Hovercraft

Abstract

The invention relates to a hovercraft and relates to the technical field of hovercrafts, the hovercraft comprises a hull and a propelling assembly, a hovering assembly is arranged above the stern of the hull, guide assemblies used for guiding the direction of the hull are arranged on the two sides of the hovering assembly, and the propelling assembly is arranged above the bow of the hull; a control assembly is arranged between the two propelling assemblies, an apron is installed at the bottom of the ship body, and a power assembly is arranged at the position, below the control assembly, of the ship body. According to the ship, the propelling assembly sprays air flow, the ship body is pushed to move forwards through reverse pushing force, and when the horizontal angle of the ship body needs to be adjusted, the control assembly adjusts the angle of the propelling assembly, meanwhile, the air outlet direction of the guide assembly is adjusted, and driving of the propelling assembly is assisted; therefore, the stability of the propulsion assembly in the process of pushing the hovercraft is maintained.

Description

Technical Field

[0001] The present application relates to the technical field of hovercraft, and in particular to hovercraft. Background Art

[0002] A hovercraft is a high-speed ship that uses the surface effect principle to form an air cushion between the hull and the supporting surface (water surface or ground) by relying on air at a pressure higher than atmospheric pressure, so that the hull can sail completely or partially away from the supporting surface. According to the way the air cushion is generated, it can be divided into two types: full-cushion hovercraft and sidewall hovercraft; In the prior art, the related technology of hovercraft can refer to the Chinese patent with publication number CN102161379A, which discloses a self-powered hovercraft, including a self-powered hovercraft composed of an engine (I), a hull (II), an air cushion (III), a fan (IV), bolts (V) and nuts (VI), wherein the air cushion (III) and the fan (IV) are mounted on the hull (II), the engine (I) is mounted on the hull (II) by bolts (V) and nuts (VI), and the magnetic force of magnets (2-2) and magnets (5-1-1) is used as power in the engine (I). The self-powered hovercraft can work continuously for 24 hours without burning oil, and does not require logistical oil replenishment. At the same time, it has a long service life, is easy to repair, and is convenient to use.

[0003] The inventor discovered the following problems in the prior art during the implementation of this application: When operating a hovercraft, the principle of aerodynamics is usually adopted. Jet is sprayed toward the bottom of the hull to form an air layer under the hull, separating the hull from the water surface or land. Then a rearward fan is set at the rear of the hull to move the hull forward. However, the movement of the hovercraft requires a separate rearward fan, which affects the accommodation space of the deck of the hovercraft. Summary of the invention

[0004] The object of the present application is to provide a hovercraft.

[0005] The hovercraft provided in this application adopts the following technical solution: A hovercraft comprises a hull and a propulsion assembly, wherein a lifting assembly is arranged above the stern of the hull, and guide assemblies for guiding the direction of the hull are arranged on both sides of the lifting assembly, and a propulsion assembly is arranged above the bow of the hull, and a control assembly is arranged between two groups of the propulsion assemblies, and a skirt is installed at the bottom of the hull, and a power assembly is arranged on the hull below the control assembly.

[0006] By adopting the above technical solution, the ship's frame of the hull is the basic framework of the hovercraft, providing support and an installation foundation for other components to ensure the structural stability of the entire hull. Then, the power components inside the starting hull are activated, and the power components supply energy to the lift components. At this time, the lift components are activated and supply air to the skirts installed around the bottom of the hull. The skirts can reduce the leakage of air inside the air cushion, improve the sealing performance of the air cushion, and can also adapt to different water or ground conditions, enhancing the stability and adaptability of the hovercraft. Then, the water outlet end of the propulsion components is adjusted, and the propulsion components eject airflows, and the hull is pushed forward by the reverse driving force. When it is necessary to adjust the horizontal angle of the hull, the control components adjust the angles of the propulsion components at this time, and at the same time adjust the air outlet direction of the guiding components, and assist the driving of the propulsion components to maintain the stability during the process of the propulsion components pushing the hovercraft.

[0007] The propulsion components include a second intake cylinder, an adjustment bracket, a fixed bracket, an inclined bracket, a stepping motor, a docking hose, and a water inlet guiding pipe. The outer diameter surface of the second intake cylinder is installed with an adjustment bracket through bolts. Fixed brackets are arranged on both sides of the adjustment bracket. An inclined bracket is arranged on the side of the fixed bracket away from the second intake cylinder. A stepping motor is arranged on the side of the inclined bracket away from the second intake cylinder. The air outlet end of the second intake cylinder is installed with a docking hose through bolts. One end of the docking hose away from the second intake cylinder is installed with a water inlet guiding pipe through bolts.

[0008] By adopting the above technical solution, the second air intake cylinder is the air intake passage of the propulsion assembly, providing the required air flow for the propulsion assembly to generate propulsion power. The adjustment bracket is installed on the outer diameter surface of the second air intake cylinder through bolts and is used to adjust the position or angle of the air intake cylinder so that it can be adjusted according to different navigation requirements to optimize the propulsion effect. Then, the fixing bracket is used to maintain the stability of the adjustment bracket and the second air intake cylinder, preventing them from shifting during operation and providing reliable support for the entire propulsion assembly. By cooperating with the fixing bracket and the stepper motor through the tilting bracket, the stepper motor drives the tilting bracket, further fixing the position of the second air intake cylinder while also causing the stepper motor to drive the tilting of the tilting bracket and drive the adjustment of the tilting angle of the position of the water inlet guide pipe, enabling the propulsion assembly to be adjusted according to different propulsion direction and force requirements. Then, the docking hose connects the second air intake cylinder and the water inlet guide pipe. When the tilting bracket adjusts the angle of the water inlet guide pipe, the soft structure of the docking hose can be used to maintain the adaptive change of the water inlet guide pipe during the tilting angle adjustment, enabling the water inlet guide pipe to be unrestricted by the structure, adapting to the relative movement and angle adjustment of different components, ensuring the smooth transmission of air flow, and guiding the air flow coming out of the second air intake cylinder to the required direction to generate the power to push the hovercraft forward. According to the adjustment of its direction and air flow size, the navigation speed and direction of the hovercraft can be changed.

