Chemical fuel multi-stage propulsion electromagnetic hybrid catapulting device

Abstract

The utility model discloses a chemical fuel multi-stage propulsion electromagnetic mixed ejection device which comprises a base, a movable seat, an electromagnetic propulsion assembly and a steam propulsion assembly. The moving seat is slidably connected to the base in the length direction of the base, the electromagnetic propelling assembly comprises a first stator and a second stator which are fixedly installed on the side, in the thickness direction, of the base, and a mover fixedly installed on the side, close to the base, of the moving seat, and the mover is located between the first stator and the second stator; the steam propelling assembly is fixedly installed on the side, away from the base, of the movable base. The mover coil in a power-on state interacts with the multiple first magnetic parts and the multiple second magnetic parts respectively, and the steam propelling assembly jointly drives the movable base to move in the length direction of the base, so that the steam propelling assembly and the electromagnetic propelling assembly can be designed in a miniaturized mode; the chemical fuel multi-stage propulsion electromagnetic mixed ejection device has the advantages of being compact in structure and small in equipment size.

Description

Technical Field

[0001] This utility model belongs to the field of catapult technology, specifically relating to a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device. Background Technology

[0002] Existing catapults are mainly divided into steam catapults and electromagnetic catapults. Specifically, a steam catapult uses high-pressure steam to drive a piston, thereby accelerating some machines in a very short time. For example, it can be used to launch airplanes, rockets, or drones to takeoff speed. An electromagnetic catapult is a linear propulsion technology that uses electromagnetic force to accelerate objects to high speeds in a short time. It is widely used in military, aerospace, and industrial fields. For example, it can be used to launch airplanes and drones to takeoff speed.

[0003] However, when using steam catapults as the sole power source for drone takeoff or launch, existing technologies suffer from the problem of large equipment size, making them unsuitable for small and medium-sized drones. For example, the equipment is too large when used alone as a launcher for drones. While electromagnetic catapults offer advantages such as high controllability and launch efficiency, they also suffer from the drawback of consuming enormous amounts of energy and requiring a large energy storage and conversion system to achieve the required takeoff speed when used alone for drone takeoff or launch. This limits their applicability to large energy supply platforms such as nuclear-powered aircraft carriers. For instance, when using electromagnetic catapults to launch drones, the permanent magnets need to be spaced far apart to achieve the required takeoff speed. Therefore, using electromagnetic catapults as the sole power source for drone takeoff or launch also suffers from the problem of large equipment size, making them unsuitable for small and medium-sized drones.

[0004] Therefore, when using steam catapults or electromagnetic catapults as the sole power source for drones to start or take off in existing technologies, there are problems such as the large size of the equipment and the difficulty in adapting it to small and medium-sized drones. Utility Model Content

[0005] The purpose of this invention is to solve the problem that when steam catapults or electromagnetic catapults are used as the sole power source for the start-up or take-off of drones, the equipment is too large and difficult to adapt to small and medium-sized drones.

[0006] To solve the above-mentioned technical problems, this utility model discloses a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device, including a base, a movable base, an electromagnetic propulsion component, and a steam propulsion component.

[0007] The movable base is positioned opposite the base on one side along its thickness direction and is slidably connected to the base along its length direction. The movable base is used to mount the drone.

[0008] The electromagnetic propulsion assembly includes a first stator and a second stator fixedly mounted on one side of a base along its thickness direction, and a mover fixedly mounted on a movable seat near the base. The first stator includes a plurality of first magnetic elements arranged side by side along the length direction of the base, and the second stator includes a plurality of second magnetic elements arranged side by side along the length direction of the base. The mover includes a mover coil. In the width direction of the base, the plurality of first magnetic elements and the plurality of second magnetic elements are arranged at intervals relative to each other. The mover is located between the first stator and the second stator, and both sides of the mover are in contact with and electrically connected to the first stator and the second stator, respectively, so as to transmit current to the mover coil of the mover through the first stator and the second stator. Through the interaction between the energized mover coil and the plurality of first magnetic elements and the plurality of second magnetic elements, the mover and the movable seat mounted on the mover are driven to translate relative to the base along the length direction of the base.

[0009] The steam propulsion assembly is fixedly installed on the side of the moving base away from the base, and the steam propulsion assembly is used to drive the moving base to move relative to the base along the length of the base.

[0010] Using the above technical solution, this chemical fuel multi-stage propulsion electromagnetic hybrid catapult device launches a UAV by mounting the UAV on a mobile seat and simultaneously activating the steam propulsion assembly and the electromagnetic propulsion assembly. At this time, current is transmitted to the mover coil of the mover through the first stator and the second stator. The energized mover coil interacts with multiple first magnetic components and multiple second magnetic components to generate Lorentz force, thereby subjecting the mover coil to linear thrust. This drives the mover and the mobile seat mounted on the mover to translate relative to the base along the length of the base. Simultaneously, the steam propulsion assembly drives the mobile seat to translate along the length of the base. When the mobile seat reaches the designated position, it is blocked, and the UAV detaches from the mobile seat under the action of inertial force, thus achieving catapult takeoff.

[0011] Therefore, it can be seen that when this chemical fuel multi-stage propulsion electromagnetic hybrid catapult launches a UAV, the moving seat is driven along the length of the base by both steam propulsion and electromagnetic propulsion components. The UAV takes off through two power sources. Under the premise of adapting to and meeting the takeoff speed of small and medium-sized UAVs, the use of two power sources means that the power of the steam propulsion and electromagnetic propulsion components does not need to be designed to be large. Therefore, the steam propulsion and electromagnetic propulsion components can be miniaturized. The moving seat is driven by the superposition of the power applied by the steam propulsion and electromagnetic propulsion components. This reduces the size of this chemical fuel multi-stage propulsion electromagnetic hybrid catapult launcher and the energy consumption of the electromagnetic propulsion component during use. As a result, this chemical fuel multi-stage propulsion electromagnetic hybrid catapult launcher has the advantages of compact structure and small equipment size.

[0012] Furthermore, since the steam propulsion component is fixedly installed on the side of the moving base away from the base, and is integrated on the moving base, after miniaturizing the steam propulsion component and the electromagnetic propulsion component, the steam propulsion component does not occupy the installation position of the electromagnetic propulsion component. Moreover, since the steam propulsion component applies additional force to drive the moving base, there is no need to set the base length too long to meet the acceleration distance of the electromagnetic propulsion component, thus achieving the miniaturization of the base design as well. This further makes the structure of this chemical fuel multi-stage propulsion electromagnetic hybrid catapult device more compact.

[0013] Furthermore, the present invention also discloses a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device, wherein the steam propulsion assembly includes a first propulsion component, a first impact component, a second propulsion component, a second impact component, and a third propulsion component, which are sequentially arranged and fixedly installed on the side of the moving base away from the base along the length direction of the base.

[0014] One end of the first impact component is fixedly connected to one end of the first propulsion component, and the other end is fixedly connected to one end of the second propulsion component. One end of the second impact component is fixedly connected to the other end of the second propulsion component, and the other end is fixedly connected to one end of the third propulsion component.

[0015] Using the above technical solution, when the steam propulsion assembly drives the mobile seat to move along the length of the base, the third propulsion component is activated to perform a first jet boost; then the third propulsion component drives the second impact component, which in turn activates the second propulsion component to perform a second jet boost; then the second propulsion component drives the first impact component, which in turn activates the first propulsion component to perform a third jet boost. This ensures that the steam propulsion assembly continuously provides power to the mobile seat during its movement, thereby enabling the UAV to take off reliably.

[0016] Furthermore, the present invention also discloses a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device. The first propulsion component includes a first fuel tank with a first cavity inside, a first ignition component and a first explosive component. The two ends of the first fuel tank are closed, and a first connection hole is provided on one end wall of the first fuel tank. The first ignition component is fixedly installed in the first connection hole, and the first explosive component is installed on the circumferential side wall of the first fuel tank.

[0017] The second propulsion component includes a second fuel tank with a second cavity inside, a second ignition component, and a second explosive component. One end of the second fuel tank is open and the other end is closed. A second connection hole is provided on the end wall of the other end of the second fuel tank. The second ignition component is fixedly installed in the second connection hole, and the second explosive component is installed on the circumferential side wall of the second fuel tank.

[0018] The third propulsion component includes a third fuel tank with a third cavity inside, a third ignition component, and a third explosive component. One end of the third fuel tank is open and the other end is closed. A third connection hole is provided on the end wall of the other end of the third fuel tank. The third ignition component is fixedly installed in the third connection hole, and the third explosive component is installed on the circumferential side wall of the third fuel tank.

[0019] The first impact component includes a first sealing flange and a first impact member. One end of the first sealing flange is fixedly connected to one end of the peripheral wall of the first fuel tank, and the other end is fixedly connected to one end of the peripheral wall of the second fuel tank. The first impact member is movably installed at the center of the first sealing flange along the length direction of the base, and the first impact member and the first ignition member are directly opposite each other in the length direction of the base.

[0020] The second impact component includes a second sealing flange and a second impact member. One end of the second sealing flange is fixedly connected to the peripheral wall of the other end of the second fuel tank, and the other end is fixedly connected to the peripheral wall of the third fuel tank. The second impact member is movably installed at the center of the second sealing flange along the length direction of the base, and the second impact member and the second ignition member are directly opposite each other in the length direction of the base.

