Air cushion vehicle control method and air cushion vehicle

Abstract

This application relates to the field of ship control, providing a hovercraft control method and hovercraft, including: in a static power generation mode, disengaging the clutch of the hovering fan, energizing the generator, and having the gas turbine drive the generator to generate electricity through a reducer, driving the propulsion fan to rotate with a reverse pitch, generating a reverse airflow to cool the generator, reducer, and gas turbine; when a sudden load reduction is detected in the generator, increasing the propulsion fan pitch through a pitch controller, increasing the load torque generated by the propulsion fan to compensate for the sudden load reduction and preventing the gas turbine from overspeeding; the hovering fan stops rotating, causing the hovercraft to contract, and the hovercraft contacts the ground through a fixed shovel, the unidirectional resistance generated by the fixed shovel balances the pull generated by the increased propulsion fan pitch, maintaining the stability of the entire vessel. By integrating the generator into the hovercraft's propulsion system and utilizing the adjustable pitch characteristic of the propulsion fan to cope with sudden load reduction, the integration of emergency power and power mobility are improved.

Description

Technical Field

[0001] This application relates to the field of ship control, and more specifically to a hovercraft control method and a hovercraft. Background Technology

[0002] In existing technologies, land-based mobile emergency power supplies mainly use road-mounted wheeled power vehicles as carriers, providing emergency power to disaster-stricken areas through onboard generator sets.

[0003] However, wheeled power vehicles are subject to regulatory load limits (e.g., GB1589-2016 stipulates a maximum permissible gross weight of 40 tons for semi-trailers), which severely restricts their chassis load-bearing capacity and cargo box volume. This limited load space results in limited power generation capacity (generally not exceeding 6MW), making it difficult to accommodate equipment for responding to sudden load reductions (such as large-mass generator rotors and load cells). In particular, in scenarios where natural disasters such as earthquakes and tsunamis damage roads, wheeled power vehicles, limited by their reliance on paved surfaces, may struggle to meet access requirements and reach emergency power generation sites such as coastal power stations in a timely manner. Therefore, existing technologies suffer from limitations in both accessibility and the ability to respond to sudden load reductions in high-power mobile emergency power supplies. Summary of the Invention

[0004] This application provides a hovercraft control method and hovercraft, which can realize a hovercraft control scheme to cope with sudden load reduction of generators, improve the system integration and environmental adaptability of emergency power supply, reduce dependence on road traffic conditions and the need for additional equipment to cope with sudden load reduction.

[0005] In a first aspect, embodiments of this application provide a hovercraft control method. The hovercraft is used in an emergency power generation scenario. The hovercraft includes a gas turbine, a reducer, a generator, and a propulsion fan connected in series. The propulsion fan is equipped with a pitch controller. The hovercraft also includes a lifting fan driven by the gas turbine through a downward output shaft of the reducer, and a fixed hoe disposed on the bottom of the hull. The lifting fan is equipped with a clutch. The method includes: In the static power generation mode, the clutch of the lifting fan is disengaged, the generator is energized, and the gas turbine drives the generator to generate electricity through the reducer. The gas turbine also drives the propulsion fan to rotate with a reverse pitch, generating a reverse airflow to cool the generator, reducer and gas turbine in sequence. When a sudden load reduction is detected in the generator, the pitch of the propulsion fan is increased by the pitch controller, so that the load torque generated by the propulsion fan increases to compensate for the sudden load reduction and prevent the gas turbine from overspeeding. In this process, the air cushion is compressed when the lifting fan stops rotating, and the hull of the hovercraft contacts the ground through the fixed hoe. The unidirectional resistance generated by the fixed hoe balances the pulling force generated by the increased pitch of the propulsion fan, thus maintaining the stability of the entire vessel.

[0006] Secondly, embodiments of this application provide a hovercraft that implements the hovercraft control method corresponding to the first aspect described above. The function can be implemented in hardware or by hardware executing corresponding software. The hardware or software includes one or more modules corresponding to the above function, and the modules can be software and / or hardware.

[0007] In one embodiment, the hovercraft includes: Gas turbines are used to provide shaft power; The reducer has an input shaft connected to the output end of the gas turbine, one output shaft connected to the generator input end, and the other output shaft connected to the clutch input end for deceleration and power distribution. The clutch is used to control the rotation of the lifting fan. A generator, connected to the output end of the reducer, is used to convert shaft power into electrical energy under energized conditions; A propulsion fan is connected to the output end of the generator and is equipped with a pitch controller, which is used to adjust the pitch direction and size of the propulsion fan. The lift fan is driven by the gas turbine through a reducer and outputs downward through a reducer and is connected to the reducer via a clutch. It is used to generate air cushion lift in driving mode. The fixed hoe, located on the front side of the hull, has a triangular structure and is used to generate unidirectional resistance when it comes into contact with the ground when the lifting fan stops or the hull lands. The control cabinet is communicatively connected to the generator and the pitch controller, respectively, and is used to send an increase pitch signal to the pitch controller when a sudden decrease in the load of the generator is detected, so as to increase the load torque of the propulsion fan to compensate for the sudden decrease in load power; The gas turbine, reducer, generator, and propulsion fan are connected in series. In the static power generation mode, the propulsion fan rotates with a reverse pitch to generate a reverse airflow, which cools the generator, reducer, and gas turbine in sequence. The resistance generated by the fixed hoe increases with the increase of the propulsion fan's thrust, in order to balance the thrust generated by the increase of the propulsion fan's pitch when the load suddenly decreases.

[0008] Compared to existing technologies, this application utilizes the characteristics of hovercraft—high speed, large load capacity, and ability to travel on water, swamps, and unpaved roads—to serve as a mobile emergency power source, making it particularly suitable for use as an emergency power source for coastal nuclear power plants. Specifically, this application integrates a generator into the hovercraft's propulsion system. During operation, the generator is not energized and idles with the reducer, serving only as a load carried by the vessel. In stationary power generation mode, most of the gas turbine's shaft power is used to drive the generator, with a portion driving the propulsion fan. Thus, in stationary power generation mode, the propulsion fan also functions as a ventilation and cooling device for the generator set and a device to handle sudden load changes, achieving a high degree of integration and reuse between the propulsion and power generation systems. When the generator encounters a sudden load reduction, the propulsion fan pitch is increased via a pitch controller, rapidly increasing the aerodynamic load torque of the propulsion fan. This directly converts the excess output power of the gas turbine into the kinetic and internal energy of the air, thereby replenishing the suddenly reduced load and preventing the gas turbine from overspeeding. Compared to traditional load cell solutions, the propulsion fan, acting as a power-consuming device, can generate a large amount of airflow for heat dissipation, eliminating the need for additional cooling auxiliary equipment and resulting in a simpler and more reliable system structure. Furthermore, the hovercraft, as a vehicle, can circumvent the regulatory load limits for wheeled vehicles, fully leveraging the advantages of gas turbines—small size, light weight, and high power—to achieve mobile emergency power generation at a higher power level. Simultaneously, the technical solution proposed in this application is not limited by land transportation conditions, allowing for rapid deployment to emergency sites even in disaster-stricken road environments, enhancing environmental adaptability. Attached Figure Description

[0009] The objectives, features, and advantages of the embodiments of this application will become readily understood by referring to the accompanying drawings and the detailed description of the embodiments. Wherein: Figure 1 This is a schematic diagram of the structure of the hovercraft in the embodiments of this application; Figure 2 This is a schematic flowchart of a hovercraft control method according to an embodiment of this application; Figure 3 This is a schematic diagram illustrating the principle of a hovercraft control method according to an embodiment of this application.

[0010] In the attached drawings, 1 represents the gas turbine, 2 the gearbox, 3 the generator, 4 the propulsion fan, 5 the rudder, 6 the propulsion airflow from outside the hull, 7 the airflow passing through the hull, 8 the propulsion fan pitch controller, 9 the lift fan, 10 the lift fan clutch, 11 the fixed hoe, 12 the air cushion, 13 the hull, 14 the control cabinet, 15 the gas turbine exhaust pipe, 16 the hull, 17 the lubricating oil radiator vent, and 18 the gas turbine air inlet. In the attached drawings, the same or corresponding reference numerals indicate the same or corresponding parts. Detailed Implementation

[0011] This application provides a hovercraft control method and a hovercraft, applicable to emergency power generation systems in scenarios requiring high-power mobile emergency power supply. The emergency power generation system includes a hovercraft vehicle and an onboard generator set, which are integrated and deployed together. The hovercraft vehicle is used to carry the generator set to the emergency power generation site and provides ventilation, cooling, and load reduction response functions for the generator set in stationary power generation mode. The onboard generator set converts the shaft power output from the gas turbine into electrical energy to supply power to external loads. The hovercraft vehicle's propulsion system is integrated in series with the generator set; the propulsion fan provides propulsion power in driving mode and also functions as a ventilation and cooling device and a power consumption device during load reduction in stationary power generation mode.