[0009] The guiding assembly includes a sealed housing, a fan, a flow deflector, an electric telescopic frame, and a docking rod. The fan is installed on the side of the sealed housing through bolts. The air outlet end of the fan is equipped with a flow deflector. The electric telescopic frame is installed at the edge of the fan through bolts. A docking rod is connected between the electric telescopic frame and the flow deflector through a clamp.

[0010] By adopting the above technical solution, the sealed housing protects the fan, preventing damage to internal components caused by water, dust, etc., and providing structural support for the overall structure through the sealed housing to maintain the stability of the fan. Then, the fan starts and generates air flow, providing auxiliary power for the direction steering process of the hovercraft's turning. By controlling the size and direction of the air flow, precise control of the hovercraft's direction can be achieved. Then, the flow deflector is used to guide the air flow generated by the fan to blow out along the required direction, improving the directivity and efficiency of the air flow and enhancing the turning effect of the hovercraft. Then, the electric telescopic frame is adjusted by telescoping. By changing its own length, the position and angle of the flow deflector are changed, thereby adjusting the direction and size of the air flow, making the turning operation of the hovercraft more flexible and precise. The flow deflector is connected to the electric telescopic frame through a clamp using the docking rod, enhancing the structural stability and ensuring a firm connection between the flow deflector and the electric telescopic frame.

[0011] The hull includes a ship's skeleton, a first separation groove, a second separation groove, and a third separation groove. A first separation groove is reserved at the front end of the ship's skeleton of the hull, a second separation groove is reserved at the terminal end of the ship's skeleton, and a third separation groove is arranged on one side of the second separation groove away from the first separation groove.

[0012] The hull further includes a reinforcement support frame, a fixing frame, and an external connection support. The reinforcement support frame is installed at the inner edge of the ship's skeleton through bolts. Fixing frames are arranged at the outer edges of the reinforcement support frame. A fixed connection structure is formed between the ship's skeleton and the fixing frames through bolts. An external connection support is arranged between the two reinforcement support frames, and a fixed connection structure is formed between the ship's skeleton and the external connection support through bolts.

[0013] By adopting the above technical solutions, the ship's skeleton is the basic framework of the hovercraft, providing support and an installation foundation for other components to ensure the structural stability of the entire hull. The specific effect of the first separation groove is to reduce the resistance at the bow part when the hovercraft is sailing, enabling the air flow or water flow to pass more smoothly, thereby improving the sailing efficiency. The second separation groove is similar to the first separation groove and is located in the middle section of the ship, helping to separate the fluid or air flow at the stern part, reducing the resistance at the stern, and improving the sailing performance. The third separation groove further refines the fluid separation function at the rear end of the hull, optimizing the hydrodynamic performance of the stern according to the air flow or water flow conditions in different sailing states. The reinforcement support frame is installed inside the ship's skeleton through bolts to enhance the structural strength of the hull, prevent the hull from deforming due to various external forces during operation, and ensure the stability and safety of the hull. The fixing frames are fixedly connected to the ship's skeleton and the reinforcement support frame through bolts to further strengthen the structure of the hull, ensure the firm connection between various components, and improve the stability of the overall structure. The external connection support is arranged between the two reinforcement support frames and is used to reinforce the overall framework of the ship's skeleton a second time, thereby maintaining the framework stability of the ship's skeleton.

[0014] The lift component includes a first air intake cylinder, an installation bracket, a connecting bracket, a shock-absorbing bracket, and an intake fan. The installation bracket is installed at the edge of the first air intake cylinder through bolts. The connecting bracket is installed on the side of the installation bracket away from the first air intake cylinder. Shock-absorbing brackets are arranged on both sides of the connecting bracket. The intake fan is arranged inside the first air intake cylinder.

[0015] By adopting the above technical solution, the first air intake cylinder is the main air intake part of the lift component, providing the required air flow for generating the lift effect, and is used to introduce external air into the interior of the apron. Then, the mounting bracket is used to stably mount the first air intake cylinder on the hull, ensuring the fixed position of the first air intake cylinder during operation and avoiding the influence of vibration or other external forces on its normal operation. Then, the first air intake cylinder and the shock-absorbing bracket are connected by a connecting frame, which plays a role in transmitting force and ensuring the connection stability between components. During the process of maintaining the operation of the first air intake cylinder, the damping rod arranged in the shock-absorbing bracket is used to reduce the vibration generated during the rotation of the intake fan blade and the impact of air flow, etc., protecting the position of the connecting piece between the lift component and the hull and avoiding the metal fatigue problem of the connecting piece during vibration, so as to extend the service life and improve the riding comfort at the same time. The intake fan rotation is the key component for generating the lift air flow. By rotating at high speed, it sucks external air into the first air intake cylinder, providing sufficient lift force for the hovercraft to enable the hull to leave the water surface or the ground, realizing hover suspension, reducing frictional resistance, and improving the navigation speed and maneuverability.