[0021] Using the above technical solution, when the steam propulsion assembly drives the mobile base to move, the high-pressure steam in the third fuel tank is ignited by the third ignition component, causing the third explosive component to eject gas for the first jet boost. Simultaneously, the high-pressure steam in the third fuel tank drives the second impact component to move along the length of the base toward the second ignition component, and then impacts the second ignition component, causing the second ignition component to ignite the high-pressure steam in the second fuel tank, causing the second explosive component to eject gas for the second jet boost. At the same time, the high-pressure steam in the second fuel tank drives the first impact component to move along the length of the base toward the second ignition component, and then impacts the first ignition component, causing the first ignition component to ignite the high-pressure steam in the first fuel tank, causing the first explosive component to eject gas for the third jet boost. In this process, only the high-pressure steam in the third fuel tank needs to be ignited by the third ignition component to achieve three jet boosts, so that when the steam propulsion assembly drives the mobile base to move, it continuously provides power to the mobile base, thereby making the UAV takeoff speed faster.

[0022] Furthermore, the present invention also discloses a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device, wherein a first steam interface is provided on the peripheral wall of the first fuel tank, a second steam interface is provided on the peripheral wall of the second fuel tank, and a third steam interface is provided on the peripheral wall of the third fuel tank.

[0023] The first explosive component includes at least one pair of first pressure relief pipes fixedly installed on the circumferential side wall of the first fuel tank. Each pair of first pressure relief pipes is arranged opposite to each other in the radial direction of the first fuel tank. One end of each first pressure relief pipe is connected to the first fuel tank, and the other end extends away from the first fuel tank and is parallel to the first fuel tank. The other end of each first pressure relief pipe is provided with a first explosion valve. The first ignition component includes a first piezoelectric ceramic, which is fixedly installed in a first connecting hole. The discharge electrode of the first piezoelectric ceramic extends through the first connecting hole into a first cavity. The first connecting hole is located at the center of one end wall of the first fuel tank.

[0024] The second explosive component includes at least one pair of second pressure relief pipes fixedly installed on the circumferential side wall of the first fuel tank. Each pair of second pressure relief pipes is arranged opposite to each other in the radial direction of the second fuel tank. One end of each second pressure relief pipe is connected to the second fuel tank, and the other end extends away from the closed end of the first fuel tank and is parallel to the second fuel tank. A second explosive valve is provided at the other end of each second pressure relief pipe. The second ignition component includes a second piezoelectric ceramic, which is fixedly installed in a second connecting hole. The discharge electrode of the second piezoelectric ceramic extends through the second connecting hole into the second cavity. The second connecting hole is located at the center of one end wall of the second fuel tank.

[0025] The third explosive component includes at least one pair of third pressure relief pipes fixedly installed on the circumferential side wall of the third fuel tank. Each pair of third pressure relief pipes is arranged opposite to each other in the radial direction of the third fuel tank. One end of each third pressure relief pipe is connected to the third fuel tank, and the other end extends away from the closed end of the first fuel tank and is parallel to the third fuel tank. A third explosive valve is provided at the other end of each third pressure relief pipe. The third ignition component includes an electric shock device, which is fixedly installed in a third connection hole. The discharge electrode of the electric shock device extends through the third connection hole into the third cavity. The third connection hole is located at the center of one end wall of the third fuel tank.

[0026] Using the above technical solution, during the first jet boost, the high-pressure steam in the third fuel tank is ignited by the discharge electrode of the stun gun, thereby releasing pressure and causing the third explosion valve to explode. The high-pressure steam is then ejected from the other end of the third pressure relief pipe, thus achieving the first jet boost. During the second jet boost, the high-pressure steam in the second fuel tank is ignited by the discharge electrode of the second piezoelectric ceramic, thereby releasing pressure and causing the second explosion valve to explode. The high-pressure steam is then ejected from the other end of the second pressure relief pipe, thus achieving the second jet boost. During the third jet boost, the high-pressure steam in the first fuel tank is ignited by the discharge electrode of the first piezoelectric ceramic, thereby releasing pressure and causing the first explosion valve to explode. The high-pressure steam is then ejected from the other end of the first pressure relief pipe, thus achieving the third jet boost. This ensures that the steam propulsion assembly continuously provides power to the moving seat, guaranteeing the takeoff speed of the UAV.

[0027] Furthermore, after the drone takes off, by quickly replacing the first explosion valve plate at the other end of the first pressure relief pipe, replacing the second explosion valve plate at the other end of the second pressure relief pipe, and replacing the third explosion valve plate at the other end of the third pressure relief pipe; then, by quickly filling the first fuel tank, second fuel tank, and third fuel tank with high-pressure steam through the first steam interface, second steam interface, and third steam interface respectively, preparations can be made for the next takeoff of the drone.

[0028] Furthermore, the present invention also discloses a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device, wherein the first impact component further includes a first cover plate, the first cover plate is fixedly installed on the other end of the first sealing flange, and the center of the first sealing flange is provided with a first channel having openings at both ends along the length direction of the base.

[0029] The first cover plate covers the opening at one end of the first channel, and the center of the first cover plate has a first passage opening that communicates with the first channel. The first impact member includes a first impact block that is movably installed in the first channel, and a plurality of first telescopic springs. One end of each first telescopic spring is fixedly connected to the corresponding side of the first impact block, and the other end extends along the length of the base and is fixedly connected to the first cover plate.

[0030] The second impact component also includes a second cover plate, which is fixedly installed at the other end of the second sealing flange, and the center of the second sealing flange has a second channel with openings at both ends along the length of the base.

[0031] The second cover plate covers the opening at one end of the second channel, and the center of the second cover plate has a second passage opening that communicates with the second channel. The second impact member includes a second impact block that is movably installed in the second channel, and a plurality of second telescopic springs. One end of each second telescopic spring is fixedly connected to the corresponding side of the second impact block, and the other end extends along the length of the base and is fixedly connected to the second cover plate.

[0032] Using the above technical solution, the high-pressure steam in the third fuel tank is ignited by the discharge electrode of the stun gun, causing the valve plate of the third explosion valve to explode for the first jet boost. At this time, the pressure in the high-pressure steam in the third fuel tank is released, causing the second impact block to move rapidly along the length of the base, thereby impacting the second piezoelectric ceramic. The discharge electrode of the second piezoelectric ceramic ignites the high-pressure steam in the second fuel tank, causing the valve plate of the second explosion valve to explode for the second jet boost. Then, the pressure in the high-pressure steam in the second fuel tank is released, causing the first impact block to move rapidly along the length of the base, thereby impacting the second piezoelectric ceramic. The discharge electrode of the first piezoelectric ceramic ignites the high-pressure steam in the first fuel tank, causing the valve plate of the second explosion valve to explode for the third jet boost. In this process, the three jet boosts of high-pressure steam are completed sequentially and quickly connected, ensuring that the mobile base has sufficient power, enabling the UAV to take off reliably.

[0033] In addition, when the first impact block moves and impacts the first piezoelectric ceramic, multiple first telescopic springs are stretched, and when the second impact block moves and impacts the second piezoelectric ceramic, multiple second telescopic springs are stretched. After the impact is completed, the first impact block can be quickly reset by pulling it with multiple first telescopic springs, and the second impact block can be quickly reset by pulling it with multiple second telescopic springs.

[0034] Furthermore, the embodiments of this utility model also disclose a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device. The first stator further includes a first mounting plate and a plurality of first electrical connecting pieces. The first mounting plate is vertically fixed to one side of the base. The plurality of first electrical connecting pieces are arranged side by side on the first mounting plate along the length direction of the base. The plurality of first magnetic components are arranged side by side on the first mounting plate along the length direction of the base.

[0035] The second stator also includes a second mounting plate and a plurality of second electrical connecting pieces. The second mounting plate is vertically fixed to one side of the base. The plurality of second electrical connecting pieces are arranged side by side on the second mounting plate along the length of the base. The plurality of second magnetic components are arranged side by side on the second mounting plate along the length of the base.

[0036] In the thickness direction of the base, a plurality of first electrical connecting pieces are spaced apart from a plurality of first magnetic elements, and a plurality of second electrical connecting pieces are spaced apart from a plurality of second magnetic elements. In the width direction of the base, a first mounting plate and a second mounting plate are spaced apart relative to each other, and a plurality of first electrical connecting pieces and a plurality of second electrical connecting pieces are spaced apart relative to each other. When the mover and the movable seat move along the length direction of the base, the two sides of the mover sequentially contact and are electrically connected with their respective first electrical connecting pieces and second electrical connecting pieces, so as to transmit current to the mover coil of the mover through the corresponding first electrical connecting pieces and second electrical connecting pieces.

[0037] By adopting the above technical solution, since the mover is located between the first stator and the second stator, by setting the first mounting plate and the second mounting plate, after multiple first magnetic elements are arranged side by side on the first mounting plate and multiple second magnetic elements are arranged side by side on the second mounting plate, when the mover coil is driven to move by the interaction of the multiple first magnetic elements and the multiple second magnetic elements, the first mounting plate and the second mounting plate can limit the mover in the width direction of the base, thereby avoiding the risk of the mover shifting position during movement.

[0038] Furthermore, since the mover can be limited in the width direction of the base by the first mounting plate and the second mounting plate, when the mover and the movable seat move along the length direction of the base, the two sides of the mover can reliably contact and connect with their respective first and second electrical connecting pieces in sequence, thus achieving the purpose of reliably moving the mover.