[0012] The solutions provided in this application relate to technologies such as ship power control and generator load management, which are specifically illustrated through the following embodiments: Among them, hovercraft are special vessels that use a lift fan to create a high-pressure air cushion under the hull, allowing the hull to lift off the ground or water surface, thereby significantly reducing drag. Hovercraft can travel on water, swamps, mudflats, and unpaved roads, and are characterized by high speed, large load capacity, and independence from paved roads, making them suitable as transport vehicles for post-disaster emergency equipment.

[0013] A sudden load reduction in a generator refers to a situation where the external load on the generator suddenly decreases or drops significantly during operation. In this case, because the output power of the prime mover (such as a gas turbine) cannot instantly adapt to the load change, the excess power will cause the rotor to accelerate. If not addressed promptly, this could lead to the gas turbine overspeeding and endangering equipment safety. Traditional methods for handling sudden load reductions typically involve using specialized equipment such as load cells to absorb the excess power. However, load cells are large and heavy, and require independent cooling systems.

[0014] In existing technologies, land-based mobile emergency power supplies mainly use road-mounted wheeled power vehicles as carriers, providing emergency power to disaster-stricken areas through onboard generator sets. This approach is based on the convenience of road transport for wheeled vehicles and the availability of mature infrastructure. However, wheeled power vehicles are subject to strict limitations on load capacity and the radius of access roads to power-consuming sites, resulting in limited power generation capacity and difficulty in accommodating equipment for handling sudden load reductions. For example, in scenarios where roads are damaged after a disaster, wheeled power vehicles are unable to travel due to their reliance on paved roads, making it difficult to reach emergency power generation sites such as coastal power stations.

[0015] Compared to existing technologies, in this embodiment, by connecting the generator in series with the propulsion system of the hovercraft, the gas turbine, reducer, generator, and propulsion fan are connected in series in sequence. In the stationary power generation mode, the propulsion fan is used to generate reverse airflow for heat dissipation by rotating with a reverse pitch. When the generator load suddenly decreases, the propulsion fan pitch is increased by the pitch controller to supplement the suddenly reduced load power. At the same time, the pull generated by the propulsion fan is balanced by the fixed shovel at the bottom of the boat to maintain the stability of the entire vessel. This solves the problem that high-power mobile emergency power supplies in the prior art are limited in terms of accessibility and ability to cope with sudden load reduction.

[0016] In some implementations, refer to Figure 1 The hovercraft control method provided in this application embodiment can be based on the attached... Figure 1 The hovercraft structure shown is realized. The hovercraft includes a bridge and hull 13, a cabin 16, and a power transmission system installed in the cabin 16.

[0017] exist Figure 1 The power transmission system comprises a gas turbine 1, a reduction gear 2 (including couplings at both ends), a generator 3, and a propulsion fan 4, connected in series. The propulsion fan 4 is equipped with a pitch controller 8 for adjusting the pitch direction and magnitude of the propulsion fan 4. A rudder 5 is located behind the propulsion fan 4 for controlling the driving direction in driving mode. Propulsion airflow 6 from outside the cabin passes through the propulsion fan 4 and forms airflow 7 passing through the cabin.

[0018] exist Figure 1 The hovercraft also includes a lifting fan 9 and a clutch 10 for the lifting fan. The lifting fan 9 is driven by the gas turbine 1 through a reducer and downward output shaft. The lifting fan 9 supplies air to the bottom of the hull in operating mode to form an air cushion 12, generating lift to lift the hull off the ground. A fixed hoe 11 is provided on the bottom of the hull, located at the front, to generate unidirectional resistance when the air cushion 12 retracts and contacts the ground. Optionally, the fixed hoe 11 is triangular in structure and located at the front of the bottom, also used to generate unidirectional resistance when the air cushion 12 retracts and contacts the ground.

[0019] exist Figure 1 The hovercraft also includes a control cabinet and a fuel tank 14. The control cabinet is communicatively connected to the generator 3 and the pitch controller 8, respectively, and is used to detect the output load status of the generator 3 and send an increase pitch signal to the pitch controller 8 when a sudden decrease in load is detected.

[0020] In addition, the top of the gas turbine 1 is provided with a gas turbine exhaust pipe 15 and a gas turbine air inlet 18, and the wall of the cabin 16 is provided with a lubricating oil radiator vent 17, which is used to dissipate heat from the lubricating oil when the propulsion fan 4 generates airflow.

[0021] It should be noted that the hovercraft involved in the embodiments of this application can be a fully-cushioned hovercraft or a sidewall hovercraft, and its power source can be an aerospace-grade gas turbine or a marine gas turbine, with the power generation capacity configured to megawatts according to the needs of the emergency scenario. For example, the embodiments of this application can be used as an emergency power source for a coastal nuclear power plant.

[0022] Alternatively, the gas turbine and propulsion fan are connected via the aforementioned reducer and coupling. The generator is connected in series between the reducer and the propulsion fan, idling with the reducer in driving mode. That is, the shaft power output from the gas turbine is first adjusted for speed and torque by the reducer before being transmitted to the generator's shaft system, and further to the propulsion fan. Through this series arrangement, the gas turbine, reducer, generator, and propulsion fan can form a single power transmission link, allowing the hovercraft to share the main power equipment in both driving and stationary power generation states, thereby improving the integration of the power and power generation systems.

[0023] Alternatively, the input shaft of the reducer is connected to the output end of the gas turbine, one output shaft of the reducer is connected to the input end of the generator, and the other output shaft of the reducer is connected to the input end of the clutch (used to control the rotation of the lifting fan), thereby achieving the functions of deceleration and power distribution.

[0024] Specifically, gas turbines are characterized by their small size, light weight, and high power density, making them suitable as the primary power source for hovercraft. A gearbox is located between the gas turbine and the generator to adjust the high-speed output of the gas turbine to a speed range suitable for the generator and propulsion fan. A coupling is located between adjacent transmission components to transmit torque and compensate for installation errors, vibrations, or minor shaft misalignments, ensuring stable transmission between the gas turbine, gearbox, generator, and propulsion fan. Therefore, hovercraft do not require separate propulsion and power generation systems; instead, they utilize a single gas turbine powertrain for both propulsion and emergency power generation.

[0025] In driving mode, the generator is not energized or outputs electrical energy. At this time, the generator acts as a rotating follower component in the shaft system, idling with the reducer output. The shaft power output from the gas turbine is primarily used to drive the propulsion fan, and can simultaneously drive the hovering fan to form an air cushion, enabling the hovercraft to travel on water, mudflats, swamps, or unpaved roads. Because the generator does not bear the main power generation load in this state, its resistance to the transmission system is small and does not affect the propulsion fan's ability to generate propulsive airflow.

[0026] During operation, the propulsive airflow generated by the propulsion fan not only propels the hovercraft forward but also creates ventilation airflow through the hull, cooling the generator, gearbox, gas turbine, and related heat dissipation components inside the hull. This ensures that the generator remains in a well-ventilated environment even when rotating with the shaft in driving mode, improving equipment reliability and enabling the hovercraft to quickly switch to stationary power generation mode upon reaching an emergency site.

[0027] In stationary power generation mode, after the hovercraft reaches the target position, the lifting fan can be disengaged from the reducer via a clutch, the air cushion retracts, and the hull and bottom anchor point contact the ground. In this state, the control cabinet energizes the generator, switching it from idle to power generation. Most of the shaft power output from the gas turbine via the reducer is converted into electrical energy by the generator to supply power to external loads. Simultaneously, the propulsion fan remains connected to the generator shaft and continues to rotate, providing ventilation and cooling for the hull and adjustable mechanical load during sudden load reductions.

[0028] Because the generator is connected in series between the reducer and the propulsion fan, the propulsion fan can directly participate in shaft power balancing when stationary. When the external load is stable, the propulsion fan can maintain a small or appropriate pitch, mainly serving a ventilation and heat dissipation function. When the generator load suddenly decreases, the pitch controller can increase the propulsion fan pitch, allowing the propulsion fan to quickly increase its torque absorption and compensate for the reduced electrical load from the generator. Therefore, the propulsion fan is not only the propulsion device when the hovercraft is moving, but also a heat dissipation device when stationary and a device for responding to sudden load reductions.