[0016] The control component includes a windproof cover, a control frame, and a carrying platform. A control frame is provided above the inner wall of the windproof cover, and a carrying platform is provided on the side of the control frame.

[0017] By adopting the above technical solution, the windproof cover provides wind protection for the control frame and the carrying platform, preventing the wind, water, and dust in the external environment from damaging the control components and ensuring the normal operation of the control components. Then, the control frame is used to carry the control equipment to realize the operation and control of the lift component, propulsion component, and guiding component of the hovercraft. It is the control core of the hovercraft, determining the operation state and performance of the hovercraft. The carrying platform facilitates personnel to take a seat.

[0018] The apron includes a support frame, a first clamping groove, a second clamping groove, and a skirt belt. A first clamping groove is provided at the stern end of the support frame. A fixed connection structure is formed between the lift component and the apron through the second air intake cylinder and the first clamping groove. A second clamping groove is provided at the top end of the support frame, and the second clamping grooves are symmetrically placed. A fixed connection structure is formed between the propulsion component and the apron bracket through the first air intake cylinder and the second clamping groove. The skirt belt is installed below the support frame by bolts.

[0019] By adopting the above technical solution, the support frame provides structural support for the entire apron, ensuring the stability of the shape and position of the apron. It is the skeleton part of the apron. Then, the first engaging groove and the lifting assembly form a fixed connection structure through the second air intake cylinder and itself, ensuring the tight connection between the apron and the lifting assembly, preventing air leakage generated during the operation of the hovercraft, and ensuring the lifting effect. Then, the second engaging grooves are symmetrically placed to firmly connect the propulsion assembly and the apron, avoiding the leakage of propulsion air flow, improving the propulsion efficiency, and at the same time ensuring the overall integrity and stability of the apron. The skirt band connected to the support frame is installed below the support frame. When the hovercraft is lifted, the apron encloses the air under the hull to form an air cushion, and the skirt band plays a role in sealing and maintaining the air cushion pressure, reducing the air leakage in the air cushion, and improving the lifting efficiency, thereby reducing the friction between the hull and the ground or water surface.

[0020] A support mounting frame is provided above the external support, and a fixed connection structure is formed between the support mounting frame and the external support through a docking plate. The power assembly includes a generator, a transmission unit, and a placement frame. The output end of the generator is connected to a transmission unit, and placement frames are installed on the four sides of the generator.

[0021] By adopting the above technical solution, the generator serves as a power source to supply power to the lifting assembly, propulsion assembly, and fan of the hovercraft to ensure their normal operation. Then, the clutch and transmission of the transmission unit cooperate with the drive shaft to transmit the power generated by the generator to other components that require power, realizing the effective transmission and distribution of power, ensuring the coordinated operation of each component. Then, the placement frames are installed on the four sides of the generator to fix and protect the generator, ensuring the stability and safety of the generator during operation.

[0022] In summary, the present application includes at least one of the following beneficial technical effects: 1. Then, when the water outlet end of the propulsion assembly is adjusted to make the propulsion assembly eject air flow, and the hull is pushed forward by the reverse driving force. When it is necessary to adjust the horizontal angle of the hull, the control assembly adjusts the angle of the propulsion assembly at this time, and at the same time adjusts the air outlet direction of the guiding assembly to assist the driving of the propulsion assembly to maintain the stability during the process of the propulsion assembly pushing the hovercraft. 2. The stepper motor drives the tilt of the tilt bracket and adjusts the position of the water inlet guide pipe to change the tilt angle, enabling the propulsion assembly to be adjusted according to different propulsion directions and force requirements. Then, the docking hose connects the second air intake cylinder and the water inlet guide pipe. When the tilt bracket adjusts the angle of the water inlet guide pipe, the flexible structure of the docking hose can be used to maintain the adaptive change of the water inlet guide pipe during the tilt angle adjustment, so that the water inlet guide pipe is not restricted by the structure, adapts to the relative movement and angle adjustment of different components, and at the same time ensures the smooth transmission of air flow. Moreover, the water inlet guide pipe guides the air flow coming out of the second air intake cylinder and directs it to the required direction, generating the power to push the hovercraft forward. According to the adjustment of its direction and air flow size, the sailing speed and direction of the hovercraft can be changed; 3. The fan starts and generates air flow, providing auxiliary power during the direction steering process of the hovercraft. By controlling the size and direction of the air flow, precise control of the direction of the hovercraft can be achieved. Then, the air flow generated by the fan is guided through the fairing and blown out along the required direction, improving the directivity and efficiency of the air flow and enhancing the steering effect of the hovercraft. Then, the electric telescopic frame is telescopically adjusted. By changing its own length, the position and angle of the fairing are changed, thereby adjusting the direction and size of the air flow, making the steering operation of the hovercraft more flexible and precise. The fairing is connected to the electric telescopic frame through a docking rod using a clamp, enhancing the structural stability and ensuring a firm connection between the fairing and the electric telescopic frame. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is the overall structural schematic diagram of the embodiment of the present application; Figure 2 is the structural schematic diagram of the hull of the embodiment of the present application; Figure 3 is the structural schematic diagram of the apron of the embodiment of the present application; Figure 4 is the top view sectional structural schematic diagram of the ship skeleton of the embodiment of the present application; Figure 5 is the top view structural schematic diagram of the power assembly of the embodiment of the present application; Figure 6 is the top view structural schematic diagram of the generator of the embodiment of the present application; Figure 7 is the top view structural schematic diagram of the first air intake cylinder of the embodiment of the present application; Figure 8 is the top view structural schematic diagram of the propulsion assembly of the embodiment of the present application; Figure 9 is the structural schematic diagram of the guiding assembly of the embodiment of the present application; Description of reference numerals: 1. Hull; 101. Ship skeleton; 102. First separation groove; 103. Second separation groove; 104. Third separation groove; 105. Reinforcing support frame; 106. Fixed frame; 107. External support bracket; 2. Lift component; 201. First air intake cylinder; 202. Mounting bracket; 203. Connecting frame; 204. Shock-absorbing bracket; 205. Intake fan; 3. Propulsion component; 301. Second air intake cylinder; 302. Adjusting bracket; 303. Fixed bracket; 304. Tilt bracket; 305. Stepper motor; 306. Docking hose; 307. Water inlet guide pipe; 4. Guidance component; 401. Sealed housing; 402. Fan; 403. Fairing; 404. Electric telescopic frame; 405. Docking rod; 5. Control component; 501. Windproof outer cover; 502. Control frame; 503. Carrying platform; 6. Apron; 601. Support frame; 602. First clamping groove; 603. Second clamping groove; 604. Skirt band; 7. Support mounting frame; 701. Docking plate; 8. Power component; 801. Generator; 802. Transmission unit; 803. Placing frame. Detailed implementation manners

