Fig.10 As shown, in the embodiment of the present application, the locking hole is a threaded hole, and the assembly hole is a light hole. A threaded hole is provided on the upper mounting plate 4-1 at fixed angles, and the plurality of threaded holes are arranged in sequence around the rotation axis of the turntable 15, and the plurality of threaded holes are distributed on an arc line centered on the rotation center of the turntable 15. The corresponding light holes on the turntable 15 are threadedly connected with the threaded holes by bolts, so as to realize reliable rotation locking of the turntable 15 and the rotation locking seat 4.

[0094] Alternatively, if Figure 2 As 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 circumference of the rotary table 15. The rotary table 15 can be locked simultaneously by the plurality of rotary locking seats 4, so as to achieve a more reliable rotary locking effect.

[0095] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the number of the swivel locking seats 4 is two, and the two swivel locking seats 4 are respectively located on both sides of the swivel table 15 along the first direction.

[0096] Alternatively, if Figure 1 As shown, in the embodiment of the present application, a plurality of assembly holes are arranged in sequence and spaced around the rotation axis of the turntable 15 on the turntable 15. The plurality of locking holes correspond one-to-one to a plurality of assembly holes among the plurality of assembly holes.

[0097] Alternatively, if Figure 1 As shown, in the embodiment of the present application, the turntable 15 is provided with a circle of assembly holes arranged in sequence and at intervals around the rotation axis of the turntable 15. The plurality of assembly holes are distributed on an arc with the rotation center of the turntable 15 as the center.

[0098] Alternatively, if Figure 2 and Fig.11 As shown, in the embodiment of the present application, the slewing locking mechanism also includes an auxiliary slewing locking structure 5, which includes a main body mounting seat 5-1 installed on the launching platform 1, an adjusting member 5-2 movably arranged on the main body mounting seat 5-1, a supporting 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. The adjusting member 5-2 is driven to move by the driving member 5-5, the supporting seat 5-3 is connected to the ball head of the adjusting member 5-2, and the supporting seat 5-3 is used to abut against the turntable 15.

[0099] In the embodiment of the present application, the auxiliary rotation locking structure 5 is connected to the ground launch platform 1 by using 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, and the adjusting member 5-2 is driven to move by the driving member 5-5 to realize the extension and retraction of the adjusting member 5-2 relative to the main body mounting seat 5-1. One end of the adjusting member 5-2 is connected to the ball head of the support seat 5-3, so that the support seat 5-3 can rotate with multiple degrees of freedom relative to the end of the adjusting member 5-2, and the support seat 5-3 can abut against the turntable 15. The ball head connection method can adapt to the adjustment of the azimuth angle of the turntable 15. Through the extension of the adjusting member 5-2 and the support seat 5-3 against the side of the turntable 15, the reliable auxiliary locking of the turntable 15 and the above equipment is realized, and the turntable 15 is further locked at the target azimuth angle.

[0100] Alternatively, if Fig.11 As shown, in the embodiment of the present application, the adjusting member 5-2 is a screw rod, and the screw rod cooperates with the thread of the main body mounting seat 5-1. By rotating the screw rod, the screw rod can be extended and retracted relative to the main body mounting seat 5-1. The end of one end of the screw rod is rotatably connected to the support seat 5-3 by a ball head connection, so that the support seat 5-3 can adapt to the adjustment of the azimuth angle of the turntable 15 to support the side of the turntable 15, thereby realizing reliable auxiliary locking of the turntable 15 and above equipment.

[0101] Alternatively, if Fig.11 As shown, in the embodiment of the present application, the ball head at the end of the screw is connected to the support seat 5-3 through the ball head sealing plate 5-4.

[0102] Alternatively, if Fig.11 As shown, in the embodiment of the present application, the driving member 5-5 includes a handwheel, which is fixedly connected to one end of the screw rod away from the support seat 5-3. Optionally, the handwheel is detachably connected to the screw rod, and a limiting top plate 5-6 and a locking nut 5-7 are provided on the side of the handwheel away from the support seat 5-3. The limiting top plate 5-6 is used to prevent the handwheel from falling off the screw rod, and the locking nut 5-7 is used to fix the handwheel on the screw rod.

[0103] The flying structure launching device provided in the embodiment of the present application is composed of a launching platform 1, a deflector 2, a carrying cabin 3, a slewing locking seat 4, an auxiliary slewing locking structure 5, a gas flow baffle 6, a marching locking mechanism 7, a leveling leg 8, a tool box 9, a slewing driving mechanism 10, etc., and is mainly used to provide an installation carrier for the slewing table 15, the erecting frame 16 and the launching box 18 of the target launching system.