[0029] The advantage of this arrangement is that the generator is integrated into the propulsion power chain, rather than being a separate external device. During operation, the generator idles with the shaft system, without affecting the hovercraft's rapid maneuverability. When generating electricity, the generator is directly connected to the same shaft system and outputs power, eliminating the need for relocation of the power source or complex mechanical switching. This structure fully utilizes the hovercraft's large payload capacity, high maneuverability, and the high power density of its gas turbines, making it suitable for use in disaster-stricken areas such as coastal power plants, nuclear power plants, or other large-scale emergency power supply scenarios where roads are damaged and ordinary power vehicles are difficult to access.

[0030] Reference Figure 2 , Figure 2 This is a flowchart illustrating a hovercraft control method provided in an embodiment of this application. The method can be executed by the hovercraft. The method includes the following steps: Step 201: In the static power generation mode, the clutch of the lifting fan is disengaged, the generator is energized, and the gas turbine drives the generator to generate electricity through the reducer. The gas turbine also drives the propulsion fan to rotate with a reverse pitch, generating a reverse airflow to cool the generator, reducer and gas turbine in sequence.

[0031] The stationary power generation mode refers to the operating state where the hovercraft stops moving and its primary function is power generation. In this mode, the hovercraft does not need to generate propulsion or lift, so the clutch of the lift fan is disengaged, causing the lift fan to stop rotating. After the lift fan stops rotating, the air cushion at the bottom of the hovercraft loses its air source and contracts, causing the hull to drop. The anchoring shovel at the bottom of the hull then contacts the ground, allowing the hovercraft to land stably on the ground.

[0032] In this embodiment, the gas turbine, reducer, generator, and propulsion fan are connected in series to form a complete transmission chain. The reducer is connected to the gas turbine and generator at both ends via couplings. In stationary power generation mode, after the generator is energized, most of the shaft power output from the gas turbine is transmitted to the generator through the reducer, driving the generator rotor to rotate and generate electricity. A portion of the shaft power continues to be transmitted to the propulsion fan, driving it to rotate.

[0033] Here, combined Figure 1 To explain, the gas turbine, reducer, generator, and propulsion fan mentioned above are connected in series. A series connection means that gas turbine 1, reducer 2, generator 3, and propulsion fan 4 share the same mechanical transmission shaft, with each component connected end-to-end to form a single power transmission path. Specifically, the output shaft of gas turbine 1 is connected to the input end of reducer 2 via a coupling. The output end of reducer 2 is then connected to the rotor shaft of generator 3 via another coupling. The end of the rotor shaft of generator 3 is directly connected to propulsion fan 4. The four components are arranged sequentially along the longitudinal direction of the ship's compartment 16 (e.g., ...). Figure 1 As shown, from the middle of the hull to the stern, the components are arranged in sequence: gas turbine 1, reducer 2, generator 3, and propulsion fan 4. This series configuration means that the shaft power output from gas turbine 1 must pass through reducer 2 and generator 3 sequentially before reaching propulsion fan 4. All components share the same rotational speed (after speed reduction by the reducer) and the same torque transmission link. Unlike the parallel configuration (where the gas turbine drives the generator and propulsion fan separately through independent drive shafts), in the series configuration, generator 3 is always in the transmission link. For example, when the hovercraft is moving (i.e., in driving mode), it is not energized and rotates freely on the shaft. When stationary and generating electricity, it is energized to absorb most of the shaft power, and the remaining power continues to be transmitted to propulsion fan 4.

[0034] Therefore, generator 3 does not require an independent power source and transmission mechanism, but is directly embedded in the transmission chain of the propulsion system. When the ship is in motion, it is transported as a load, and when the ship is generating electricity, it works as a power conversion device, thus realizing a high degree of integration and reuse of the propulsion system and the power generation system.

[0035] The reverse pitch refers to setting the propeller blade angle in the opposite direction to the pitch direction during operation. In operation mode, the propeller pitch direction causes airflow to be expelled from the inside of the hull to the outside, generating forward propulsion. In stationary power generation mode, after the pitch is set in reverse by the pitch controller, the airflow generated by the propeller is reversed, drawing in air from the outside of the hull and creating a reverse airflow that blows into the hull.

[0036] The reverse airflow generated by the propulsion fan flows sequentially through the generator, reducer, and gas turbine in the opposite direction of the drive chain, providing forced air cooling for these heat-generating components. Because the generator generates a large amount of heat during power generation due to copper and iron losses, the reducer generates heat due to gear meshing friction, and the gas turbine's casing temperature is high after the high-temperature gas performs work, continuous ventilation and heat dissipation are required to ensure that all components operate within a safe temperature range.

[0037] In some implementations, the reverse airflow exits the ship's hull after passing through the gas turbine. As the exiting airflow passes near the gas turbine's inlet, it flows in the intake direction, forming a protective airflow. Because the exhaust gas from the gas turbine's exhaust pipe is high in temperature and low in oxygen content, if this exhaust gas is drawn into the inlet, it will affect the gas turbine's combustion efficiency and may even cause flameout. This protective airflow isolates the exhaust gas from the inlet, preventing high-temperature, low-oxygen exhaust gas from flowing back into the inlet and ensuring the quality of the gas turbine's intake air.

[0038] In some implementations, the hovercraft's bulkhead is equipped with oil radiator vents. After passing through the gas turbine, the reverse airflow also passes through the oil radiator vents to cool the lubricating oil in the gearbox and gas turbine, maintaining the oil temperature within the normal operating range.

[0039] Through the above steps, this embodiment of the application utilizes the reverse pitch rotation of the propulsion fan to achieve forced ventilation and heat dissipation for all heat-generating components in the cabin, without the need for an additional independent ventilation system or water cooling system. The system structure is simple, and the heat dissipation airflow path covers the generator, reducer, gas turbine, and lubricating oil radiator, resulting in uniform and reliable heat dissipation.

[0040] In some embodiments, the exhaust pipe and air inlet of the gas turbine are respectively located on the top of the hovercraft's hull. Based on this, in step 201, driving the propulsion fan to rotate with a reverse pitch generates a reverse airflow to sequentially cool the generator, reducer, and gas turbine, including: In stationary power generation mode, the propeller pitch is reversed via the pitch controller, causing the reverse airflow generated by the propeller to be drawn in from the outside of the hull, flowing sequentially through the generator, reducer, and gas turbine before being discharged from the hull. As the discharged airflow passes through the gas turbine's inlet, it flows in the intake direction, isolating the exhaust gas from the gas turbine's exhaust pipe from the inlet.

[0041] In other words, in the static power generation mode, the propulsion fan generates a reverse airflow with a reverse pitch to form a protective airflow near the gas turbine's air inlet, preventing the high-temperature, low-oxygen exhaust gas discharged from the gas turbine's exhaust pipe from entering the air inlet.

[0042] Specifically, during operation, a gas turbine draws in air from the outside through its intake port for combustion, and the resulting high-temperature exhaust gas is discharged through its exhaust pipe. Since both the exhaust pipe and the intake port are located on the top of the ship's hull and are spatially adjacent, in the absence of external airflow interference, the exhaust gas discharged through the exhaust pipe may diffuse in the top area of ​​the hull and be re-drawn in through the intake port. The exhaust gas discharged through the exhaust pipe is high in temperature and has a significantly reduced oxygen content after combustion. If this exhaust gas is drawn into the intake port, it will cause the gas turbine's intake temperature to rise and its oxygen content to decrease, thereby reducing combustion efficiency. In severe cases, it may lead to unstable combustion or even flameout of the gas turbine.

[0043] In this embodiment, the reverse airflow generated by the reverse pitch rotation of the propeller fan is drawn in from the outside of the hull, flows along the drive chain through the various heat-generating components inside the hull, and is finally discharged from the hull. Since the exhaust direction is consistent with the intake direction of the gas turbine, the discharged airflow forms a continuously flowing layer of fresh air near the intake. This fresh air layer spatially isolates the high-temperature, low-oxygen exhaust gas from the exhaust pipe from the intake, ensuring that the intake always draws in fresh air from the outside rather than exhaust gas from the exhaust pipe. Therefore, without adding additional isolation devices or flow guiding structures, the airflow generated by the reverse pitch of the propeller fan alone is sufficient to protect the intake.

[0044] Optionally, the hovercraft's hull walls are equipped with oil radiator vents. The method of driving the propulsion fan to rotate in the opposite pitch, generating a reverse airflow to cool the generator, reducer, and gas turbine sequentially, further includes: in stationary power generation mode, the reverse airflow generated by the propulsion fan is drawn in from the outside of the hull, flows sequentially through the generator, reducer, gas turbine, and oil radiator vents, and then exits from the hull. In operating mode, the airflow generated by the propulsion fan enters from the outside of the hull, ventilates the equipment inside, flows through the hull, and exits through the oil radiator vents.