[0024] The following will Figure 1 - with reference to Figure 9 the accompanying drawings, the present application will be further described in detail.

[0025] Embodiment: An air-cushion vehicle, including a hull 1 and a propulsion component 3. Above the stern of the hull 1, a lift component 2 is provided. On both sides of the lift component 2, a guidance component 4 for guiding the direction of the hull 1 is provided. Above the bow of the hull 1, a propulsion component 3 is provided. Between the two propulsion components 3, a control component 5 is provided. At the bottom of the hull 1, an apron 6 is installed. Below the control component 5 of the hull 1, a power component 8 is provided. Among them, the ship skeleton 101 of the hull 1 is the basic framework of the air-cushion vehicle, providing support and installation basis for other components to ensure the structural stability of the entire hull 1. Then, the power component 8 inside the hull 1 is started, and the power component 8 supplies energy to the lift component 2. At this time, the lift component 2 is started and supplies air to the apron 6 installed around the bottom of the hull 1. Among them, the apron 6 can reduce the leakage of air in the air cushion, improve the sealing performance of the air cushion, and can also adapt to different water or ground conditions, enhancing the stability and adaptability of the air-cushion vehicle. Then, when the water outlet end of the propulsion component 3 is adjusted to make the propulsion component 3 eject air flow, and the hull 1 is pushed forward by the reverse driving force. When it is necessary to adjust the horizontal angle of the hull 1, at this time, the control component 5 adjusts the angle of the propulsion component 3, and at the same time adjusts the air outlet direction of the guidance component 4 to assist the driving of the propulsion component 3 to maintain the stability during the process of the propulsion component 3 pushing the air-cushion vehicle.

[0026] The propulsion assembly 3 includes a second air intake cylinder 301, an adjustment bracket 302, a fixed bracket 303, an inclined bracket 304, a stepper motor 305, a docking hose 306, and a water inlet guide pipe 307. The outer diameter surface of the second air intake cylinder 301 is mounted with the adjustment bracket 302 by bolts. Fixed brackets 303 are provided on both sides of the adjustment bracket 302. An inclined bracket 304 is provided on the side of the fixed bracket 303 away from the second air intake cylinder 301. A stepper motor 305 is provided on the side of the inclined bracket 304 away from the second air intake cylinder 301. The air outlet end of the second air intake cylinder 301 is mounted with the docking hose 306 by bolts. One end of the docking hose 306 away from the second air intake cylinder 301 is mounted with the water inlet guide pipe 307 by bolts. Among them, the second air intake cylinder 301 is the air intake channel of the propulsion assembly 3, providing the required airflow for the propulsion assembly 3 to generate propulsion power. The adjustment bracket 302 is mounted on the outer diameter surface of the second air intake cylinder 301 by bolts, used to adjust the position or angle of the air intake cylinder, so that it can be adjusted according to different navigation requirements to optimize the propulsion effect. Then the fixed bracket 303 maintains the stability of the adjustment bracket 302 and the second air intake cylinder 301, preventing them from shifting during operation, providing reliable support for the entire propulsion assembly 3. By cooperating with the fixed bracket 303 and the stepper motor 305 through the inclined bracket 304, the inclined bracket 304 is driven by the stepper motor 305. While further fixing the position of the second air intake cylinder 301, it also makes the inclined bracket 304 driven by the stepper motor 305 tilt, and drives the position of the water inlet guide pipe 307 to adjust the tilt angle, so that the propulsion assembly 3 can be adjusted according to different propulsion direction and force requirements. Then the docking hose 306 connects the second air intake cylinder 301 and the water inlet guide pipe 307, so that when the inclined bracket 304 adjusts the angle of the water inlet guide pipe 307, through the flexible structure of the docking hose 306, it can maintain the adaptive change of the water inlet guide pipe 307 during the tilting angle process, so that the water inlet guide pipe 307 is not restricted by the structure, adapts to the relative movement and angle adjustment of different components, and at the same time ensures the smooth transmission of the airflow. And the water inlet guide pipe 307 guides the airflow coming out of the second air intake cylinder 301 and directs it to the required direction to generate the power to push the hovercraft forward. According to the adjustment of its direction and the size of the airflow, the navigation speed and direction of the hovercraft can be changed.