[0104] Alternatively, if Figure 2 As shown, in the embodiment of the present application, the leveling legs 8 can be hydraulic leveling legs, or can be a telescopic structure such as a jack. The tool box 9 is used to store operating tools (such as wrenches), spare parts, consumables, etc.

[0105] The working process of the flying structure launching device provided in the embodiment of the present application is as follows: (1) Place the ground launch platform 1 at the predetermined launch site and securely fix the ground launch platform 1 to the ground using anchor bolts; (2) Unlock the movable bolt of the marching locking mechanism 7 and flip it to an unlocking position parallel to the upper surface of the load compartment 3; (3) Unlock the turntable 15 and the rotation locking mechanism (remove the bolts connecting the turntable 15 and the rotation locking seat 4 so that the support seat 5-3 of the auxiliary rotation locking structure 5 no longer presses against the side of the turntable 15), so that the turntable 15 is in a free state; (4) Using the leveling legs 8 to support the ground launch platform 1, and adjusting the heel angle and pitch angle; (5) The rotary table 15 is rotated about the rotary support 14 by manually cranking the screw lift of the rotary drive mechanism 10 to achieve the azimuth angle required for the launch (i.e., the target azimuth angle); (6) After rotating into place, the turntable 15 is securely locked with the rotation locking mechanism (the bolts connecting the turntable 15 and the rotation locking seat 4 are tightened, and the hand wheel of the auxiliary rotation locking structure 5 is turned so that the support seat 5-3 is pressed against the side of the turntable 15), thereby realizing the locking of the rotation mechanism; (7) Open the door of the load-bearing cabin 3 and operate the control box 11, the generator set 12, the hydraulic system 13 and other internal equipment as needed to realize power supply, erection and other operations; (8) After completing pre-launch preparations, all equipment is powered off, the hatch is closed, and personnel are evacuated.

[0106] The flying structure launching device provided in the embodiment of the present application can be applied to the ground launching of multi-functional cruise targets, and can further be applied to the ground launching of hypersonic targets.

[0107] Based on the same inventive concept, the embodiment of the present application provides an aircraft launch system, which includes: an aircraft and the above-mentioned flying structure launch device. The aircraft is placed in the launch box 18 of the rotating mechanism of the flying structure launch device as the flying structure to be launched.

[0108] 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, the aircraft launch system in the embodiment of the present application also has the above-mentioned beneficial effects of the flight structure launch device in the embodiment of the present application, which will not be repeated here.

[0109] Optionally, in an embodiment of the present application, the aircraft includes but is not limited to cruise targets, aircraft, spacecraft, rockets, etc.

[0110] By applying the embodiments of the present application, at least the following beneficial effects can be achieved: In an embodiment of the present application, a flight structure to be launched (such as an aircraft) is carried by a slewing mechanism, and the slewing mechanism is rotatably arranged relative to a launch platform. By rotating the slewing mechanism, the flight structure to be launched can be driven to rotate relative to the launch platform, thereby adjusting the azimuth of the flight structure to be launched. A slewing drive mechanism is connected to the slewing mechanism, and the slewing drive mechanism can drive the slewing mechanism to rotate, thereby driving the flight structure to be launched to rotate, and achieving the purpose of adjusting the azimuth of the flight structure to be launched. The slewing mechanism can be locked on the launch platform by a slewing locking mechanism, thereby fixing the flight structure to be launched at the target azimuth. A gas flow guide structure is arranged on at least part of the periphery of the slewing mechanism, so that the gas flow generated by the flight structure to be launched can be guided through the gas flow guide structure. The electrical equipment provides at least one function of control, drive and power supply to the slewing mechanism.

[0111] In the embodiment of the present application, the rotary drive mechanism, the rotary locking mechanism, the gas flow guide structure and the electrical equipment are integrated on the launch platform, and a highly integrated design is adopted to integrate the functions of hydraulic and electrical equipment installation, azimuth adjustment, rotary locking and unlocking, and gas flow guide into the launch platform, which not only reduces the development cost, but also improves the function of the launch system. In addition, in the embodiment of the present application, the azimuth angle of the flying structure to be launched is adjustable by setting a rotary mechanism. Therefore, the flying structure launch device provided in the embodiment of the present application solves the difficulties of high launch cost and loss of target distance in vertical launch in the development stage of inclined launch of cruise targets.