[0045] Specifically, the vent of the lubricating oil radiator is located on the ship's bulkhead, with the lubricating oil radiator connected to its inner side. The lubricating oil radiator is used to cool the lubricating oil circulating in the gearbox and gas turbine. After absorbing frictional heat at the gear meshing surfaces of the gearbox and the bearings of the gas turbine, the temperature of the lubricating oil rises. It needs to dissipate this heat to the outside air through the lubricating oil radiator to maintain the lubricating oil temperature within the normal operating range, ensuring lubrication effectiveness and equipment lifespan.

[0046] In stationary power generation mode, the reverse airflow generated by the propeller fan rotating in the opposite direction is drawn in from the outside of the hull and flows sequentially along the drivetrain through the generator, gearbox, and gas turbine, dissipating heat from these components. After passing the gas turbine, the airflow continues to flow, passing through the vents of the lubricating oil radiator located on the hull wall, carrying away heat from the surface of the lubricating oil radiator, and finally exiting from the hull. Thus, the reverse airflow simultaneously dissipates heat from all components of the drivetrain and the lubrication system during its single flow through the hull, eliminating the need for a separate fan or cooling pipes for the lubricating oil radiator.

[0047] In operating mode, the propulsion fan rotates with a forward pitch to generate thrust, and the airflow direction is opposite to that in stationary power generation mode. At this time, the propulsion airflow from outside the hull enters the hull from behind the propulsion fan, flowing over the surfaces of various equipment within the hull to ventilate and cool them. After flowing through the hull, the airflow exits through the vents of the lubricating oil cooler on the hull wall, carrying away heat from the surface of the lubricating oil cooler during the exit process, thus achieving cooling of the lubricating oil during operation.

[0048] As can be seen, regardless of whether it is in stationary power generation mode or in operating mode, the airflow generated by the propulsion fan passes through the vent of the lubricating oil radiator. The only difference is the direction of the airflow through the hull. In stationary power generation mode, the airflow is drawn in from the propulsion fan side, passes through the transmission chain, and is discharged through the vent. In operating mode, the airflow enters the hull from the propulsion fan side, flows through the internal equipment, and is discharged through the vent. In both modes, the lubricating oil radiator is located in the airflow path, achieving effective air cooling and ensuring temperature control of the lubrication system of the hovercraft under different operating conditions.

[0049] After introducing the static power generation mode, the following section will introduce the hovercraft's driving mode.

[0050] As an optional embodiment, in driving mode, the generator is controlled to idle without energizing and is driven by the reducer. The gas turbine drives the propulsion fan and the lift fan to rotate through the reducer. The propulsion force is adjusted by the pitch controller, and the driving direction is controlled by the rudder. If switching from driving mode to stationary power generation mode, the clutch of the lift fan is disengaged. After the air cushion retracts and the fixed hoe contacts the ground, the generator is energized.

[0051] Specifically, in operating mode, the generator is not energized and idles with the reducer. In this mode, the generator only acts as a load on the transmission chain, moving with the ship without generating electromagnetic drag torque or consuming shaft power. All shaft power output from the gas turbine drives the propulsion fan and lift fan respectively through the reducer. The lift fan supplies air to the hull to form an air cushion, generating lift to lift the hull off the ground. The propulsion fan generates propulsive airflow, and the pitch is adjusted by the pitch controller to control propulsion, while the rudder controls the direction of travel. In this mode, the airflow generated by the propulsion fan passes through the cabin, ventilating the equipment inside and cooling the lubricating oil through the vents of the lubricating oil radiators on the cabin walls.

[0052] When the hovercraft arrives at the emergency power generation site and needs to switch from driving mode to stationary power generation mode, the clutch of the lifting fan is first disengaged, causing the lifting fan to stop rotating. After the lifting fan stops, it no longer supplies air to the hull, and the air cushion gradually contracts due to the lack of air supply. The hull descends, and the anchoring shovel on the hull contacts the ground, allowing the hovercraft to land stably. Once the air cushion has fully contracted and the anchoring shovel is reliably in contact with the ground, the generator is then energized via the control cabinet, entering the stationary power generation state. This switching sequence ensures that when the generator is energized, the hull has landed stably via the anchoring shovel and can withstand the thrust generated by the increased propeller pitch when the load suddenly decreases.

[0053] Step 202: When a sudden load reduction is detected in the generator, the pitch of the propulsion fan is increased by the pitch controller to increase the load torque generated by the propulsion fan to compensate for the sudden load reduction and prevent the gas turbine from overspeeding.

[0054] In this embodiment, the air cushion is compressed when the lifting fan stops rotating, and the hull of the hovercraft contacts the ground through a fixed hoe. The unidirectional resistance generated by the fixed hoe balances the pulling force generated after the propulsion fan pitch increases, so as to maintain the stability of the entire ship.

[0055] In static power generation mode, the lifting fan stops rotating and no longer supplies air to the hull air cushion because the clutch of the lifting fan is disengaged. After losing its air source, the air cushion gradually contracts, and the hull descends until the fixed shovel on the bottom of the hull contacts the ground, and the hovercraft changes from a hovering state to a landing state.

[0056] The fixed shovel has a triangular structure and is located on the front side of the hull. The triangular cross-section of the fixed shovel causes it to generate only unidirectional resistance when in contact with the ground, that is, it can only resist the force in the rearward direction (the direction of the propulsion fan pull) and will not constrain the hull in other directions.

[0057] When a sudden load reduction occurs and the pitch controller increases the propeller fan pitch, the propeller fan generates increased load torque while also exerting a significant rearward pull on the entire vessel. Because the fixed shovel is located on the forward side of the hull, the hovercraft forms a certain angle with the ground when the air cushion retracts and touches down. The rearward pull generated by the propeller fan is decomposed along this angle into a component parallel to the ground and a component pointing towards the ground. The component pointing towards the ground increases the normal force exerted by the hull on the ground, which in turn increases the friction and embedment resistance between the fixed shovel and the ground. Therefore, the resistance generated by the fixed shovel on the hull adaptively increases with the increase in propeller fan pull, always balancing the pull generated by the increased propeller fan pitch, maintaining the stability of the entire vessel during sudden load changes, and preventing displacement or capsizing.

[0058] Based on the above principles, refer to Figure 3 The schematic diagram illustrates the motion principle of a hovercraft, assuming the fixed shovel is a triangular structure positioned at the front of the hull. The triangular cross-section of the fixed shovel causes it to generate only unidirectional resistance when in contact with the ground, meaning it can only resist forces in the rearward direction (the direction of the propulsion fan's pull), without constraining the hull in other directions.

[0059] like Figure 3 As shown, when a sudden load reduction occurs and the pitch controller increases the propeller fan pitch, the propeller fan generates increased load torque while also exerting a significant rearward pull on the entire ship. Figure 3 The arrow on the right side indicates fan pull. Because the fixed shovel is positioned at the front of the hull, the hovercraft forms an angle with the ground when the air cushion retracts and touches down, with the front of the hull lower than the rear. The fixed shovel generates forward-pointing resistance after embedding itself in the ground. Figure 3 The left-hand arrow (marked as the fixed hoe resistance) is in the opposite direction to the backward pull generated by the propulsion fan.

[0060] Depend on Figure 3 It can be seen that the rearward thrust generated by the propeller fan is decomposed into a component parallel to the ground and a component pointing towards the ground along the hull's tilt direction. The component pointing towards the ground increases the normal force exerted by the hull on the ground, which in turn increases the friction and embedment resistance between the fixed shovel and the ground. Therefore, the resistance generated by the fixed shovel on the hull increases adaptively with the increase of the propeller fan thrust, always balancing the thrust generated by the increase in propeller fan pitch, maintaining the stability of the entire vessel during sudden load changes, and preventing hull displacement or capsizing.

[0061] In this embodiment, a sudden load reduction refers to a situation where the external electrical load suddenly decreases significantly or completely drops during normal generator operation. When a sudden load reduction occurs, the generator's electromagnetic drag torque drops sharply, while the gas turbine's output power cannot decrease synchronously in a short time due to thermal inertia and the response delay of the fuel supply system. At this time, the shaft power output by the gas turbine exceeds the power consumed by the load on the drive train, and the excess power is converted into rotational kinetic energy of the rotor system, causing the speed to rise rapidly. If measures are not taken in time to replenish the load, the gas turbine speed will exceed the maximum permissible speed, i.e., overspeeding occurs, which may cause serious mechanical accidents such as blade breakage and bearing damage.