[0027] The guiding component 4 includes a sealed housing 401, a fan 402, a deflector 403, an electric telescopic frame 404 and a docking rod 405. The fan 402 is installed on the side of the sealed housing 401 through bolts. The deflector 403 is installed at the air outlet end of the fan 402. The electric telescopic frame 404 is installed at the edge of the fan 402 through bolts. The docking rod 405 is connected between the electric telescopic frame 404 and the deflector 403 through a clamp. The sealed housing 401 provides protection for the fan 402 to prevent damage to internal components caused by water, dust, etc., and structurally supports the overall structure through the sealed housing 401 to maintain the stability of the fan 402. Then the fan 402 starts and generates air flow, providing auxiliary power during the steering of the hovercraft. By controlling the size and direction of the air flow, precise control of the direction of the hovercraft can be achieved. Then the deflector 403 is used to guide the air flow generated by the fan 402 to blow out along the required direction, improving the directivity and efficiency of the air flow and enhancing the steering effect of the hovercraft. Then the electric telescopic frame 404 is telescopically adjusted. By changing its own length, the position and angle of the deflector 403 are changed, thereby adjusting the direction and size of the air flow, making the steering operation of the hovercraft more flexible and precise. The deflector 403 is connected to the electric telescopic frame 404 through a docking rod 405 using a clamp, enhancing the structural stability and ensuring the firm connection between the deflector 403 and the electric telescopic frame 404.

[0028] The hull 1 includes a ship skeleton 101, a first separation groove 102, a second separation groove 103 and a third separation groove 104. A first separation groove 102 is reserved at the front end of the ship of the ship skeleton 101. A second separation groove 103 is reserved at the end of the ship of the ship skeleton 101. A third separation groove 104 is arranged on one side of the second separation groove 103 away from the first separation groove 102.

[0029] The hull 1 also includes a reinforcing support frame 105, a fixing frame 106, and an external support frame 107. The reinforcing support frame 105 is installed at the inner edge of the ship's frame 101 by bolts. Fixing frames 106 are provided at the outer edges of the reinforcing support frame 105. A fixed connection structure is formed between the ship's frame 101 and the fixing frames 106 by bolts. An external support frame 107 is provided between the two reinforcing support frames 105. A fixed connection structure is formed between the ship's frame 101 and the external support frame 107 by bolts. Then, the ship's frame 101 is the basic framework of the hovercraft, providing support and an installation foundation for other components, ensuring the structural stability of the entire hull 1. The first separation groove 102 specifically reduces the resistance at the bow part when the hovercraft is sailing, enabling air or water flow to pass more smoothly, improving the sailing efficiency. And the second separation groove 103 is similar to the first separation groove 102 and is located at the ship's terminal, helping to separate the fluid or air flow at the stern part, reducing the resistance at the stern, and improving the sailing performance. The third separation groove 104 further refines the fluid separation function at the rear end of the hull 1, optimizing the hydrodynamic performance of the stern according to the air or water flow conditions in different sailing states. The reinforcing support frame 105 is installed inside the ship's frame 101 by bolts to enhance the structural strength of the hull 1, preventing the hull 1 from deforming due to various external forces during operation and ensuring the stability and safety of the hull 1. Then, the fixing frames 106 are fixedly connected to the ship's frame 101 and the reinforcing support frame 105 by bolts, further strengthening the structure of the hull 1, ensuring the firm connection between various components, and improving the overall structural stability. The external support frame 107 is provided between the two reinforcing support frames 105 and is used to reinforce the overall framework of the ship's frame 101 a second time, thereby maintaining the framework stability of the ship's frame 101.

[0030] The lift component 2 includes a first air intake cylinder 201, a mounting bracket 202, a connecting frame 203, a shock-absorbing bracket 204, and an intake fan 205. The edge of the first air intake cylinder 201 is bolted with the mounting bracket 202. The connecting frame 203 is mounted on one side of the mounting bracket 202 away from the first air intake cylinder 201. Shock-absorbing brackets 204 are provided on both sides of the connecting frame 203. The intake fan 205 is arranged inside the first air intake cylinder 201. The first air intake cylinder 201 is the main air intake part of the lift component 2, providing the airflow required for generating the lift effect, and is suitable for introducing external air into the inside of the apron 6. Then, the mounting bracket 202 is used to stably mount the first air intake cylinder 201 on the hull 1, ensuring the fixed position of the first air intake cylinder 201 during operation and avoiding the influence of vibration or other external forces on its normal operation. Then, the connecting frame 203 connects the first air intake cylinder 201 and the shock-absorbing bracket 204, playing a role in transmitting force and ensuring the connection stability between components. During the process of maintaining the operation of the first air intake cylinder 201 by the shock-absorbing bracket 204, the damping rod arranged in the shock-absorbing bracket 204 is used to reduce the vibration generated by the rotation of the intake fan blade and the impact of the airflow, etc., protecting the position of the connecting parts between the lift component 2 and the hull 1, avoiding the metal fatigue problem of the connecting parts during vibration, so as to extend the service life and improve the riding comfort at the same time. The rotation of the intake fan 205 is the key component for generating the lift airflow. By rotating at high speed, it sucks external air into the first air intake cylinder 201, providing sufficient lift force for the hovercraft, enabling the hull 1 to leave the water surface or the ground, realizing hover suspension, reducing the frictional resistance, and improving the sailing speed and maneuverability.