[0112] Those skilled in the art will appreciate that the various operations, methods, steps, measures, and schemes in the processes discussed in this application may be alternated, changed, combined, or deleted. Furthermore, other steps, measures, and schemes in the various operations, methods, and processes discussed in this application may also be alternated, changed, rearranged, decomposed, combined, or deleted. Furthermore, steps, measures, and schemes in the related art that are similar to those disclosed in this application may also be alternated, changed, rearranged, decomposed, combined, or deleted.

[0113] In the description of the present application, the directions or positional relationships indicated by words such as "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" are based on the exemplary directions or positional relationships shown in the accompanying drawings. They are for the convenience of describing or simplifying the description of the embodiments of the present application, and do not indicate or imply that the referred device or component must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be understood as limitations on the present application.

[0114] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0115] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0116] 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.

[0117] The above is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, without departing from the technical concept of the scheme of the present application, other similar implementation methods based on the technical ideas of the present application are also within the protection scope of the embodiments of the present application.

Claims

1. A flying structure launching device, characterized in that: include: Launch platform; A slewing mechanism, rotatably disposed on the launching platform, and used for carrying 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 slewing locking mechanism, used to lock the slewing mechanism on the launching platform; A gas flow guiding structure, located at least partially around the circumference of the rotary mechanism, and used to guide the gas flow generated by the flight structure to be launched; An electrical device, connected at least to 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 guiding structure and the electrical equipment are integrated on the launching platform.

2. The flying structure launching device according to claim 1, characterized in that: The rotary drive mechanism comprises: A driving component, mounted on the launching platform; a first transmission component connected to the driving component, wherein the first transmission component has 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, and 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.

3. The flying structure launching device according to claim 2, 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 matched with the lead screw, and a guide structure connected to the drive nut, 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 comprises 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.

4. The flying structure launching device according to claim 3, characterized in that: Include at least one of the following: The rotary drive mechanism also 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 meshed with the turbine to drive the turbine to rotate, and the turbine is sleeved on the lead screw to drive the lead screw to rotate; The guide structure includes a slider fixedly connected to the driving nut and a guide rail arranged on the launching platform, the guide rail extends along the first direction, and the slider is slidably matched with the guide rail; The rotary drive mechanism further comprises a sliding seat fixedly connected to the driving nut, and the sliding seat is provided with a plurality of the guide structures sequentially arranged in the second direction.

5. The flying structure launching device according to any one of claims 1 to 4, characterized in that: It also includes a carrying cabin, which is detachably mounted on the launching platform; The electrical equipment comprises a control box, a generator set and a hydraulic system, wherein 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-bearing cabin.

6. The flying structure launching device according to claim 5, 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 bearing 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 limiting seat. When the locking member is at 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.

7. The flying structure launching device according to claim 6, characterized in that: Include at least one of the following: The opening of the limiting groove is arranged upward, and in the direction in which the bottom of the limiting groove points to the opening, the side wall of the limiting groove is inclined outward; The locking member comprises a bolt, the bolt is rotatably connected to the lateral limit seat through a pin, and the fastener comprises a nut for threadably cooperating with the bolt; A plurality of locking members are disposed 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.

8. The flying structure launching device according to any one of claims 1 to 4, 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 guiding structure comprises a flow guide, which is arranged on a part of the outer periphery of the rotary mechanism, and the top surface of the flow guide is an inclined surface inclined downward in a direction away from the rotary mechanism, and the gas flow is guided by 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 launching platform, and the side sealing plate is connected to the main body bending plate to form an accommodating cavity for accommodating the rotary drive mechanism to prevent the gas flow from blowing onto the rotary drive mechanism.

9. The flying structure launching device according to any one of claims 1 to 4, characterized in that: The slewing locking mechanism includes a slewing locking seat connected to the launching platform; The rotary locking seat is provided with a plurality of locking holes, which 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.

10. The flying structure launching device according to claim 9, characterized in that: Include at least one of the following: The rotary locking seats are provided in plurality, and the plurality of rotary locking seats are arranged at intervals along the circumference of the rotary table; The turntable is provided with a plurality of assembly holes which are arranged in sequence and at intervals around the rotation axis of the turntable; The rotary locking mechanism also includes an auxiliary rotary locking structure, which includes a main mounting seat installed on the launching platform, an adjusting member movably arranged on the main mounting seat, a supporting 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 supporting seat is connected to the ball head of the adjusting member, and the supporting seat is used to abut against the turntable.

11. An aircraft launch system, characterized in that: include: A flying structure launching device as claimed in any one of claims 1 to 10; The flying vehicle, as a flying structure to be launched, is placed in the launching box of the rotating mechanism of the flying structure launching device.

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