[0062] In this embodiment, the hovercraft is equipped with a control cabinet, which is communicatively connected to both the generator and the pitch controller. The control cabinet monitors the generator's output load status in real time. When a sudden decrease in the generator's output load is detected, the control cabinet sends an increase pitch signal to the pitch controller. In response to this increase pitch signal, the pitch controller increases the pitch of the propulsion fan.

[0063] Increasing the blade pitch refers to increasing the installation angle of the propeller fan blades, thus increasing the angle between the blades and the plane of rotation. With an increased blade pitch, the amount of air propelled by the propeller fan per revolution increases, and the aerodynamic drag torque increases accordingly, meaning the load torque exerted by the propeller fan on the drive shaft increases. This increased load torque compensates for the electromagnetic drag torque suddenly reduced due to the shedding of external load, allowing the total load power in the drive train to rematch with the output power of the gas turbine, thereby suppressing speed increases and preventing the gas turbine from overspeeding.

[0064] In some implementations, the pitch controller determines the target pitch of the propulsion fan based on the load reduction carried in the increased pitch signal, so that the increased load torque of the propulsion fan matches the torque corresponding to the load reduction. Thus, the above steps achieve corresponding control between the pitch increment and the load reduction, preventing insufficient pitch adjustment from causing the gas turbine to still overspeed, or excessive pitch adjustment from causing a sudden drop in gas turbine speed.

[0065] In this embodiment, during the absorption of sudden power reduction, the propulsion fan directly converts the shaft power output by the gas turbine into the kinetic and internal energy of the air. Unlike the prior art that uses a load box to dissipate excess power through resistive heating, when the propulsion fan acts as a power-consuming device, the large amount of airflow it drives can itself dissipate heat for the propulsion fan and the equipment inside the ship's cabin, eliminating the need for additional cooling auxiliary equipment.

[0066] In some embodiments, the fixed hoe has a triangular structure and is positioned at the front of the hull. When the hovercraft retracts and touches down, the hull forms an angle with the ground. The rearward pull generated by the propulsion fan is decomposed along the angle into a component parallel to the ground and a component pointing towards the ground. The resistance exerted by the fixed hoe on the hull increases adaptively with the increase of the propulsion fan's pull.

[0067] Specifically, the fixed shovel can be a triangular, wedge-shaped, or rigid component with a ramped guide structure. The apex or edge of the triangular structure is positioned towards the ground, allowing it to insert, press into, or abut against the ground surface when the hull lands. For muddy, sandy, tidal flat, unpaved roads, or loose post-disaster ground, the fixed shovel can create mechanical interlocking resistance by partially embedding itself in the ground. For harder ground, the fixed shovel can generate significant frictional resistance and supporting reaction force through its ramps, edges, or bottom contact surface. Thus, the fixed shovel not only limits the horizontal displacement of the hovercraft during stationary power generation but also counteracts the rearward pull on the entire hull when the propulsion fan generates reverse airflow.

[0068] Furthermore, since the fixed shovel is located on the front side of the hull, when the air cushion retracts, the hull is not completely horizontally in contact with the ground. Instead, the area near the fixed shovel serves as one of the main support points, causing the hull to form a certain angle of inclination relative to the ground. At this time, the axis of the propulsion fan tilts accordingly with the hull relative to the ground. When the propulsion fan is adjusted to reverse propulsion or reverse airflow mode via the pitch controller while stationary and generating electricity, the airflow it generates is blown into the hull to ventilate and cool components such as the generator, reducer, gas turbine, and lubricating oil radiator vents. Simultaneously, the propulsion fan generates a rearward pull on the hull. Due to the angle of inclination between the hull and the ground, this rearward pull can be decomposed into a component parallel to the ground and a component pointing towards the ground. The component parallel to the ground tends to push the hovercraft backward, while the component pointing towards the ground increases the pressure of the hull and the fixed shovel on the ground.

[0069] Therefore, as the thrust of the propulsion fan increases, the normal clamping force on the fixed shovel increases synchronously, causing a corresponding increase in the frictional resistance, embedding resistance, or mechanical engagement resistance between the fixed shovel and the ground. In other words, the resistance generated by the fixed shovel on the hull can passively and adaptively increase with the increase of the propulsion fan thrust, thus forming a stable limiting effect without the need for an additional drive mechanism. This structure is particularly suitable for operating conditions where the generator load suddenly decreases. For example, when the external electrical load suddenly decreases, the control cabinet sends an increase pitch signal to the pitch controller, causing the propulsion fan to quickly increase its absorption torque to supplement the suddenly reduced generator load and suppress the gas turbine from running over. At the same time, the thrust generated by the propulsion fan on the entire vessel will also increase accordingly, while the fixed shovel generates greater ground resistance due to the greater downforce, thus enabling the hovercraft to remain stationary and stable during the sudden load reduction process.

[0070] Through the aforementioned structure, the fixed shovel works in conjunction with the propulsion fan, pitch controller, and the retracted grounding state of the air cushion: on the one hand, the propulsion fan serves as both a ventilation and heat dissipation device when generating electricity at rest and a rapid power consumption device during sudden load reduction. On the other hand, the fixed shovel utilizes the tilted attitude of the hull after grounding to convert the increased pull of the propulsion fan into greater ground clamping force and limiting resistance. This method eliminates the need for additional high-power braking devices, external anchoring devices, or complex hydraulic outriggers, achieving coordinated hull stability, equipment heat dissipation, and load reduction protection at emergency power generation sites.

[0071] In some embodiments, the hovercraft is also equipped with a control cabinet. Optionally, the control cabinet is communicatively connected to the generator, the pitch controller, and the gas turbine speed or operating status detection device, respectively. Based on this, in step 202, when a sudden load reduction is detected in the generator, the pitch of the propulsion fan is increased via the pitch controller, including: the control cabinet detects a sudden reduction in the output load of the generator and sends a pitch increase signal to the pitch controller; the pitch controller responds to the pitch increase signal and increases the pitch of the propulsion fan.

[0072] Specifically, in the stationary power generation state, the air cushion fan disengages via a clutch, the air cushion retracts, and the hull and bottom anchor points contact the ground. At this time, the gas turbine drives the generator via a gearbox to generate electricity, simultaneously driving the propulsion fan to rotate. Under the control of the pitch controller, the propulsion fan operates in reverse or anti-pitch mode, allowing airflow into the hull and sequentially ventilating and cooling the generator, gearbox, gas turbine, and oil cooler vents. When the external electrical load remains stable, the generator absorbs most of the shaft power output from the gas turbine, and the propulsion fan only performs ventilation, cooling, and some auxiliary load functions.

[0073] When the control cabinet detects a sudden decrease in the generator's output load, it indicates a sudden reduction in external electrical load, causing a corresponding decrease in the electromagnetic braking torque of the generator on the gas turbine's output shaft. If other power-consuming devices are not added promptly, the gas turbine's output power cannot decrease synchronously within a short period, easily leading to a rapid increase in the rotational speed of the gas turbine, reducer, generator, and propulsion fan's transmission system. Therefore, in this step, the control cabinet sends an increase pitch signal to the pitch controller. In response to this signal, the pitch controller increases the propulsion fan's pitch, causing a rapid increase in the propulsion fan's air resistance torque and absorbed torque.

[0074] With an increased propeller pitch, the gas turbine output shaft experiences a greater mechanical load, compensating for the reduced load on the generator caused by a sudden decrease in external load, allowing the gas turbine's output power to continue to be consumed. Simultaneously, the reverse airflow and kinetic energy generated by the propeller also increase, directly converting the gas turbine's excess output power into the kinetic and internal energy of the air. Since the propeller itself is a high-flow-rate aerodynamic device, it can maintain or enhance ventilation and cooling of equipment within the ship's cabin while absorbing sudden load reductions, thus eliminating the need for external energy-consuming equipment such as large-capacity load cells.

[0075] Further optionally, one method for the control cabinet to detect a sudden decrease in the output load of the generator can be that the control cabinet monitors the output power or output current of the generator in real time, and when the decrease in the output power or output current exceeds a preset sudden decrease threshold and the rate of decrease exceeds a preset speed threshold, it is determined that the generator has experienced a sudden load decrease.

[0076] For example, the control cabinet can calculate the output active power based on the generator's voltage, current, and power factor, or it can directly acquire the power detection signal from the generator's output terminal. When the output power rapidly decreases from a higher load level to a lower load level, and this decrease is not a slow change as is typical during normal regulation, the control cabinet triggers the load reduction response logic.