[0031] The control component 5 includes a windproof cover 501, a control frame 502, and a bearing platform 503. The control frame 502 is arranged above the inner wall of the windproof cover 501, and the bearing platform 503 is arranged on the side of the control frame 502. The windproof cover 501 provides windproof protection for the control frame 502 and the bearing platform, preventing the wind, water, and dust in the external environment from damaging the control components and ensuring the normal operation of the control components. Then, the control frame 502 is used to carry the control equipment to realize the operation and control of the lift component 2, the propulsion component 3, and the guiding component 4 of the hovercraft. It is the control core of the hovercraft, determining the operation state and performance of the hovercraft. The bearing platform 503 facilitates personnel to take a seat.

[0032] The apron 6 includes a support frame 601, a first engaging groove 602, a second engaging groove 603, and a skirt 604. The stern end of the support frame 601 is provided with the first engaging groove 602, and a fixed connection structure is formed between the lift component 2 and the apron 6 through the second air inlet cylinder 301 and the first engaging groove 602. The top end of the support frame 601 is provided with the second engaging groove 603, and the second engaging grooves 603 are symmetrically placed. A fixed connection structure is formed between the propulsion component 3 and the apron 6 through the first air inlet cylinder 201 and the second engaging groove 603. The skirt 604 is installed below the support frame 601 by bolts. The support frame 601 provides structural support for the entire apron 6, ensuring the shape and position stability of the apron 6. It is the framework part of the apron 6. Then, the first engaging groove 602 and the lift component 2 form a fixed connection structure through the second air inlet cylinder 301 and itself, ensuring the tight connection between the apron 6 and the lift component 2, preventing air leakage generated during the operation of the hovercraft, and ensuring the lift effect. Then, the second engaging grooves 603 are symmetrically placed, firmly connecting the propulsion component 3 and the apron 6, avoiding the leakage of propulsion air flow, improving the propulsion efficiency, and at the same time ensuring the overall integrity and stability of the apron 6. The skirt 604 connected to the support frame 601 is installed below the support frame 601. When the hovercraft is lifted, the apron 6 encloses the air under the hull 1 to form an air cushion, and the skirt 604 plays a role in sealing and maintaining the air cushion pressure, reducing the air leakage in the air cushion, and improving the lift efficiency, thereby reducing the friction between the hull 1 and the ground or water surface.

[0033] A support mounting frame 7 is provided above the external support bracket 107, and a fixed connection structure is formed between the support mounting frame 7 and the external support bracket 107 through the docking plate 701. The power component 8 includes a generator 801, a transmission unit 802, and a placement frame 803. The output end of the generator 801 is connected to a transmission unit, and the placement frame 803 is installed on the four sides of the generator 801. The generator 801 serves as a power source to provide power for the lift component 2, the propulsion component 3, and the fan 402 of the hovercraft, ensuring their normal operation. Then, the clutch and transmission of the transmission unit 802 cooperate with the transmission shaft to transmit the power generated by the generator 801 to other components that require power, realizing the effective transmission and distribution of power, ensuring the coordinated operation of each component. Then, the placement frame 803 is installed on the four sides of the generator 801, playing a role in fixing and protecting the generator 801, ensuring the stability and safety of the generator 801 during operation.

[0034] The implementation principle of the embodiments of this application is as follows: The ship's frame 101 of the middle hull 1 is the basic framework of the hovercraft, providing support and an installation foundation for other components to ensure the structural stability of the entire hull 1. Then, the power component 8 inside the starting hull 1 is activated, and the power component 8 supplies energy to the lift component 2. At this time, the lift component 2 is activated and supplies air to the skirt 6 installed around the bottom of the hull 1. The skirt 6 can reduce the leakage of air inside the air cushion, improve the sealing performance of the air cushion, and can also adapt to different water or ground conditions, enhancing the stability and adaptability of the hovercraft. Then, when the water outlet end of the propulsion component 3 is adjusted to make the propulsion component 3 eject air flow, the hull 1 is pushed forward by the reverse driving force. When it is necessary to adjust the horizontal angle of the hull 1, the control component 5 adjusts the angle of the propulsion component 3 at this time, and at the same time adjusts the air outlet direction of the guiding component 4 to assist the driving of the propulsion component 3 to maintain the stability during the process of the propulsion component 3 pushing the hovercraft.

[0035] Among them, the second air intake cylinder 301 is the air intake channel of the propulsion component 3, providing the required air flow for the propulsion component 3 to generate propulsion power. The adjustment bracket 302 is installed on the outer diameter surface of the second air intake cylinder 301 through bolts, used to adjust the position or angle of the air intake cylinder so that it can be adjusted according to different navigation requirements to optimize the propulsion effect. Then, the fixing bracket 303 maintains the stability of the adjustment bracket 302 and the second air intake cylinder 301, preventing them from shifting during operation and providing reliable support for the entire propulsion component 3. By cooperating the inclined bracket 304 with the fixing bracket 303 and the stepper motor 305, the stepper motor 305 drives the inclined bracket 304. While further fixing the position of the second air intake cylinder 301, it also makes the inclined bracket 304 driven by the stepper motor 305 tilt, driving the position of the water inlet guiding pipe 307 to adjust the tilt angle, so that the propulsion component 3 can be adjusted according to different propulsion directions and force requirements. Then, the docking hose 306 connects the second air intake cylinder 301 and the water inlet guiding pipe 307, enabling the inclined bracket 304 to maintain the adaptive change of the water inlet guiding pipe 307 during the process of adjusting the tilt angle through the soft structure of the docking hose 306, so that the water inlet guiding pipe 307 is not restricted by the structure, adapts to the relative movement and angle adjustment of different components, and at the same time ensures the smooth transmission of air flow. And the water inlet guiding pipe 307 guides the air flow coming out of the second air intake cylinder 301 to the required direction, generating the power to push the hovercraft forward. According to the adjustment of its direction and air flow size, the navigation speed and direction of the hovercraft can be changed.