[0039] Furthermore, the embodiments of this utility model also disclose a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device, wherein the mover further includes a coil box, a first brush and a second brush. The coil box is fixedly installed on the side of the moving base near the base, and the first brush and the second brush are respectively fixedly installed on both sides of the coil box in the width direction of the base.

[0040] The coil box has an internal space for housing, in which the moving coil is fixedly installed. The first brush and the second brush are electrically connected to the moving coil. When the moving coil and the movable seat move along the length of the base, the first brush and the second brush sequentially contact and connect with their respective first and second electrical connecting pieces, so that the corresponding first and second electrical connecting pieces transmit current to the moving coil through the first brush and the second brush.

[0041] By adopting the above technical solution, the moving coil can be limited by setting a coil box, thereby avoiding the risk of the moving coil becoming loose during movement. In addition, by setting the second brush to contact and connect with the second electrical connecting piece, since the contact area of ​​the brush is large when it is electrically connected, the first brush and the first electrical connecting piece can be reliably electrically connected, and the second brush and the second electrical connecting piece can be reliably electrically connected when the moving part moves along the length direction of the base, thereby enabling the moving part to move reliably along the length direction of the base.

[0042] Furthermore, the present invention also discloses a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device, wherein a pair of guide portions are provided on one side of the base along its thickness direction, the pair of guide portions extend along the length direction of the base, and the pair of guide portions are arranged at intervals relative to each other in the width direction of the base, and the first stator and the second stator are located between the pair of guide portions.

[0043] The mobile base includes a sliding plate and a connecting frame fixedly installed on the side of the sliding plate away from the base. The side of the sliding plate near the base is provided with a pair of guided parts corresponding to a pair of guide parts. The pair of guided parts are slidably connected to the pair of guide parts so that the mobile base is slidably connected to the base along the length direction of the base. The end of the connecting frame away from the base is provided with a pair of connecting protrusions, and the pair of connecting protrusions are used to engage the landing gear of the drone.

[0044] By adopting the above technical solution, a pair of guide parts and a pair of guided parts are set up to cooperate with each other, so that the slide can be guided by the pair of guide parts during the movement, thereby realizing the purpose of the moving seat being able to move reliably along the length direction of the base.

[0045] In addition, a pair of connecting protrusions are set on the connecting frame to easily engage the drone's landing gear when the drone needs to be launched, so that the drone will not fall off the connecting frame while being moved by the moving seat.

[0046] Furthermore, the embodiments of this utility model also disclose a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device, which further includes a launch support and a position adjustment assembly. The launch support includes a support body and a support plate fixedly installed on the top of the support body. In the length direction of the support plate, one end of the base is rotatably connected to one end of the support plate. The position adjustment assembly includes a drive component and a transmission component. The drive component is installed on the other end of the support plate near the base. One end of the transmission component is drively connected to the drive end of the drive component, and the other end is drively connected to the other side of the base.

[0047] Using the above technical solution, when it is necessary to adjust the launch angle of the UAV, the drive component can drive the transmission component to swing, thereby causing the base to swing around one end, changing the position of the other end of the base in the height direction of the launch bracket, thus achieving the purpose of adjusting the launch angle of the UAV and enabling the UAV to adapt to different launch environments.

[0048] Furthermore, the present invention also discloses a chemical fuel multi-stage propulsion electromagnetic hybrid catapult device. The driving components include a mounting frame, a screw, a drive handwheel, and a slider. The mounting frame is fixedly installed on the other end of the support plate near the base. The screw extends along the length of the support plate and is rotatably connected to the mounting frame at both ends. The drive handwheel is fixed to one end of the screw, and the slider is threadedly connected to the screw.

[0049] The transmission component includes a pair of transmission rods that correspond one-to-one with the two ends of the slider in the width direction of the support plate. One end of each transmission rod is rotatably connected to the corresponding end of the slider, and the other end extends to be rotatably connected to the other end of the base.

[0050] Using the above technical solution, when it is necessary to adjust the launch angle of the drone, the drive handwheel is rotated, which causes the screw to rotate. At this time, the slider moves along the length of the base, which in turn drives a pair of transmission rods to gradually raise or lower the other end of the base, ultimately achieving the purpose of adjusting the launch angle of the drone. During this process, since the slider and the screw are threadedly connected, the position of the base can be limited by the slider after the angle of the base is adjusted, thus avoiding the risk of the base position shifting due to the weight of the drone when it is launched. Attached Figure Description

[0051] Figure 1 A three-dimensional schematic diagram of the chemical fuel multi-stage propulsion electromagnetic hybrid catapult device provided in this embodiment of the utility model when an unmanned aerial vehicle is installed;

[0052] Figure 2 A partial perspective view of the chemical fuel multi-stage propulsion electromagnetic hybrid catapult device provided in an embodiment of this utility model;

[0053] Figure 3 A partial three-dimensional schematic diagram of the chemical fuel multi-stage propulsion electromagnetic hybrid catapult device provided in this embodiment of the utility model when an unmanned aerial vehicle is installed;

[0054] Figure 4 This is a three-dimensional schematic diagram of the first stator provided in an embodiment of the present utility model;

[0055] Figure 5 This is a three-dimensional schematic diagram of the mover provided in an embodiment of the present utility model;

[0056] Figure 6 A perspective view of the connecting frame provided in an embodiment of this utility model;

[0057] Figure 7 A perspective view of the steam propulsion assembly provided in an embodiment of this utility model;

[0058] Figure 8 A cross-sectional view of the steam propulsion assembly provided in an embodiment of this utility model;

[0059] Figure 9 for Figure 8 Enlarged view of section A;

[0060] Figure 10 A perspective view of the first propulsion component and the first impact component being fixedly connected according to an embodiment of the present utility model;

[0061] Figure 11 This is a cross-sectional view of the first propulsion component and the first impact component being fixedly connected according to an embodiment of the present utility model;

[0062] Figure 12 A perspective view of the first impact component provided in an embodiment of this utility model;

[0063] Figure 13 An exploded view of the first impact component provided in this embodiment of the utility model;

[0064] Figure 14 A cross-sectional view of the first impact component provided in an embodiment of this utility model;

[0065] Figure 15 for Figure 14 Enlarged view of section B;

[0066] Figure 16 This is a three-dimensional schematic diagram of the second propulsion component being fixedly connected with the first impact component and the second impact component according to an embodiment of the present utility model.

[0067] Figure 17 This is a cross-sectional view of the second propulsion component and the first and second impact components fixedly connected according to an embodiment of the present utility model.

[0068] Figure 18 A perspective view of the third propulsion component and the second impact component fixedly connected according to an embodiment of the present utility model;

[0069] Figure 19 This is a cross-sectional view of the third propulsion component and the second impact component when they are fixedly connected according to an embodiment of the present utility model;

[0070] Figure 20Another partial perspective view of the chemical fuel multi-stage propulsion electromagnetic hybrid catapult device provided in this embodiment of the utility model;

[0071] Figure 21 for Figure 20 A magnified view of a portion of the image;

[0072] Figure 22 This is a partial schematic diagram of the base;

[0073] Figure 23 for Figure 22 Enlarged view of section C.

[0074] Explanation of reference numerals in the attached figures:

[0075] 1. Base;

[0076] 10. Guide section; 11. Baffle; 12. Hydraulic damper; 13. Groove; 14. Connecting ring;

[0077] 2. Portable seat;

[0078] 20. Slide plate; 21. Connecting frame; 22. Guided part; 23. Connecting protrusion;

[0079] 3. Electromagnetic propulsion components;

[0080] 30. First stator;

[0081] 300, First magnetic component; 301, First mounting plate; 302, First electrical connector;

[0082] 31. Second stator;

[0083] 310. Second magnetic component; 312. Second mounting plate; 313. Second electrical connector;

[0084] 32. Moving part;

[0085] 320. Moving coil; 321. Coil box; 322. First brush; 323. Second brush;

[0086] 4. Steam propulsion components;

[0087] 40. First propulsion component;

[0088] 400. First fuel tank; 401. First explosive component; 402. First piezoelectric ceramic; 403. First pressure relief pipe; 404. First explosion valve; 405. First steam interface; 406. First connecting seat;

[0089] 41. First impact component;

[0090] 410. First sealing flange; 411. First impact member; 412. First cover plate; 413. First channel; 414. First impact block; 415. First telescopic spring; 416. First passage; 417. First ball bearing; 418. First buffer ring;

[0091] 42. Second propulsion component;

[0092] 420. Second fuel tank; 421. Second explosive component; 422. Second piezoelectric ceramic; 423. Second pressure relief pipe; 424. Second explosion valve; 425. Second steam interface; 426. Second connecting seat;

[0093] 43. Second impact component;

[0094] 430. Second sealing flange; 431. Second impact member; 432. Second cover plate; 433. Second channel; 434. Second impact block; 435. Second telescopic spring; 436. Second passage;

[0095] 44. Third propulsion component;

[0096] 440. Third fuel tank; 441. Third explosive component; 442. Electric shock device; 443. Third pressure relief pipe; 444. Third explosion valve; 445. Third steam interface; 446. Third connection seat;

[0097] 5. Launching bracket;

[0098] 50. Support body; 51. Support plate; 52. Clearance opening;

[0099] 6. Position adjustment component;

[0100] 60. Drive components;

[0101] 600. Mounting bracket; 601. Screw; 602. Drive handwheel; 603. Slider;

[0102] 61. Transmission components;

[0103] 610. Transmission rod;

[0104] 7. Drones. Detailed Implementation

[0105] To make the objectives, technical solutions, and advantages of this utility model clearer, the embodiments of this utility model will be described in further detail below with reference to the accompanying drawings.