[0077] Furthermore, the control cabinet can also detect a sudden decrease in the generator's output load by monitoring the generator's output frequency, generator speed, or gas turbine output shaft speed in real time. When the external load suddenly decreases, the generator's electromagnetic resistance torque decreases, and the transmission system exhibits an acceleration trend. Therefore, the generator's output frequency, generator speed, or gas turbine output shaft speed will increase within a short period. The control cabinet can determine that a sudden load decrease has occurred when it detects that the increase in the output frequency or speed exceeds a preset increase threshold, and / or the increase rate exceeds a preset acceleration threshold, and sends an increase pitch signal to the pitch controller.

[0078] In other embodiments, the control cabinet can also determine a sudden load reduction based on the status signals of external load switches, circuit breakers, grid-connected switches, or load-side protection devices. When a circuit breaker in the external load circuit trips, a portion of the load branch is disconnected, or the load-side control system sends a load disconnection signal to the control cabinet, the control cabinet can use this status signal as one of the criteria for determining a sudden load reduction. Preferably, the control cabinet can combine this status signal with generator output power, output current, or speed change signals to avoid malfunctions caused by fluctuations or short-term disturbances in a single sensor.

[0079] In some implementations, the control cabinet can also identify sudden load reductions by comparing the output status of the gas turbine with the electrical output status of the generator. For example, when the gas turbine's fuel supply, speed command, or output power command remains essentially constant for a short period, while the generator's output power or output current suddenly drops, it indicates that the gas turbine is still providing high shaft power to the drive system, but the electrical power absorbed by the generator has significantly decreased. In this case, the control cabinet can determine that a sudden load reduction has occurred. This method can reflect the power imbalance between the gas turbine's mechanical output and the generator's electrical load, and is suitable for rapidly triggering propeller fan pitch increase control.

[0080] Furthermore, after determining that the generator has experienced a sudden load reduction, the control cabinet can determine the increase in propeller fan pitch based on the magnitude of the load reduction. When the load reduction is small, the control cabinet can send a small pitch increase signal to the pitch controller, causing the propeller fan to moderately increase its power absorption. When the load reduction is large, the control cabinet can send a large pitch increase signal to the pitch controller, causing the propeller fan to quickly enter a larger pitch state to absorb more shaft power in a shorter time. Therefore, the propeller fan can serve not only as a ventilation and cooling device during static power generation but also as a rapidly adjustable mechanical load during sudden load reductions in the generator.

[0081] Alternatively, during the increase of the propeller fan pitch, the control cabinet can continue to monitor the generator output frequency, gas turbine speed, or transmission system speed. When the upward trend in speed is detected to be suppressed, or the generator output frequency returns to the allowable range, the control cabinet can maintain the current pitch, or gradually reduce the propeller fan pitch according to the stable state after the gas turbine power reduction. This closed-loop regulation method can avoid the gas turbine speed from dropping too quickly due to an excessive increase in the propeller fan pitch at once, and can also avoid insufficient pitch increase from failing to effectively suppress overspeed.

[0082] Through the aforementioned control methods, the control cabinet, pitch controller, propeller fan, and generator form a load reduction response system. When the external load on the generator suddenly decreases, the control cabinet can quickly identify the load reduction and adjust the propeller fan to a higher power absorption state via the pitch controller, allowing the propeller fan to consume the remaining output power of the gas turbine. Combined with the restraining effect of the hull-mounted shovels on the hull when stationary during power generation, even if the propeller fan generates a large reverse pull due to the increased pitch, the hovercraft can still maintain stability, thus ensuring the safe operation of the emergency power generation equipment under load reduction conditions.

[0083] Optionally, in the above steps, the pitch controller, in response to the increased pitch signal, increases the pitch of the propulsion fan, including: the pitch controller determining the target pitch of the propulsion fan based on the load reduction carried in the increased pitch signal, wherein the increased load torque of the propulsion fan matches the torque corresponding to the load reduction. The load reduction can represent a decrease in generator output power, a decrease in output current, or a decrease in shaft load torque calculated by the control cabinet based on the generator output status.

[0084] Specifically, in a stationary power generation state, the gas turbine simultaneously drives the generator and the propulsion fan via a reducer. When the external load on the generator suddenly decreases, the electromagnetic drag torque of the generator on the shaft system decreases accordingly. The power previously absorbed by the generator on the shaft system is suddenly released, which can easily cause an increase in the speed of the gas turbine and drive shaft system. At this time, the control cabinet can estimate the torque reduction corresponding to the sudden load reduction based on the decrease in generator output power and the current shaft speed, and send this load reduction or torque reduction in a pitch increase signal to the pitch controller. The pitch controller then determines the target pitch for the propulsion fan, ensuring that the air drag torque of the propulsion fan after increasing the pitch matches, or at least partially matches, the torque corresponding to the sudden load reduction.

[0085] As the pitch of the propeller fan increases, its blades' ability to do work on the air strengthens, leading to a corresponding increase in the shaft power absorbed and the load torque generated by the propeller fan. Therefore, the load reduction in the generator due to a sudden decrease in external load can be compensated by the increased aerodynamic load from the propeller fan. The remaining shaft power output by the gas turbine is no longer primarily manifested as shaft acceleration, but is converted into the kinetic and internal energy of the air by the propeller fan. Combined with the implementation method of the propeller fan for ventilation, heat dissipation, and load surge response in the static power generation state in the embodiments of this application, this control method enables the propeller fan to function as both a cooling device and a rapid energy dissipation device.

[0086] In some implementations, the pitch controller can pre-store the correspondence between load reduction and target pitch. This correspondence can be pre-calibrated based on the propeller fan's aerodynamic characteristics, current speed, blade structure parameters, and gas turbine output characteristics. When the load reduction carried in the increased pitch signal is small, the pitch controller determines a smaller target pitch increment; when the load reduction is large, the pitch controller determines a larger target pitch increment. In this way, the increase in propeller fan power absorption can be matched to the decrease in generator load, avoiding insufficient pitch adjustment leading to inadequate overspeed suppression, and also avoiding excessive pitch adjustment leading to a rapid decrease in shaft speed.

[0087] Furthermore, the pitch controller can also increase the propulsion fan pitch in response to the increased pitch signal by: the pitch controller querying a preset pitch control table based on the current propulsion fan speed, current pitch, generator load reduction, and gas turbine operating status. The preset pitch control table may include target pitches or pitch increments corresponding to different speed ranges and different load reduction ranges. After obtaining the target pitch, the pitch controller controls the propulsion fan to increase the pitch at a preset adjustment rate, gradually bringing the propulsion fan into a power absorption state that matches the current load reduction condition.

[0088] In some embodiments, increasing the pitch of the propulsion fan via the pitch controller to increase the load torque generated by the propulsion fan to compensate for the sudden decrease in load power further includes: when the pitch of the propulsion fan increases, the propulsion fan absorbs the shaft power output by the gas turbine and directly converts the shaft power into the kinetic and internal energy of the air to replace the external load box in consuming the sudden decrease in load power, and dissipates heat from the propulsion fan itself and the equipment inside the ship's cabin without the need to connect external auxiliary cooling equipment.

[0089] This can be understood as follows: after a sudden load reduction in the generator, the pitch controller adjusts the blade angle of the propulsion fan based on the increased pitch signal from the control cabinet, causing the propulsion fan to generate a greater air resistance torque at the same or similar speed. Since the propulsion fan, gas turbine, reducer, and generator are located in the same transmission link, the increased propulsion fan pitch leads to an increased load torque on the transmission shaft system, thereby quickly compensating for the reduced electromagnetic load on the generator caused by the sudden decrease in external load.

[0090] Specifically, when the external electrical load suddenly decreases, the generator's output power drops, and the electromagnetic braking torque exerted by the generator on the gas turbine's output shaft decreases. At this time, the gas turbine may still maintain its original fuel supply or output power for a short period. If there are no other power consumption pathways, the shaft system containing the gas turbine, generator, and propulsion fan is prone to an increase in speed. By increasing the propulsion fan pitch, the propulsion fan's power absorption increases rapidly, causing some of the power originally consumed by the external electrical load to be consumed by the propulsion fan, thereby suppressing shaft overspeed.

[0091] In the above implementation process, the propulsion fan does not absorb additional electrical energy, but rather directly absorbs the mechanical shaft power output by the gas turbine. As the propulsion fan pitch increases, the work done by the blades on the air increases, and more shaft power is converted into the kinetic energy, pressure energy, and internal energy generated by airflow disturbances. Therefore, the gas turbine's surplus output power can be directly released into the air through the propulsion fan, without first being converted into electrical energy by a generator and then into heat by an external load box.