[0036] The sealed housing 401 provides protection for the fan 402 against damage to internal components caused by water, dust, etc., and provides structural support for the overall structure through the sealed housing 401 to maintain the stability of the fan 402. Then the fan 402 starts and generates an air flow, providing auxiliary power during the direction steering process of the hovercraft. By controlling the size and direction of the air flow, precise control of the direction of the hovercraft can be achieved. Then the air deflector 403 is used to guide the air flow generated by the fan 402 to blow out along the required direction, improving the directivity and efficiency of the air flow and enhancing the turning effect of the hovercraft. Then the electric telescopic frame 404 is telescopically adjusted. By changing its own length, the position and angle of the air deflector 403 are changed, thereby adjusting the direction and size of the air flow to make the turning operation of the hovercraft more flexible and precise. The air deflector 403 is connected to the electric telescopic frame 404 through a docking rod 405 using a clamp to enhance the structural stability and ensure a firm connection between the air deflector 403 and the electric telescopic frame 404.

[0037] Then the ship's skeleton 101 is the basic framework of the hovercraft, providing support and an installation foundation for other components to ensure the structural stability of the entire hull 1. Then the first separation groove 102, its specific effect is to reduce the resistance of the bow part when the hovercraft is sailing, enabling the air flow or water flow to pass through more smoothly, improving the sailing efficiency. And the second separation groove 103 is similar to the first separation groove 102 and is located at the end of the ship, helping to separate the fluid or air flow at the stern part, reducing the resistance at the stern and improving the sailing performance. The third separation groove 104 further refines the fluid separation function at the rear end of the hull 1, optimizing the hydrodynamic performance of the stern according to the air flow or water flow conditions in different sailing states and strengthening the support frame 105 is installed inside the ship's skeleton 101 through bolts to enhance the structural strength of the hull 1, preventing the hull 1 from deforming due to various external forces during operation and ensuring the stability and safety of the hull 1. Then the fixing frame 106 is fixedly connected to the ship's skeleton 101 and the strengthening support frame 105 through bolts to further strengthen the structure of the hull 1, ensuring a firm connection between each component and improving the stability of the overall structure. Then the external support 107 is arranged between two groups of strengthening support frames 105 and is used for secondary reinforcement of the overall framework of the ship's skeleton 101, thereby maintaining the framework stability of the ship's skeleton 101.

[0038] The first air intake cylinder 201 is the main air intake part of the lift component 2, providing the airflow required to generate the lift effect, suitable for introducing external air into the interior of the apron 6. Then, the mounting bracket 202 is used to stably mount the first air intake cylinder 201 on the hull 1, ensuring the fixed position of the first air intake cylinder 201 during operation and avoiding its normal operation being affected by vibration or other external forces. Then, the first air intake cylinder 201 and the shock-absorbing bracket 204 are connected by the connecting frame 203, which plays a role in transmitting force and ensuring the connection stability between components. During the process of maintaining the operation of the first air intake cylinder 201, the shock-absorbing bracket 204 reduces the vibration generated by the rotation of the intake fan blade and the impact of the airflow through the damping rod set inside the shock-absorbing bracket 204, protecting the position of the connecting parts between the lift component 2 and the hull 1 and avoiding the metal fatigue problem of the connecting parts during vibration, so as to extend the service life and improve the riding comfort at the same time. The rotation of the intake fan 205 is the key component to generate the lift airflow. It sucks external air into the first air intake cylinder 201 through high-speed rotation, providing sufficient lift force for the hovercraft to enable the hull 1 to leave the water surface or the ground, achieve hover suspension, reduce frictional resistance, and improve the navigation speed and maneuverability.

[0039] The windproof outer cover 501 provides wind protection for the control frame 502 and the bearing platform, preventing the wind, water, and dust in the external environment from damaging the control components and ensuring the normal operation of the control components. Then, the control frame 502 is used to carry the control equipment to realize the operation and control of the lift component 2, the propulsion component 3, and the guiding component 4 of the hovercraft. It is the control core of the hovercraft, determining the operation state and performance of the hovercraft. The bearing platform 503 facilitates personnel to take a seat.

[0040] Among them, the support frame 601 provides structural support for the entire apron 6, ensuring the shape and position stability of the apron 6. It is the framework part of the apron 6. Then, the first clamping groove 602 and the lift component 2 form a fixed connection structure through the second air intake cylinder 301 and itself, ensuring the tight connection between the apron 6 and the lift component 2, preventing the airflow leakage generated during the operation of the hovercraft, and ensuring the lift effect. Then, the second clamping grooves 603 are symmetrically placed to firmly connect the propulsion component 3 and the apron 6, avoiding the leakage of the propulsion airflow, improving the propulsion efficiency, and ensuring the overall integrity and stability of the apron 6 at the same time. The skirt belt 604 connected to the support frame 601 is installed below the support frame 601. When the hovercraft is lifted, the apron 6 encloses the air under the hull 1 to form an air cushion, and the skirt belt 604 plays a role in sealing and maintaining the air cushion pressure, reducing the air leakage in the air cushion, improving the lift efficiency, and thus reducing the friction between the hull 1 and the ground or water surface.