[0106] First, the overall structure of the chemical fuel multi-stage propulsion electromagnetic hybrid catapult device provided in this embodiment will be introduced.

[0107] like Figures 1-3As shown, the chemical fuel multi-stage propulsion electromagnetic hybrid catapult device provided in this embodiment includes a base 1, a movable base 2, an electromagnetic propulsion component 3, and a steam propulsion component 4.

[0108] Specifically, the movable base 2 is disposed opposite to the base 1 on one side along its thickness direction and is slidably connected to the base 1 along its length direction. The movable base 2 is used to mount the drone 7. When the drone 7 is mounted on the movable base 2, the movable base 2 can be driven to move along the length direction of the base 1 by the electromagnetic propulsion component 3 and the steam propulsion component 4, thereby driving the drone 7 to move along the length direction of the base 1.

[0109] More specifically, the electromagnetic propulsion assembly 3 includes a first stator 30 and a second stator 31 fixedly mounted on one side of the base 1 along its thickness direction, and a mover 32 fixedly mounted on the side of the movable base 2 near the base 1. The first stator 30 includes a plurality of first magnetic elements 300 arranged side by side along the length direction of the base 1, the second stator 31 includes a plurality of second magnetic elements 310 arranged side by side along the length direction of the base 1, and the mover 32 includes a mover coil 320. In the width direction of the base 1, the plurality of first magnetic elements 300 and the plurality of second magnetic elements 310 are positioned opposite each other. The mover 32 is positioned between the first stator 30 and the second stator 31, with both sides of the mover 32 in contact with and electrically connected to the first stator 30 and the second stator 31, respectively, to transmit current to the mover coil 320 of the mover 32 through the first stator 30 and the second stator 31. When the movable base 2 needs to move, the energized mover coil 320 interacts with multiple first magnetic elements 300 and multiple second magnetic elements 310, jointly driving the mover 32 and the movable base 2 mounted on the mover 32 to translate relative to the base 1 along the length direction of the base 1. It should be understood that the number of multiple first magnetic elements 300 and multiple second magnetic elements 310 can be 8, 10, 16, etc., and this embodiment is not limited to a single one.

[0110] More specifically, the steam propulsion assembly 4 is fixedly installed on the side of the movable base 2 away from the base 1, and the steam propulsion assembly 4 is used to drive the movable base 2 to move relative to the base 1 along the length direction of the base 1.

[0111] Furthermore, the operating principle of this chemical fuel multi-stage propulsion electromagnetic hybrid catapult device is as follows: When this chemical fuel multi-stage propulsion electromagnetic hybrid catapult device launches the UAV 7, the UAV 7 is mounted on the moving seat 2, and then the steam propulsion component 4 and the electromagnetic propulsion component 3 are activated simultaneously. At this time, current is transmitted to the mover coil 320 of the mover 32 through the first stator 30 and the second stator 31. Then, the mover coil 320, which is in the energized state, generates Lorentz force through the interaction of multiple first magnetic elements 300 and multiple second magnetic elements 310, thereby causing the mover coil 320 to receive linear thrust, which in turn drives the mover 32 and the moving seat 2 mounted on the mover 32 to translate relative to the base 1 along the length direction of the base 1. At the same time, the steam propulsion component 4 drives the moving seat 2 to translate along the length direction of the base 1. When the moving seat 2 moves to the designated position, the moving seat 2 is blocked, and then the UAV 7 separates from the moving seat 2 under the action of inertial force, thereby realizing catapult take-off.

[0112] Therefore, it can be seen that when this chemical fuel multi-stage propulsion electromagnetic hybrid catapult launches the UAV 7, the steam propulsion component 4 and the electromagnetic propulsion component 3 jointly drive the moving seat 2 to move along the length of the base 1. The UAV 7 takes off through two power sources. Under the premise of adapting to and meeting the takeoff speed of small and medium-sized UAVs 7, since two power sources are set, it is not necessary to design the power of the steam propulsion component 4 and the electromagnetic propulsion component 3 to be large. Therefore, the steam propulsion component 4 and the electromagnetic propulsion component 3 can be miniaturized. The moving seat 2 is driven by the superposition of the power applied by the steam propulsion component 4 and the electromagnetic propulsion component 3. This reduces the volume of this chemical fuel multi-stage propulsion electromagnetic hybrid catapult launcher and the energy consumption of the electromagnetic propulsion component 3 during use. This makes this chemical fuel multi-stage propulsion electromagnetic hybrid catapult launcher have the advantages of compact structure and small equipment size.

[0113] Furthermore, since the steam propulsion component 4 is fixedly installed on the side of the moving base 2 away from the base 1, and the steam propulsion component 4 is integrated on the moving base 2, after miniaturizing the steam propulsion component 4 and the electromagnetic propulsion component 3, the steam propulsion component 4 does not occupy the installation position of the electromagnetic propulsion component 3. Moreover, since the steam propulsion component 4 applies additional force to drive the moving base 2 to move, it is not necessary to set the length of the base 1 to be too long to meet the acceleration distance of the electromagnetic propulsion component 3. This also achieves the miniaturization design of the base 1, further making the structure of this chemical fuel multi-stage propulsion electromagnetic hybrid catapult device more compact.

[0114] The following explains how the movable seat 2 moves on the base 1 and how the movable seat 2 is set up.

[0115] In one implementation, such as Figures 1-3 ,as well as Figure 6 The base 1 shown has a pair of guide portions 10 on one side along its thickness direction. The pair of guide portions 10 extend along the length direction of the base 1 and are spaced apart from each other in the width direction of the base 1. The first stator 30 and the second stator 31 are located between the pair of guide portions 10.

[0116] The movable seat 2 includes a slide plate 20 and a connecting frame 21 fixedly installed on the side of the slide plate 20 away from the base 1. The side of the slide plate 20 close to the base 1 is provided with a pair of guided parts 22 corresponding to a pair of guide parts 10. The pair of guided parts 22 are slidably connected to the pair of guide parts 10 so that the movable seat 2 is slidably connected to the base 1 along the length direction of the base 1. Thus, the slide plate 20 is guided by the pair of guide parts 10 during movement, thereby achieving the purpose of the movable seat 2 being able to reliably move along the length direction of the base 1.

[0117] Specifically, a pair of connecting protrusions 23 are provided at the end of the connecting frame 21 away from the base 1, and the pair of connecting protrusions 23 are used to engage the landing gear of the drone 7, so that the drone 7 will not fall off the connecting frame 21 when it is moved by the moving seat 2.

[0118] More specifically, the structure and arrangement of the guide part 10 and the guided part 22 are not limited, and the following is an example.

[0119] In one embodiment, a pair of guide portions 10 are configured as a pair of guide rails extending along the length direction of the base 1, and a pair of guided portions 22 are configured as a pair of guide grooves extending along the length direction of the base 1 on the side of the slide plate 20 near the base 1 and adapted to the pair of guide rails. Each guide groove is slidably connected to the corresponding guide rail, thereby enabling the slide plate 20 to be slidably connected to the base 1.

[0120] In another embodiment, a pair of guide portions 10 are configured as a pair of slide grooves extending along the length direction of the base 1, and a pair of guided portions 22 are configured as a pair of sliders 603 extending along the length direction of the base 1 on the side of the slide plate 20 near the base 1 and adapted to the pair of slide grooves. Each slide groove is slidably connected to the corresponding slider 603, thereby making the slide plate 20 slidably connected to the base 1.

[0121] Furthermore, in order to enable the UAV 7 to be launched and take off by inertia after the moving seat 2 has moved to a certain distance during takeoff, in one embodiment, each guide part 10 is provided with a baffle 11 at both ends in its length direction, and each baffle 11 is erected at the corresponding end of the guide part 10, so that when the UAV 7 is moved to the end of the guide part 10 by the moving seat 2, the baffle 11 blocks the moving seat 2, and at this time the UAV 7 takes off under the action of inertia.

[0122] In addition, each baffle 11 is also provided with a hydraulic buffer 12. One end of the hydraulic buffer 12 is fixedly installed on the side of the baffle 11 near the moving seat 2, and the other end extends towards the moving seat 2 along the length of the base 1. This allows the moving seat 2 to be buffered and decelerated when it moves to the baffle 11, thus reducing the risk of damage to the moving seat 2.

[0123] The structure and configuration of the electromagnetic propulsion device will be further explained below.

[0124] First, the structure and arrangement of the first stator 30 and the second stator 31 will be explained.

[0125] In one implementation, such as Figures 2-4 The first stator 30 shown also includes a first mounting plate 301 and a plurality of first electrical connecting pieces 302. The first mounting plate 301 is vertically fixed to one side of the base 1. The plurality of first electrical connecting pieces 302 are arranged side by side on the first mounting plate 301 along the length direction of the base 1. The plurality of first magnetic elements 300 are arranged side by side on the first mounting plate 301 along the length direction of the base 1.

[0126] Specifically, the second stator 31 also includes a second mounting plate 312 and a plurality of second electrical connecting pieces 313. The second mounting plate 312 is vertically fixed to one side of the base 1. The plurality of second electrical connecting pieces 313 are arranged side by side on the second mounting plate 312 along the length direction of the base 1. The plurality of second magnetic elements 310 are arranged side by side on the second mounting plate 312 along the length direction of the base 1.