[0092] Compared to using an external load cell, the propulsion fan, as a power-consuming device, offers advantages such as high structural integration, short response chain, and superior cooling. External load cells typically require large resistive loads, switching devices, cable connections, and cooling fans, which increases equipment weight and layout space in high-power emergency power generation scenarios, and necessitates additional consideration of the load cell's own heat dissipation. In this embodiment, however, the propulsion fan is already integrated into the hovercraft's propulsion system, eliminating the need for additional large-mass energy-consuming equipment and better adapting to the compact layout requirements of a hovercraft as a mobile emergency power source.

[0093] Furthermore, when absorbing power from a sudden load reduction, the propulsion fan generates an increased airflow rate and velocity. This airflow creates an enhanced ventilation path within the ship's hull, providing convective cooling to the generator, gearbox, gas turbine, oil cooler vents, and related transmission components. In other words, while acting as a device to cope with sudden load reductions, the propulsion fan also functions as a hull ventilation and equipment cooling system, allowing the consumed remaining shaft power to be expelled from the hull through airflow and heat diffusion.

[0094] In a stationary power generation state, the propulsion fan can operate in reverse or anti-pitch mode, allowing airflow to enter the hull and sequentially flow through the generator, gearbox, gas turbine, and oil radiator vents. As the pitch increases, the airflow's heat transfer capacity to these surfaces enhances, effectively removing heat generated by the generator windings, gearbox lubrication system, external gas turbine components, and oil radiator. Therefore, even with a sudden reduction in generator load and the propulsion fan absorbing a large amount of residual shaft power for a short period, the propulsion fan itself and the main equipment within the hull can still achieve continuous cooling.

[0095] Alternatively, the airflow generated by the propulsion fan can also create a protective flow field near the gas turbine inlet, preventing the high-temperature, low-oxygen exhaust gas discharged from the gas turbine exhaust pipe from flowing back to the gas turbine inlet. Thus, during a sudden load reduction, increasing the propulsion fan pitch not only increases the mechanical load but also enhances cabin ventilation and intake protection, thereby ensuring the intake quality and operational stability of the gas turbine during load changes.

[0096] Because the propulsion fan is directly connected to the shaft drive, the increase in its load torque can be quickly applied to the gas turbine output. Compared to consuming electrical power through an external load cell, this mechanical absorption method reduces electrical switching, load connection, and external cooling, which is beneficial for forming an effective braking load in a short time after a sudden load reduction. For high-power emergency power generation equipment, this method can reduce system complexity and improve the reliability of responding to sudden load reductions.

[0097] Furthermore, the control cabinet can adjust the increase in propeller pitch based on the magnitude of the sudden load reduction, ensuring that the increased load torque matches the reduced load power. When the sudden load reduction is small, the propeller only needs to moderately increase its pitch to compensate for the small power shortfall. When the sudden load reduction is large, the propeller can quickly enter a larger pitch state to absorb more power from the gas turbine output shaft. In this way, the propeller can avoid both insufficient power absorption leading to an increase in shaft speed and excessive power absorption causing a rapid decrease in gas turbine speed.

[0098] In some alternative implementations, as the gas turbine's fuel control system gradually reduces its output power, the control cabinet can also gradually reduce the propeller fan pitch via the pitch controller, so that the shaft power absorbed by the propeller fan is adapted to the output state of the gas turbine after power reduction. Thus, the propeller fan quickly takes over the remaining shaft power in the initial stage of a sudden load reduction, and gradually returns to a suitable operating state for ventilation and heat dissipation after the system stabilizes, thereby achieving a balance between emergency power absorption and stable operation.

[0099] Through the above implementation, the propulsion fan, in its stationary power generation state, not only serves as a ventilation and heat dissipation device for the ship's cabin but also functions as a rapidly adjustable mechanical load. When the external load on the generator suddenly decreases, the propulsion fan directly absorbs the remaining shaft power output from the gas turbine by increasing its pitch, converting this shaft power into the kinetic and internal energy of the air, thereby replacing the external load box to consume power. Simultaneously, the high-volume airflow generated by the propulsion fan can dissipate heat for itself and the equipment inside the cabin, eliminating the need for external auxiliary cooling equipment. This improves the mobility, integration, and load reduction response capability of the emergency power-assisted hovercraft.

[0100] In this embodiment, the gas turbine, reducer, generator, and propulsion fan are connected in series by incorporating a generator into the hovercraft's propulsion system. In stationary power generation mode, the propulsion fan rotates with a reverse pitch to generate reverse airflow for cooling. When the generator load suddenly decreases, the propulsion fan pitch is increased by a pitch controller to compensate for the reduced load power. Since this embodiment reuses the hovercraft's own propulsion fan as both a ventilation and cooling device for the generator set and a load reduction response device, instead of requiring an additional independent load box and cooling system on the wheeled power vehicle as in the prior art, this embodiment eliminates the need for additional load reduction response space. This allows it to overcome the regulatory load limits for wheeled power vehicles and achieve mobile emergency power generation with a higher power rating. As can be seen, in this embodiment, the propulsion fan absorbs the reduced power while directly converting the shaft power output from the gas turbine into the kinetic and internal energy of the air. The airflow it drives is sufficient for cooling, resulting in a simple system structure and highly integrated functionality. Because hovercraft can travel on water, swamps, and unpaved roads without relying on paved roads, and because a fixed hoe on the bottom of the boat generates unidirectional resistance to balance the thrust generated by the increased pitch of the propeller fan when the load suddenly decreases, the emergency generator hovercraft obtained in this application can achieve an ideal effect in responding to sudden load decreases. It can effectively solve the problem that high-power mobile emergency power supplies in the prior art are limited in terms of accessibility and load decrease response capabilities.

[0101] The above describes a hovercraft control method in the embodiments of this application. The hovercraft that implements the above hovercraft control method will be described below.

[0102] The hovercraft in this embodiment can achieve the above-mentioned... Figure 2 The steps of the hovercraft control method executed in the corresponding embodiments are described below. The functions implemented by the hovercraft can be achieved through hardware or through hardware executing corresponding software. The hardware or software includes one or more modules corresponding to the above functions, and the modules can be software and / or hardware. The implementation of the hovercraft's functions can be referred to... Figure 2 The operations performed in the corresponding embodiments are similar to those described above, and will not be repeated here.

[0103] In some implementations, a gas turbine is used to provide shaft power; The reducer has an input shaft connected to the output end of the gas turbine, one output shaft connected to the generator input end, and the other output shaft connected to the clutch input end for deceleration and power distribution. The clutch is used to control the rotation of the lifting fan. A generator, connected to the output end of the reducer, is used to convert shaft power into electrical energy under energized conditions; A propulsion fan is connected to the output end of the generator and is equipped with a pitch controller, which is used to adjust the pitch direction and size of the propulsion fan. The lift fan is driven by the gas turbine through a reducer to output a downward shaft and is connected to the gas turbine via a clutch. It is used to generate air cushion lift in driving mode. The fixed hoe, located on the front side of the hull, has a triangular structure and is used to generate unidirectional resistance when it comes into contact with the ground when the lifting fan stops or the hull lands. The control cabinet is communicatively connected to the generator and the pitch controller, respectively, and is used to send an increase pitch signal to the pitch controller when a sudden decrease in the load of the generator is detected, so as to increase the load torque of the propulsion fan to compensate for the sudden decrease in load power; The gas turbine, reducer, generator, and propulsion fan are connected in series. In the static power generation mode, the propulsion fan rotates with a reverse pitch to generate a reverse airflow, which cools the generator, reducer, and gas turbine in sequence. The resistance generated by the fixed hoe increases with the increase of the propulsion fan's thrust, in order to balance the thrust generated by the increase of the propulsion fan's pitch when the load suddenly decreases.

[0104] In this embodiment, the hovercraft is constructed by connecting a gas turbine, a reducer, a generator, and a propulsion fan in series. It is equipped with a pitch controller for adjusting the propulsion fan pitch, a lifting fan for buoyancy, a fixed hoe for landing limit, and a control cabinet for detecting generator load changes and controlling pitch adjustment. In driving mode, the hovercraft can be rapidly maneuvered using the gas turbine. In stationary power generation mode, the same power chain drives the generator to output electrical energy. When the generator load suddenly decreases, the propulsion fan pitch is increased to rapidly increase the propulsion fan's load torque, absorbing the remaining shaft power output by the gas turbine. Simultaneously, the ground resistance of the fixed hoe, which increases with the propulsion fan's thrust, maintains the hull's stability. Thus, the hovercraft possesses the capabilities of rapid arrival at emergency sites, high-power generation, load reduction suppression, equipment heat dissipation, and stationary stability, improving the integration, environmental adaptability, and operational safety of emergency power generation equipment.