[0041] Its generator 801 serves as a power source to supply electricity to the lift component 2, propulsion component 3, and fan 402 of the hovercraft, ensuring their normal operation. Then, the clutch and transmission of the transmission unit 802 cooperate with the transmission shaft to transmit the power generated by the generator 801 to other components that require power, achieving effective transmission and distribution of power, ensuring the coordinated operation of each component. Then, the placement frame 803 is installed on the four sides of the generator 801, playing a role in fixing and protecting the generator 801, ensuring the stability and safety of the generator 801 during operation.

[0042] The embodiments of this specific implementation manner are all preferred embodiments of this application, and do not limit the protection scope of this application accordingly. The same components are denoted by the same reference numerals. Therefore, all equivalent changes made according to the structure, shape, and principle of this application shall be covered within the protection scope of this application.

Claims

1. An air cushion vehicle, comprising a hull (1) and a propulsion assembly (3), characterized in that: A lifting assembly (2) is arranged above the stern of the hull (1), and guide assemblies (4) for guiding the direction of the hull (1) are arranged on both sides of the lifting assembly (2), and a propulsion assembly (3) is arranged above the bow of the hull (1), and a control assembly (5) is arranged between two groups of the propulsion assemblies (3), and a skirt (6) is installed at the bottom of the hull (1), and a power assembly (8) is arranged on the hull (1) below the control assembly (5).

2. The hovercraft according to claim 1, characterized in that: The propulsion assembly (3) comprises a second air intake cylinder (301), an adjustment bracket (302), a fixed bracket (303), an inclined bracket (304), a stepping motor (305), a docking hose (306) and a water inlet guide pipe (307), wherein the adjustment bracket (302) is mounted on the outer diameter surface of the second air intake cylinder (301) by means of bolts, and the fixed brackets (303) are arranged on both sides of the adjustment bracket (302), and the inclined bracket (304) is arranged on the side of the fixed bracket (303) away from the second air intake cylinder (301), and the stepping motor (305) is arranged on the side of the inclined bracket (304) away from the second air intake cylinder (301), and the docking hose (306) is mounted on the air outlet end of the second air intake cylinder (301) by means of bolts, and the water inlet guide pipe (307) is mounted on the end of the docking hose (306) away from the second air intake cylinder (301) by means of bolts.

3. The hovercraft according to claim 1, characterized in that: The guide assembly (4) comprises a sealed housing (401), a fan (402), a flow guide cover (403), an electric telescopic frame (404) and a docking rod (405); the fan (402) is mounted on the side of the sealed housing (401) via bolts, the flow guide cover (403) is mounted on the air outlet end of the fan (402), the electric telescopic frame (404) is mounted on the edge of the fan (402) via bolts, and a docking rod (405) is connected between the electric telescopic frame (404) and the flow guide cover (403) via a clamp.

4. The hovercraft according to claim 1, characterized in that: The hull (1) comprises a ship frame (101), a first separation slot (102), a second separation slot (103) and a third separation slot (104), wherein the first separation slot (102) is reserved at the front end of the ship frame (101), the second separation slot (103) is reserved at the midship section of the ship frame (101), and the third separation slot (104) is arranged on a side of the second separation slot (103) away from the first separation slot (102).

5. The hovercraft according to claim 4, characterized in that: The hull (1) further comprises a reinforcing support frame (105), a fixing frame (106) and an external bracket (107), and the reinforcing support frame (105) is installed at the inner edge of the ship frame (101) by means of bolts, and the outer edge of the reinforcing support frame (105) is provided with a fixing frame (106), and a fixed connection structure is formed between the ship frame (101) and the fixing frame (106) by means of bolts, and an external bracket (107) is provided between two groups of the reinforcing support frames (105), and a fixed connection structure is formed between the ship frame (101) and the external bracket (107) by means of bolts.

6. The hovercraft according to claim 1, characterized in that: The cushion lifting assembly (2) comprises a first air intake cylinder (201), a mounting bracket (202), a connecting frame (203), a shock absorbing bracket (204) and an air intake fan (205), wherein the mounting bracket (202) is mounted on the edge of the first air intake cylinder (201) by means of bolts, and the connecting frame (203) is mounted on the side of the mounting bracket (202) away from the first air intake cylinder (201), and shock absorbing brackets (204) are arranged on both sides of the connecting frame (203), and the air intake fan (205) is arranged inside the first air intake cylinder (201).

7. The hovercraft according to claim 1, characterized in that: The control assembly (5) comprises a windproof outer cover (501), a control frame (502) and a bearing platform (503), wherein the control frame (502) is arranged above the inner wall of the windproof outer cover (501), and the bearing platform (503) is arranged on the side of the control frame (502).

8. The hovercraft according to claim 1, characterized in that: The skirt (6) comprises a support frame (601), a first engaging groove (602), a second engaging groove (603) and a skirt belt (604), and the first engaging groove (602) is provided at the stern end of the support frame (601), and a fixed connection structure is formed between the cushioning assembly (2) and the skirt (6) through a second air intake cylinder (301) and the first engaging groove (602), and a second engaging groove (603) is provided at the top end of the support frame (601), and the second engaging grooves (603) are symmetrically arranged, and a fixed connection structure is formed between the propulsion assembly (3) and the skirt (6) bracket through the first air intake cylinder (201) and the second engaging groove (603), and a skirt belt (604) is installed below the support frame (601) through bolts.

9. The hovercraft according to claim 5, characterized in that: A support mounting frame (7) is arranged above the external bracket (107), and a fixed connection structure is formed between the support mounting frame (7) and the external bracket (107) via a docking plate (701), and the power assembly (8) comprises a generator (801), a transmission unit (802) and a placement frame (803), and the output end of the generator (801) is connected to the transmission unit, and the placement frames (803) are installed on four sides of the generator (801).

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