[0127] More specifically, in the thickness direction of the base 1, a plurality of first electrical connecting pieces 302 are spaced apart from a plurality of first magnetic elements 300, and a plurality of second electrical connecting pieces 313 are spaced apart from a plurality of second magnetic elements 310. In the width direction of the base 1, a first mounting plate 301 and a second mounting plate 312 are spaced apart relative to each other, and a plurality of first electrical connecting pieces 302 and a plurality of second electrical connecting pieces 313 are spaced apart relative to each other. When the mover 32 and the movable seat 2 move along the length direction of the base 1, the two sides of the mover 32 sequentially contact and are electrically connected with their respective first electrical connecting pieces 302 and second electrical connecting pieces 313, so as to transmit current to the mover coil 320 of the mover 32 through the corresponding first electrical connecting pieces 302 and second electrical connecting pieces 313.

[0128] More specifically, since the mover 32 is located between the first stator 30 and the second stator 31, by setting the first mounting plate 301 and the second mounting plate 312, after multiple first magnetic elements 300 are arranged side by side on the first mounting plate 301 and multiple second magnetic elements 310 are arranged side by side on the second mounting plate 312, when the mover coil 320 drives the mover 32 to move together with the interaction of the multiple first magnetic elements 300 and the multiple second magnetic elements 310, the first mounting plate 301 and the second mounting plate 312 can limit the mover 32 in the width direction of the base 1, thereby avoiding the risk of the mover 32 shifting its position during movement.

[0129] Furthermore, since the first mounting plate 301 and the second mounting plate 312 can limit the movement of the mover 32 in the width direction of the base 1, when the mover 32 and the moving seat 2 move along the length direction of the base 1, the two sides of the mover 32 can reliably contact and connect with their respective first electrical connecting piece 302 and second electrical connecting piece 313 in sequence, thus achieving the purpose of reliably moving the mover 32.

[0130] More specifically, the structure and arrangement of the first magnetic component 300 and the second magnetic component 310 are not limited. For example, they can be permanent magnet blocks, permanent magnet strips, permanent magnet sheets, etc. This embodiment does not limit them to a single type.

[0131] Furthermore, it should be noted that the polarities of two adjacent first magnetic elements 300 are opposite, and the polarities of two adjacent second magnetic elements 310 are opposite. Moreover, the multiple first magnetic elements 300 and the multiple second magnetic elements 310 are directly opposite to each other and correspond one-to-one. The polarities of one first magnetic element 300 and one second magnetic element 310 that are directly opposite to each other are opposite. Thus, when the multiple first electrical connecting pieces 302 and the multiple electrical connecting pieces 313 are energized, a magnetic field is generated, forming a Lorentz force. This causes the mover coil 320 to move due to the pushing and pulling forces of the multiple first magnetic elements 300 and the multiple second magnetic elements 310.

[0132] Furthermore, the structure and arrangement of the mover 32 will be explained in more detail below.

[0133] In one embodiment, the mover 32 further includes a coil box 321, a first brush 322, and a second brush 323. The coil box 321 is fixedly installed on the side of the movable base 2 near the base 1. In the width direction of the base 1, the first brush 322 and the second brush 323 are respectively fixedly installed on both sides of the coil box 321. The inside of the coil box 321 has a receiving space, and the mover coil 320 is fixedly installed in the receiving space. Thus, the mover coil 320 can be limited by the coil box 321, thereby avoiding the risk of the mover coil 320 becoming loose during movement.

[0134] Specifically, the first brush 322 and the second brush 323 are electrically connected to the moving coil 320, respectively. When the moving part 32 and the moving base 2 move along the length of the base 1, the first brush 322 and the second brush 323 sequentially contact and connect with their respective first electrical connecting piece 302 and second electrical connecting piece 313, so that the corresponding first electrical connecting piece 302 and second electrical connecting piece 313 transmit current to the moving coil 320 through the first brush 322 and the second brush 323.

[0135] More specifically, when the mover 32 moves along the length of the base 1, the first brush 322 and the second brush 323 sequentially contact and connect with their respective first electrical connecting piece 302 and second electrical connecting piece 313. Since the contact area of ​​the brushes is large when they are connected, the first brush 322 can reliably connect with the first electrical connecting piece 302 and the second brush 323 can reliably connect with the second electrical connecting piece 313 when the mover 32 moves along the length of the base 1, thereby enabling the mover 32 to move reliably along the length of the base 1.

[0136] Furthermore, the structure and arrangement of the steam propulsion assembly 4 will be explained in more detail below.

[0137] Specifically, such as Figure 7 As shown, the steam propulsion assembly 4 includes a first propulsion component 40, a first impact component 41, a second propulsion component 42, a second impact component 43 and a third propulsion component 44, which are arranged sequentially along the length of the base 1 and fixedly installed on the side of the movable seat 2 away from the base 1.

[0138] Specifically, one end of the first impact component 41 is fixedly connected to one end of the first propulsion component 40, and the other end is fixedly connected to one end of the second propulsion component 42. One end of the second impact component 43 is fixedly connected to the other end of the second propulsion component 42, and the other end is fixedly connected to one end of the third propulsion component 44.

[0139] More specifically, when the steam propulsion assembly 4 drives the mobile seat 2 to move along the length of the base 1, the third propulsion component 44 is activated to perform a first jet boost; then the third propulsion component 44 drives the second impact component 43, and the second impact component 43 activates the second propulsion component 42 to perform a second jet boost; then the second propulsion component 42 drives the first impact component 41, and the first impact component 41 activates the first propulsion component 40 to perform a third jet boost, so that the steam propulsion assembly 4 continuously provides power to the mobile seat 2 during the movement, thereby enabling the UAV 7 to take off reliably.

[0140] More specifically, the first propulsion component 40 is fixedly connected to the side of the movable seat 2 away from the base 1 via the first connecting seat 406, the second propulsion component 42 is fixedly connected to the side of the movable seat 2 away from the base 1 via the second connecting seat 426, and the third propulsion component 44 is fixedly connected to the side of the movable seat 2 away from the base 1 via the third connecting seat 446, thereby ensuring that the first propulsion component 40, the second propulsion component 42, and the third propulsion component 44 are reliably fixed on the movable seat 2.

[0141] More specifically, the structure and arrangement of the first propulsion component 40, the first impact component 41, the second propulsion component 42, the second impact component 43 and the third propulsion component 44 are not limited, and examples are given below.

[0142] In one implementation, such as Figures 8-11 As shown, the first propulsion component 40 includes a first fuel tank 400 with a first cavity inside, a first ignition component and a first explosive component 401. The first fuel tank 400 is closed at both ends, and a first connection hole is provided on one end wall of the first fuel tank 400. The first ignition component is fixedly installed in the first connection hole, and the first explosive component 401 is installed on the circumferential side wall of the first fuel tank 400.

[0143] like Figure 8 , Figure 16 , Figure 17 As shown, the second propulsion component 42 includes a second fuel tank 420 with a second cavity inside, a second ignition component and a second explosive component 421. One end of the second fuel tank 420 is open and the other end is closed. A second connection hole is provided on the end wall of the other end of the second fuel tank 420. The second ignition component is fixedly installed in the second connection hole, and the second explosive component 421 is installed on the circumferential side wall of the second fuel tank 420.

[0144] like Figure 8 , Figure 18 , Figure 19As shown, the third propulsion component 44 includes a third fuel tank 440 with a third cavity inside, a third ignition component, and a third explosive component 441. One end of the third fuel tank 440 is open and the other end is closed. A third connection hole is provided on the end wall of the other end of the third fuel tank 440. The third ignition component is fixedly installed in the third connection hole, and the third explosive component 441 is installed on the circumferential side wall of the third fuel tank 440.

[0145] like Figure 8 ,as well as Figures 12-15 As shown, the first impact component 41 includes a first sealing flange 410 and a first impact member 411. One end of the first sealing flange 410 is fixedly connected to one end peripheral wall of the first fuel tank 400, and the other end is fixedly connected to one end peripheral wall of the second fuel tank 420. The first impact member 411 is movably installed at the center of the first sealing flange 410 along the length direction of the base 1, and the first impact member 411 and the first ignition member are directly opposite each other in the length direction of the base 1.

[0146] It should be noted that the fixing method for one end of the first sealing flange 410 to be fixedly connected to one end peripheral wall of the first fuel tank 400 and the other end to be fixedly connected to one end peripheral wall of the second fuel tank 420 can be screwing, welding, etc., which is not limited in this embodiment. For example, an internal thread is provided on one end wall of the first fuel tank 400, and an external thread is provided on the outer peripheral wall of one end of the first sealing flange 410. Then, the external thread on the outer peripheral wall of one end of the first sealing flange 410 is threadedly connected to the internal thread on the outer peripheral wall of one end of the first fuel tank 400, so that one end of the first sealing flange 410 is fixedly connected to one end peripheral wall of the first fuel tank 400. Similarly, an internal thread is provided on one end wall of the second fuel tank 420, and an external thread is provided on the outer peripheral wall of the other end of the first sealing flange 410. Then, the external thread on the outer peripheral wall of the other end of the first sealing flange 410 is threadedly connected to the internal thread on the outer peripheral wall of one end of the second fuel tank 420, so that the other end of the first sealing flange 410 is fixedly connected to one end peripheral wall of the second fuel tank 420.

[0147] The second impact component 43 includes a second sealing flange 430 and a second impact member 431. One end of the second sealing flange 430 is fixedly connected to the peripheral wall of the other end of the second fuel tank 420, and the other end is fixedly connected to the peripheral wall of the third fuel tank 440. The second impact member 431 is movably installed at the center of the second sealing flange 430 along the length direction of the base 1, and the second impact member 431 and the second ignition member are directly opposite each other in the length direction of the base 1.