[0105] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0106] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working processes of the systems, devices, and modules described above can be referred to the corresponding processes in the foregoing method embodiments, and will not be repeated here.

[0107] In the embodiments provided in this application, it should be understood that the disclosed systems, apparatuses, and methods can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of modules is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple modules or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be indirect coupling or communication connection through some interfaces, apparatuses, or modules, and may be electrical, mechanical, or other forms.

[0108] The modules described as separate components may or may not be physically separate. The components shown as modules may or may not be physical modules; that is, they may be located in one place or distributed across multiple network modules. Some or all of the modules can be selected to achieve the purpose of this embodiment according to actual needs.

[0109] Furthermore, the functional modules in the various embodiments of this application can be integrated into one processing module, or each module can exist physically separately, or two or more modules can be integrated into one module. The integrated module can be implemented in hardware or as a software functional module. If the integrated module is implemented as a software functional module and sold or used as an independent product, it can be stored in a computer-readable storage medium.

[0110] In the above embodiments, implementation can be achieved, in whole or in part, through software, hardware, firmware, or any combination thereof. When implemented in software, it can be implemented, in whole or in part, as a computer program product.

[0111] The technical solutions provided in the embodiments of this application have been described in detail above. Specific examples have been used in the embodiments of this application to illustrate the principles and implementation methods of the embodiments of this application. The description of the above embodiments is only for the purpose of helping to understand the methods and core ideas of the embodiments of this application. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of the embodiments of this application. Therefore, the content of this specification should not be construed as a limitation on the embodiments of this application.

Claims

1. A method for controlling a hovercraft, characterized in that, The hovercraft is used in emergency power generation scenarios. The hovercraft includes a gas turbine, a reducer, a generator, and a propulsion fan connected in series. The propulsion fan is equipped with a pitch controller. The hovercraft also includes a lifting fan driven by the gas turbine through a downward output shaft of the reducer, and a fixed hoe installed on the bottom of the hull. The lifting fan is equipped with a clutch. The method includes: In the static power generation mode, the clutch of the lifting fan is disengaged, the generator is energized, and the gas turbine drives the generator to generate electricity through the reducer. The gas turbine also drives the propulsion fan to rotate with a reverse pitch, generating a reverse airflow to cool the generator, reducer and gas turbine in sequence. When a sudden load reduction is detected in the generator, the pitch of the propulsion fan is increased by the pitch controller, thereby increasing the load torque generated by the propulsion fan to compensate for the sudden load reduction and prevent the gas turbine from overspeeding. In this process, the air cushion is deflating when the lifting fan stops, and the hull of the hovercraft contacts the ground through the fixed hoe. The unidirectional resistance generated by the fixed hoe balances the pulling force generated by the increased pitch of the propulsion fan, thus maintaining the stability of the entire vessel.

2. The hovercraft control method according to claim 1, characterized in that, The method further includes: In driving mode, the generator is de-energized and idles with the reducer. The gas turbine drives the propulsion fan and the lift fan to rotate through the reducer. The propulsion force is adjusted by the pitch controller and the driving direction is controlled by the rudder. If switching from the driving mode to the stationary power generation mode, the clutch of the lifting fan is disengaged, and after the air cushion contracts and the fixed hoe contacts the ground, the generator is energized.

3. The hovercraft control method according to claim 1, characterized in that, The fixed hoe has a triangular structure and is located on the front side of the bottom of the boat. When the air cushion retracts and touches the ground, the hull of the hovercraft forms an angle with the ground. The backward pull generated by the propulsion fan is decomposed into a component parallel to the ground and a component pointing towards the ground along the included angle direction, and the resistance generated by the fixed hoe on the hull increases adaptively with the increase of the propulsion fan pull.

4. The hovercraft control method according to claim 1, characterized in that, The exhaust pipe and air inlet of the gas turbine are respectively located on the top of the cabin of the hovercraft; The method of driving the propulsion fan to rotate with a reverse pitch to generate a reverse airflow to cool the generator, reducer, and gas turbine in sequence includes: In the static power generation mode, the pitch of the propulsion fan is set to reverse by the pitch controller, so that the reverse airflow generated by the propulsion fan is drawn in from the outside of the cabin, flows through the generator, reducer and gas turbine in sequence and is discharged from the cabin. When the exhaust gas flows through the gas turbine's inlet, it flows in the intake direction, isolating the exhaust gas from the gas turbine's exhaust pipe from the inlet.

5. The hovercraft control method according to claim 1, characterized in that, The hovercraft is equipped with a lubricating oil radiator ventilation port on its cabin wall. The method of driving the propulsion fan to rotate with a reverse pitch to generate a reverse airflow to cool the generator, reducer, and gas turbine in sequence also includes: In the static power generation mode, the reverse airflow generated by the propulsion fan is drawn in from the outside of the cabin, flows through the generator, reducer, gas turbine and lubricating oil radiator vent in sequence and then is discharged from the cabin. In driving mode, the airflow generated by the propulsion fan enters from the outside of the cabin to ventilate the equipment inside the cabin, and then flows out through the air exchange port of the lubricating oil radiator after passing through the interior of the cabin.

6. The hovercraft control method according to claim 1, characterized in that, The hovercraft is also equipped with a control cabinet; the step of increasing the pitch of the propulsion fan via the pitch controller when a sudden load reduction of the generator is detected includes: The control cabinet detects a sudden decrease in the output load of the generator and sends an increase pitch signal to the pitch controller; The pitch controller responds to the increased pitch signal by increasing the pitch of the propulsion fan.

7. The hovercraft control method according to claim 6, characterized in that, The pitch controller, in response to the increased pitch signal, increases the pitch of the propulsion fan, including: The pitch controller determines the target pitch of the propulsion fan based on the load reduction carried in the increased pitch signal, and the increased load torque of the propulsion fan matches the torque corresponding to the load reduction.

8. The hovercraft control method according to claim 1, characterized in that, The gas turbine and the propulsion fan are connected by a reducer and a coupling. The generator is connected in series between the reducer and the propulsion fan, and idles with the reducer in driving mode.

9. The hovercraft control method according to claim 1, characterized in that, The method of increasing the pitch of the propulsion fan through the pitch controller to increase the load torque generated by the propulsion fan to compensate for the sudden decrease in load power also includes: When the pitch of the propulsion fan increases, the propulsion fan absorbs the shaft power output by the gas turbine and directly converts the shaft power into the kinetic and internal energy of the air to replace the sudden reduction in load power consumed by the external load box, and dissipates heat for the propulsion fan itself and the equipment inside the ship's cabin, without the need to connect to external auxiliary cooling equipment.

10. A hovercraft, characterized in that, The hovercraft is used to implement the hovercraft control method as described in any one of claims 1 to 9, wherein the hovercraft comprises: Gas turbines are used to provide shaft power; The reducer has an input shaft connected to the output end of the gas turbine, one output shaft connected to the generator input end, and the other output shaft connected to the clutch input end for deceleration and power distribution. The clutch is used to control the rotation of the lifting fan. A generator, connected to the output end of the reducer, is used to convert shaft power into electrical energy under energized conditions; A propulsion fan is connected to the output end of the generator and is equipped with a pitch controller, which is used to adjust the pitch direction and size of the propulsion fan. The lift fan is driven by the gas turbine through a reducer to output a downward shaft and is connected to the gas turbine via a clutch. It is used to generate air cushion lift in driving mode. The fixed hoe, located on the front side of the hull, has a triangular structure and is used to generate unidirectional resistance when it comes into contact with the ground when the lifting fan stops or the hull lands. The control cabinet is communicatively connected to the generator and the pitch controller, respectively, and is used to send an increase pitch signal to the pitch controller when a sudden decrease in the load of the generator is detected, so as to increase the load torque of the propulsion fan to compensate for the sudden decrease in load power; The gas turbine, reducer, generator, and propulsion fan are connected in series. In the static power generation mode, the propulsion fan rotates with a reverse pitch to generate a reverse airflow, which cools the generator, reducer, and gas turbine in sequence. The resistance generated by the fixed hoe increases with the increase of the propulsion fan's thrust, in order to balance the thrust generated by the increase of the propulsion fan's pitch when the load suddenly decreases.

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