[0148] It should be noted that the fixing method for one end of the second sealing flange 430 to be fixedly connected to the peripheral wall of the other end of the second fuel tank 420 and the other end to be fixedly connected to the peripheral wall of the third fuel tank 440 is not limited. For example, it can be screwed, welded, etc., and this embodiment does not limit it to a single method. For example, an internal thread is provided on the end wall of one end of the second fuel tank 420, and an external thread is provided on the outer peripheral wall of one end of the second sealing flange 430, so that the external thread on the outer peripheral wall of one end of the second sealing flange 430 is connected to the end wall of the second fuel tank 420. The internal threaded port on the wall is threaded to fix one end of the second sealing flange 430 to one end of the peripheral wall of the second fuel tank 420. Similarly, an internal threaded port is provided on one end wall of the third fuel tank 440, and an external thread is provided on the outer peripheral wall of the other end of the second sealing flange 430. The external thread on the outer peripheral wall of the other end of the second sealing flange 430 is then threaded to the internal threaded port on one end wall of the third fuel tank 440, so that the other end of the second sealing flange 430 is fixedly connected to one end of the peripheral wall of the third fuel tank 440.

[0149] More specifically, when the steam propulsion assembly 4 drives the mobile base 2 to move, the high-pressure steam in the third fuel tank 440 is ignited by the third ignition component, causing the third explosive component 441 to eject gas for the first jet boost. Simultaneously, the high-pressure steam in the third fuel tank 440 drives the second impact component 431 to move along the length of the base 1 toward the second ignition component, and then impacts the second ignition component, thereby causing the second ignition component to ignite the high-pressure steam in the second fuel tank 420, causing the second explosive component 421 to eject gas for the second jet boost. At the same time, the high-pressure steam in the second fuel tank 420 drives the first impact component 411 to move along the length of the base 1 toward the second ignition component, and then impacts the first ignition component, thereby causing the first ignition component to ignite the high-pressure steam in the first fuel tank 400, causing the first explosive component 401 to eject gas for the third jet boost. In this process, only the high-pressure steam in the third fuel tank 440 needs to be ignited by the third ignition component to achieve three jet boosts, so that when the steam propulsion assembly 4 drives the mobile base 2 to move, it continuously provides power to the mobile base 2, thereby making the takeoff speed of the UAV 7 faster.

[0150] In addition, such as Figure 8 As shown, a first steam inlet 405 is provided on the peripheral wall of the first fuel tank 400, a second steam inlet 425 is provided on the peripheral wall of the second fuel tank 420, and a third steam inlet 445 is provided on the peripheral wall of the third fuel tank 440. High-pressure steam can be quickly injected into the first fuel tank 400, the second fuel tank 420, and the third fuel tank 440 respectively through the first steam inlet 405, the second steam inlet 425, and the third steam inlet 445 to prepare for the takeoff of the UAV 7.

[0151] More specifically, such as Figure 1 As shown, along the length of the base 1, a pair of first buffer rings 418 are fitted at both ends of the first sealing flange 410, and a pair of second buffer rings are fitted at both ends of the second sealing flange 430, thereby achieving the function of sealing and vibration reduction.

[0152] More specifically, the structure and arrangement of the first explosive component 401, the first ignition component, the second explosive component 421, the second ignition component, the third explosive component 441, and the third ignition component are not limited, and examples are given below.

[0153] In one implementation, such as Figures 8-11 As shown, the first explosive component 401 includes at least one pair of first pressure relief pipes 403 fixedly installed on the circumferential side wall of the first fuel tank 400. Each pair of first pressure relief pipes 403 is arranged opposite to each other in the radial direction of the first fuel tank 400. One end of each first pressure relief pipe 403 is connected to the first fuel tank 400, and the other end extends away from the first fuel tank 400 and is parallel to the first fuel tank 400. A first explosion valve 404 is provided at the other end of each first pressure relief pipe 403. The first ignition component includes a first piezoelectric ceramic 402, which is fixedly installed in a first connecting hole. The discharge electrode of the first piezoelectric ceramic 402 extends through the first connecting hole into a first cavity. The first connecting hole is located at the center of one end wall of the first fuel tank 400. It should be understood that the number of first pressure relief pipes 403 can be 1 pair, 2 pairs, 3 pairs, etc., and this embodiment does not limit this.

[0154] Specifically, such as Figure 8 , Figure 16 , Figure 17 As shown, the second explosive component 421 includes at least one pair of second pressure relief pipes 423 fixedly installed on the circumferential side wall of the first fuel tank 400. Each pair of second pressure relief pipes 423 is arranged opposite to each other in the radial direction of the second fuel tank 420. One end of each second pressure relief pipe 423 is connected to the second fuel tank 420, and the other end extends away from the closed end of the first fuel tank 400 and is parallel to the second fuel tank 420. A second explosive valve 424 is provided at the other end of each second pressure relief pipe 423. The second ignition component includes a second piezoelectric ceramic 422, which is fixedly installed in a second connecting hole. The discharge electrode of the second piezoelectric ceramic 422 extends through the second connecting hole into the second cavity. The second connecting hole is located at the center of one end wall of the second fuel tank 420. It should be understood that the number of second pressure relief pipes 423 can be 1 pair, 2 pairs, 3 pairs, etc., and this embodiment does not limit this.

[0155] More specifically, such as Figure 8 , Figure 18, Figure 19 As shown, the third explosive component 441 includes at least one pair of third pressure relief pipes 443 fixedly installed on the circumferential side wall of the third fuel tank 440. Each pair of third pressure relief pipes 443 is arranged opposite to each other in the radial direction of the third fuel tank 440. One end of each third pressure relief pipe 443 is connected to the third fuel tank 440, and the other end extends away from the closed end of the first fuel tank 400 and is parallel to the third fuel tank 440. A third explosive valve 444 is provided at the other end of each third pressure relief pipe 443. The third ignition component includes an electric shock device 442, which is fixedly installed in a third connecting hole. The discharge electrode of the electric shock device 442 extends through the third connecting hole into the third cavity. The third connecting hole is located at the center of one end wall of the third fuel tank 440. It should be understood that the number of third pressure relief pipes 443 can be 1 pair, 2 pairs, 3 pairs, etc., and this embodiment does not limit this.

[0156] More specifically, during the first jet boost, the discharge electrode of the stun gun 442 ignites the high-pressure steam in the third fuel tank 440, thereby releasing pressure through the high-pressure steam and causing the third explosion valve 444 to explode. The high-pressure steam then exits from the other end of the third pressure relief pipe 443, thus achieving the first jet boost. During the second jet boost, the discharge electrode of the second piezoelectric ceramic 422 ignites the high-pressure steam in the second fuel tank 420, thereby releasing pressure through the high-pressure steam and causing the second explosion valve 424 to explode. The high-pressure steam then exits from the other end of the second pressure relief pipe 423, thus achieving the second jet boost. During the third jet boost, the discharge electrode of the first piezoelectric ceramic 402 ignites the high-pressure steam in the first fuel tank 400, thereby releasing pressure through the high-pressure steam and causing the first explosion valve 404 to explode. The high-pressure steam then exits from the other end of the first pressure relief pipe 403, thus achieving the third jet boost. This ensures that when the steam propulsion assembly 4 drives the mobile seat 2, it continuously provides power to the mobile seat 2, guaranteeing the takeoff speed of the UAV 7.

[0157] Furthermore, after the UAV 7 has taken off, by quickly replacing the valve plate of the first explosion valve 404 at the other end of the first pressure relief pipe 403, replacing the valve plate of the second explosion valve 424 at the other end of the second pressure relief pipe 423, and replacing the valve plate of the third explosion valve 444 at the other end of the third pressure relief pipe 443; and then quickly filling the first fuel tank 400, the second fuel tank 420, and the third fuel tank 440 with high-pressure steam through the first steam interface 405, the second steam interface 425, and the third steam interface 445 respectively, high-pressure steam can be injected into the first fuel tank 400, the second fuel tank 420, and the third fuel tank 440 to prepare for the next takeoff of the UAV 7.

[0158] Furthermore, the structure and arrangement of the first impact member 411 and the second impact member 431 are not limited, and examples are given below.

[0159] In one implementation, such as Figures 12-15 As shown, the first impact component 41 further includes a first cover plate 412, which is fixedly installed at the other end of the first sealing flange 410. The center of the first sealing flange 410 has a first channel 413 with openings at both ends along the length of the base 1. The first cover plate 412 covers the opening at one end of the first channel 413, and its center has a first through-hole 416 communicating with the first channel 413. The first impact component 411 includes a first impact block 414 movably installed within the first channel 413, and a plurality of first telescopic springs 415. One end of each first telescopic spring 415 is fixedly connected to a corresponding side of the first impact block 414, and the other end extends along the length of the base 1 and is fixedly connected to the first cover plate 412. It should be understood that the number of the plurality of first telescopic springs 415 can be 2, 3, 5, etc., and this embodiment does not limit this number.

[0160] Specifically, such as Figure 8 and Figure 17 As shown, the second impact component 43 further includes a second cover plate 432, which is fixedly installed at the other end of the second sealing flange 430. The center of the second sealing flange 430 has a second channel 433 with openings at both ends along the length of the base 1. The second cover plate 432 covers the opening at one end of the second channel 433, and its center has a second through-hole 436 communicating with the second channel 433. The second impact component 431 includes a second impact block 434 movably installed within the second channel 433, and a plurality of second telescopic springs 435. One end of each second telescopic spring 435 is fixedly connected to a corresponding side of the second impact block 434, and the other end extends along the length of the base 1 and is fixedly connected to the second cover plate 432. It should be understood that the number of the plurality of second telescopic springs 435 can be 2, 3, 5, etc., and this embodiment does not limit this number.

[0161] More specifically, when the steam propulsion assembly 4 is working, the high-pressure steam in the third fuel tank 440 is ignited by the discharge electrode of the stun gun 442, causing the valve plate of the third explosion valve 444 to explode for the first jet boost. At this time, the pressure is released by the high-pressure steam in the third fuel tank 440, causing the second impact block 434 to move rapidly along the length of the base 1, thereby impacting the second piezoelectric ceramic 422. The discharge electrode of the second piezoelectric ceramic 422 ignites the high-pressure steam in the second fuel tank 420, which in turn causes the valve plate of the second explosion valve 424 to explode for the second jet boost. Then, the pressure is released by the high-pressure steam in the second fuel tank 420, causing the first impact block 414 to move rapidly along the length of the base 1, thereby impacting the second piezoelectric ceramic 422. The discharge electrode of the first piezoelectric ceramic 402 ignites the high-pressure steam in the first fuel tank 400, which in turn causes the valve plate of the second explosion valve 424 to explode for the third jet boost. In this process, the three jet boosts of high-pressure steam are completed sequentially and quickly connected, ensuring that the mobile base 2 has sufficient power so that the UAV 7 can take off reliably.

[0162] Furthermore, when the first impact block 414 moves to impact the first piezoelectric ceramic 402, multiple first telescopic springs 415 are stretched, and when the second impact block 434 moves to impact the second piezoelectric ceramic 422, multiple second telescopic springs 435 are stretched. After the impact is completed, the first impact block 414 can be quickly reset by pulling it with multiple first telescopic springs 415, and the second impact block 434 can be quickly reset by pulling it with multiple second telescopic springs 435.

[0163] Furthermore, in one implementation, such as Figure 15 As shown, in the radial direction of the first channel 413, a pair of first balls 417 opposite to each other are provided at both ends of the first impact block 414; in the radial direction of the second channel 433, a pair of second balls opposite to each other are provided at both ends of the second impact block 434; thereby reducing the frictional force when the first impact block 414 and the second impact block 434 move.

[0164] Furthermore, since the drone 7 is affected by the surrounding environment during takeoff, such as obstacles in front, it is necessary to adjust the launch angle of the drone 7. Therefore, in one embodiment, such as Figure 20 and Figure 21 As shown, this chemical fuel multi-stage propulsion electromagnetic hybrid catapult also includes a launch support 5 and a position adjustment component 6. The launch support 5 can stably support the drone 7, and the position adjustment component 6 can adjust the launch angle of the drone 7 to avoid obstruction by obstacles.

[0165] Specifically, the launch bracket 5 includes a bracket body 50 and a support plate 51 fixedly installed on the top of the bracket body 50. In the length direction of the support plate 51, one end of the base 1 is rotatably connected to one end of the support plate 51. The position adjustment assembly 6 includes a drive component 60 and a transmission component 61. The drive component 60 is installed on the other end of the support plate 51 near the base 1. One end of the transmission component 61 is drively connected to the drive end of the drive component 60, and the other end is drively connected to the other side of the base 1.

[0166] More specifically, when it is necessary to adjust the launch angle of the UAV 7, the drive component 60 can drive the transmission component 61 to swing, thereby causing the base 1 to swing around one end, changing the position of the other end of the base 1 in the height direction of the launch bracket 5, thereby achieving the purpose of adjusting the launch angle of the UAV 7, so that the UAV 7 can adapt to different launch environments.

[0167] More specifically, the structure and arrangement of the drive component 60 and the transmission component 61 are not limited, and the following is an example.

[0168] In one implementation, such as Figure 21 As shown, the drive component 60 includes a mounting bracket 600, a screw 601, a drive handwheel 602, and a slider 603. The mounting bracket 600 is fixedly mounted on the other end of the support plate 51 near the base 1. The screw 601 extends along the length of the support plate 51 and is rotatably connected to the mounting bracket 600 at both ends. The drive handwheel 602 is fixed to one end of the screw 601, and the slider 603 is threadedly connected to the screw 601.

[0169] Specifically, the transmission component 61 includes a pair of transmission rods 610 that correspond one-to-one with the two ends of the slider 603 in the width direction of the support plate 51. One end of each transmission rod 610 is rotatably connected to the corresponding end of the slider 603, and the other end extends to be rotatably connected to the other end of the base 1.

[0170] More specifically, when it is necessary to adjust the launch angle of the drone 7, the drive handwheel 602 is rotated, which causes the screw 601 to rotate. At this time, the slider 603 moves along the length of the base 1, thereby linking a pair of transmission rods 610 to gradually lift the base 1 or lower the other end of the base 1, ultimately achieving the purpose of adjusting the launch angle of the drone 7. During this process, since the slider 603 is threadedly connected to the screw 601, after the angle of the base 1 is adjusted, the position of the base 1 can be limited by the slider 603, thereby avoiding the risk of the base 1 shifting due to the gravity of the drone 7 when it is launched.

[0171] More specifically, the support plate 51 is also provided with a clearance opening 52, so that when the base 1 is in contact with the support plate 51, the clearance opening 52 can avoid the position adjustment component 6.

[0172] Furthermore, such as Figure 22 and Figure 23 As shown, one end of the base 1 is also provided with a pair of connecting rings 14 spaced apart along its length. By setting a rotating shaft on the support plate 51 and having the rotating shaft pass through the inner holes of the pair of connecting rings 14, the base 1 can be rotatably connected to the support plate 51. Of course, the rotatable connection between the base 1 and the support plate 51 can also be other configuration methods, such as setting a rotating bearing, hinge, etc., which are not limited in this embodiment.

[0173] In addition, a groove 13 is provided on the base 1 to reduce the weight of the base 1, making this chemical fuel multi-stage propulsion electromagnetic hybrid catapult device lighter. At the same time, the groove 13 can be used to observe whether the first brush 322 and the first electrical connection piece 302, and the second brush 323 and the second electrical connection piece 313 are in good contact.

[0174] The above description illustrates the implementation of this utility model through specific embodiments. Those skilled in the art can easily understand other advantages and effects of this utility model from the content disclosed in this specification. Although the description of this utility model is presented in conjunction with preferred embodiments, this does not mean that the features of this utility model are limited to this embodiment. On the contrary, the purpose of describing the utility model in conjunction with the embodiments is to cover other options or modifications that may be derived based on the claims of this utility model. To provide a deep understanding of this utility model, many specific details will be included in the following description. This utility model may also be implemented without using these details. Furthermore, to avoid confusion or obscuring the focus of this utility model, some specific details will be omitted in the description. It should be noted that, unless otherwise specified, the embodiments and features in the embodiments of this utility model can be combined with each other.

[0175] It should be noted that in this specification, similar reference numerals and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0176] In the description of this embodiment, it should be noted that the terms "upper", "lower", "inner", "bottom", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship that the utility model product is usually placed in during use. They are only for the convenience of describing the utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the utility model.

[0177] The terms “first”, “second”, etc., are used only to distinguish descriptions and should not be interpreted as indicating or implying relative importance.

[0178] In the description of this embodiment, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set up," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this embodiment based on the specific circumstances.

Claims

1. A multi-stage propulsion electromagnetic hybrid catapult device using chemical fuels, characterized in that, include: Base; A movable base is disposed opposite to the base on one side along its thickness direction and is slidably connected to the base along its length direction, and the movable base is used to mount a drone; An electromagnetic propulsion assembly includes a first stator and a second stator fixedly mounted on one side of a base along its thickness direction, and a mover fixedly mounted on the side of a movable base near the base. The first stator includes a plurality of first magnetic elements arranged side-by-side along the length direction of the base, and the second stator includes a plurality of second magnetic elements arranged side-by-side along the length direction of the base. The mover includes a mover coil. In the width direction of the base, the plurality of first magnetic elements and the plurality of second magnetic elements are spaced apart from each other. The mover is located between the first stator and the second stator, and both sides of the mover are in contact with and electrically connected to the first stator and the second stator, respectively, to transmit current to the mover coil of the mover through the first stator and the second stator. Through the interaction between the energized mover coil and the plurality of first magnetic elements and the plurality of second magnetic elements, the mover and the movable base mounted on the mover are driven to translate relative to the base along the length direction of the base. A steam propulsion assembly is fixedly installed on the side of the movable base away from the base, and the steam propulsion assembly is used to drive the movable base to move relative to the base along the length direction of the base.

2. The chemical fuel multi-stage propulsion electromagnetic hybrid catapult device as described in claim 1, characterized in that, The steam propulsion assembly includes a first propulsion component, a first impact component, a second propulsion component, a second impact component, and a third propulsion component, which are sequentially arranged and fixedly installed on the side of the movable seat away from the base along the length direction of the base. One end of the first impact component is fixedly connected to one end of the first propulsion component, and the other end is fixedly connected to one end of the second propulsion component. One end of the second impact component is fixedly connected to the other end of the second propulsion component, and the other end is fixedly connected to one end of the third propulsion component.

3. The chemical fuel multi-stage propulsion electromagnetic hybrid catapult device as described in claim 2, characterized in that, The first propulsion component includes a first fuel tank with a first cavity inside, a first ignition component and a first explosive component. The two ends of the first fuel tank are closed, and a first connection hole is provided on one end wall of the first fuel tank. The first ignition component is fixedly installed in the first connection hole, and the first explosive component is installed on the circumferential side wall of the first fuel tank. The second propulsion component includes a second fuel tank with a second cavity inside, a second ignition component and a second explosive component. One end of the second fuel tank is open and the other end is closed. A second connection hole is provided on the end wall of the other end of the second fuel tank. The second ignition component is fixedly installed in the second connection hole, and the second explosive component is installed on the circumferential side wall of the second fuel tank. The third propulsion component includes a third fuel tank with a third cavity inside, a third ignition component and a third explosive component. One end of the third fuel tank is open and the other end is closed. A third connection hole is provided on the end wall of the other end of the third fuel tank. The third ignition component is fixedly installed in the third connection hole. The third explosive component is installed on the circumferential side wall of the third fuel tank. The first impact component includes a first sealing flange and a first impact member. One end of the first sealing flange is fixedly connected to one end of the peripheral wall of the first fuel tank, and the other end is fixedly connected to one end of the peripheral wall of the second fuel tank. The first impact member is movably installed at the center of the first sealing flange along the length direction of the base, and the first impact member and the first ignition member are directly opposite each other in the length direction of the base. The second impact component includes a second sealing flange and a second impact member. One end of the second sealing flange is fixedly connected to the peripheral wall of the other end of the second fuel tank, and the other end is fixedly connected to the peripheral wall of the third fuel tank. The second impact member is movably installed at the center of the second sealing flange along the length direction of the base, and the second impact member and the second ignition member are directly opposite each other along the length direction of the base.

4. The chemical fuel multi-stage propulsion electromagnetic hybrid catapult device as described in claim 3, characterized in that, The first fuel tank is provided with a first steam port on its peripheral sidewall, the second fuel tank is provided with a second steam port on its peripheral sidewall, and the third fuel tank is provided with a third steam port on its peripheral sidewall. The first explosive component includes at least one pair of first pressure relief pipes fixedly installed on the circumferential side wall of the first fuel tank. Each pair of first pressure relief pipes is arranged opposite to each other in the radial direction of the first fuel tank. One end of each first pressure relief pipe is connected to the first fuel tank, and the other end extends away from the first fuel tank and is parallel to the first fuel tank. A first explosive valve is provided at the other end of each first pressure relief pipe. The first ignition component includes a first piezoelectric ceramic, which is fixedly installed in the first connecting hole. The discharge electrode of the first piezoelectric ceramic extends through the first connecting hole into the first cavity. The first connecting hole is located at the center of one end wall of the first fuel tank. The second explosive component includes at least one pair of second pressure relief pipes fixedly installed on the circumferential side wall of the first fuel tank. Each pair of second pressure relief pipes is arranged opposite to each other in the radial direction of the second fuel tank. One end of each second pressure relief pipe is connected to the second fuel tank, and the other end extends away from the closed end of the first fuel tank and is parallel to the second fuel tank. A second explosive valve is provided at the other end of each second pressure relief pipe. The second ignition component includes a second piezoelectric ceramic, which is fixedly installed in the second connecting hole. The discharge electrode of the second piezoelectric ceramic extends through the second connecting hole into the second cavity. The second connecting hole is located at the center of one end wall of the second fuel tank. The third explosive component includes at least one pair of third pressure relief pipes fixedly installed on the circumferential side wall of the third fuel tank. Each pair of third pressure relief pipes is arranged opposite to each other in the radial direction of the third fuel tank. One end of each third pressure relief pipe is connected to the third fuel tank, and the other end extends away from the closed end of the first fuel tank and is parallel to the third fuel tank. A third explosive valve is provided at the other end of each third pressure relief pipe. The third ignition component includes an electric shock device, which is fixedly installed in the third connection hole. The discharge electrode of the electric shock device extends through the third connection hole into the third cavity. The third connection hole is located at the center of one end wall of the third fuel tank.

5. The chemical fuel multi-stage propulsion electromagnetic hybrid catapult device as described in claim 4, characterized in that, The first impact component also includes a first cover plate, which is fixedly installed at the other end of the first sealing flange, and the center of the first sealing flange is provided with a first channel with openings at both ends along the length direction of the base; The first cover plate covers the opening at one end of the first channel, and the center of the first cover plate has a first passage opening that communicates with the first channel. The first impact member includes a first impact block that is movably installed in the first channel, and a plurality of first telescopic springs. One end of each first telescopic spring is fixedly connected to a corresponding side of the first impact block, and the other end extends along the length direction of the base and is fixedly connected to the first cover plate. The second impact component also includes a second cover plate, which is fixedly installed at the other end of the second sealing flange, and the center of the second sealing flange is provided with a second channel with openings at both ends along the length direction of the base; The second cover plate covers the opening at one end of the second channel, and the center of the second cover plate has a second passage opening that communicates with the second channel. The second impact member includes a second impact block that is movably installed in the second channel, and a plurality of second telescopic springs. One end of each second telescopic spring is fixedly connected to a corresponding side of the second impact block, and the other end extends along the length of the base and is fixedly connected to the second cover plate.

6. The chemical fuel multi-stage propulsion electromagnetic hybrid catapult device as described in claim 1, characterized in that, The first stator further includes a first mounting plate and a plurality of first electrical connecting pieces. The first mounting plate is vertically fixed to one side of the base. The plurality of first electrical connecting pieces are arranged side by side on the first mounting plate along the length direction of the base. The plurality of first magnetic elements are arranged side by side on the first mounting plate along the length direction of the base. The second stator further includes a second mounting plate and a plurality of second electrical connecting pieces. The second mounting plate is vertically fixed to one side of the base. The plurality of second electrical connecting pieces are arranged side by side on the second mounting plate along the length direction of the base. The plurality of second magnetic elements are arranged side by side on the second mounting plate along the length direction of the base. In the thickness direction of the base, the plurality of first electrical connecting pieces are spaced apart from the plurality of first magnetic elements, and the plurality of second electrical connecting pieces are spaced apart from the plurality of second magnetic elements. In the width direction of the base, the first mounting plate and the second mounting plate are spaced apart relative to each other, and the plurality of first electrical connecting pieces and the plurality of second electrical connecting pieces are spaced apart relative to each other. When the mover and the movable seat move along the length direction of the base, both sides of the mover sequentially contact and are electrically connected to their respective first electrical connecting pieces and second electrical connecting pieces, so as to transmit current to the mover coil of the mover through the corresponding first electrical connecting pieces and second electrical connecting pieces.

7. The chemical fuel multi-stage propulsion electromagnetic hybrid catapult device as described in claim 6, characterized in that, The moving element also includes a coil box, a first brush, and a second brush. The coil box is fixedly installed on the side of the movable base near the base. In the width direction of the base, the first brush and the second brush are respectively fixedly installed on both sides of the coil box. The coil box has an internal accommodating space, and the moving coil is fixedly installed in the accommodating space. The first brush and the second brush are electrically connected to the moving coil. When the moving coil and the movable seat move along the length direction of the base, the first brush and the second brush sequentially contact and are electrically connected to their respective first and second electrical connecting pieces, so that the corresponding first and second electrical connecting pieces transmit current to the moving coil through the first brush and the second brush.

8. The chemical fuel multi-stage propulsion electromagnetic hybrid catapult device as described in claim 1, characterized in that, The base has a pair of guide portions on one side along its thickness direction, the pair of guide portions extend along the length direction of the base, and the pair of guide portions are spaced apart from each other in the width direction of the base, with the first stator and the second stator located between the pair of guide portions; The mobile base includes a sliding plate and a connecting frame fixedly installed on the side of the sliding plate away from the base. The side of the sliding plate near the base is provided with a pair of guided portions corresponding to the pair of guide portions. The pair of guided portions are slidably connected to the pair of guide portions so that the mobile base is slidably connected to the base along the length direction of the base. The end of the connecting frame away from the base is provided with a pair of connecting protrusions, and the pair of connecting protrusions are used to engage the landing gear of the UAV.

9. The chemical fuel multi-stage propulsion electromagnetic hybrid catapult device as described in any one of claims 1-8, characterized in that, The chemical fuel multi-stage propulsion electromagnetic hybrid catapult also includes: The launch bracket includes a bracket body and a support plate fixedly installed on the top of the bracket body. In the length direction of the support plate, one end of the base is rotatably connected to one end of the support plate. A position adjustment assembly includes a driving component and a transmission component. The driving component is installed on the other end of the support plate near the base. One end of the transmission component is connected to the driving end of the driving component, and the other end is connected to the other side of the base.

10. The chemical fuel multi-stage propulsion electromagnetic hybrid catapult device as described in claim 9, characterized in that, The driving component includes a mounting bracket, a screw, a driving handwheel, and a slider. The mounting bracket is fixedly installed on the other end of the support plate near the base. The screw extends along the length of the support plate and is rotatably connected to the mounting bracket at both ends. The driving handwheel is fixed to one end of the screw, and the slider is threadedly connected to the screw. The transmission component includes a pair of transmission rods that correspond one-to-one with the two ends of the slider in the width direction of the support plate. One end of each transmission rod is rotatably connected to the corresponding end of the slider, and the other end extends to be rotatably connected to the other end of the base.

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