A roll-stopping stabilizer for a hovercraft
By integrating an attitude detection module, a central control unit, and an adjustable airbag deflector structure, the hovercraft's attitude can be monitored and dynamically adjusted in real time. This solves the problems of adaptability and response lag in the hovercraft's anti-capsule device, and improves navigation safety and handling stability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- HARBIN CHUANGQI TOURISM EQUIP TECH DEV CO LTD
- Filing Date
- 2025-10-20
- Publication Date
- 2026-07-24
AI Technical Summary
Existing anti-capsulation technologies cannot adapt to the non-contact levitation operation characteristics of hovercraft. They suffer from poor adaptability, slow response, lack of real-time attitude control and aerodynamic-structural coordinated control mechanisms, making it difficult to meet the high stability and safety requirements of hovercraft under complex working conditions.
The system integrates an attitude detection module, a central control unit, and an adjustable lateral stabilizing airbag or controllable deflector structure to achieve intelligent sensing and active adjustment of the hovercraft's lateral attitude. The attitude detection module monitors changes in the hull in real time, and the central control unit analyzes and processes the data before issuing commands. The active control components and auxiliary support components work together to adjust the airflow distribution and airbag pressure to balance the forces on the hull.
It effectively prevents hovercraft from tilting accidents caused by center of gravity shift or external disturbances, significantly improves navigation safety and handling stability, and provides rapid response and stable support, especially in high-speed navigation or complex waters.
Smart Images
Figure CN224545952U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of marine engineering technology, specifically a stabilizing device for preventing capsizing of hovercraft. Background Technology
[0002] With the widespread application of hovercraft in water transportation, emergency rescue, and special operational scenarios, their navigation stability, especially their anti-capsulation performance, has become a key factor affecting safety. When hovercraft operate at high speeds or in complex waters (such as those with large waves or strong crosswinds), they are highly susceptible to roll or even capsizing accidents due to center of gravity shift, uneven air cushion pressure distribution, or external disturbances. Therefore, developing an efficient and reliable anti-capsulation stabilization device suitable for hovercraft is of great significance. While existing anti-capsulation technologies for ships or vehicles have some reference value, the unique characteristics of hovercraft—such as their suspended operation, low water resistance, high maneuverability, and lack of fixed contact between the hull and the water surface—make traditional anti-capsulation mechanisms based on buoyancy structures or wheel supports difficult to directly apply.
[0003] A search revealed a publicly available design for an anti-capsulation vessel, with publication number CN105539763B. This design utilizes longitudinally extending arc-shaped wing plates on both sides of the hull, forming a semi-enclosed area between the hull sidewalls and deck to enhance resistance to lateral wind and waves, thereby improving the vessel's anti-capsulation performance. While this structure is simple and low-cost, its anti-capsulation principle relies on the hydrodynamic interaction between the hull and the water, making it suitable for traditional vessels with a fixed draft. However, when a hovercraft operates, the hull is above the water surface, relying primarily on the air cushion for support. The arc-shaped wing plates cannot effectively interact with the water surface, thus limiting the effectiveness of this structure on hovercraft and rendering it ineffective in handling sudden situations such as air cushion failure or dynamic tilting.
[0004] A search revealed a ship anti-capsulation structure with publication number CN110371266B. This design incorporates movable devices with fans and support rods on both sides of the hull. The fans mitigate the impact of lateral waves, while the support rods provide auxiliary support. Although this design incorporates active intervention and possesses some dynamic response capability, its fan system primarily weakens the impact of external waves and lacks a real-time sensing and feedback control mechanism for the hull's attitude. Furthermore, the support rods only deploy under specific conditions and lack continuous adjustment capability. More importantly, the device's support design is still based on the premise that the hull is in contact with the water. However, hovercraft operate with an air-film barrier at the bottom, making it impossible to achieve effective grounding support similar to the support rods. This renders the structure completely ineffective in hovercraft applications.
[0005] The aforementioned problems indicate that existing anti-capsulation technologies are mostly designed for traditional ships or land vehicles, relying on physical contact supports or hydrodynamic stability, and are unsuitable for the non-contact, levitating operation of hovercraft. Existing technologies generally suffer from poor adaptability, slow response, inability to achieve real-time attitude control, and a lack of aerodynamic-structural coordinated control mechanisms when applied to hovercraft, making it difficult to meet the high stability and safety requirements of hovercraft under complex operating conditions. Therefore, there is an urgent need for a dedicated anti-capsulation stabilization device for hovercraft that can combine air cushion pressure regulation, attitude sensing, and active stability control to achieve real-time monitoring and dynamic compensation of hull roll, thereby effectively preventing capsizing accidents.
[0006] This utility model aims to provide an anti-capsulation stabilization device for hovercraft. By integrating an attitude detection module, a central control unit, and an adjustable lateral stabilizing airbag or controllable deflector structure, it achieves intelligent perception and active adjustment of the hovercraft's lateral attitude, filling the gap in the field of anti-capsulation technology for non-contact operation platforms and improving the navigation safety and handling stability of hovercraft in harsh environments. Utility Model Content
[0007] This utility model relates to an anti-capsulation stabilization device for a hovercraft, comprising an attitude detection module, a central control unit, an active control component, and an auxiliary support component. The attitude detection module is installed inside the central hull of the hovercraft near the center of gravity to monitor changes in the hull's lateral attitude in real time. The central control unit is located to one side of the attitude detection module and is connected to it via a signal line. The active control component is symmetrically distributed on the outer contours of both sides of the hovercraft and is fixedly connected to the hull frame via a hydraulic drive mechanism. The auxiliary support component is located at the bottom of the hovercraft near the edge and is connected to the hovercraft's bottom plate via an elastic suspension system.
[0008] The attitude detection module includes a gyroscope sensor, an accelerometer, and a data processing unit. The gyroscope sensor and the accelerometer are respectively fixed to the inner wall of the detection module housing by bolts, and the detection module housing is fixed to the bottom plate of the central hull of the hovercraft by welding. The data processing unit is embedded in the middle of the detection module housing and is electrically connected to the gyroscope sensor and the accelerometer through a circuit board, and is used to integrate and output data signals of the hull attitude change.
[0009] The central control unit includes a microprocessor, a signal amplifier, and a communication interface. The microprocessor is installed inside the control unit housing via a slot. The signal amplifier is fixed to the side wall of the control unit housing with screws and connected to the microprocessor via wires. The communication interface is embedded in the outer wall of the control unit housing and is used to receive signals transmitted by the attitude detection module and send processed instructions to the active control component.
[0010] The active control component includes an adjustable guide vane, a drive motor, and a transmission mechanism. The adjustable guide vane is connected to a fixed bracket on the side wall of the hovercraft via a hinge. The drive motor is fixed to the top of the fixed bracket with bolts, and the output shaft of the drive motor is connected to the transmission mechanism via a coupling. The transmission mechanism includes a gear set and a rack. The gear set is fixed to the output shaft of the drive motor via a key connection. The rack is slidably connected to the inner wall of the fixed bracket via a slide rail and engages with the gear set via meshing, for converting the rotational motion of the drive motor into angle adjustment of the adjustable guide vane.
[0011] The auxiliary support assembly includes a flexible airbag, an inflation pump, and a pressure sensor. The flexible airbag is fixed to the edge area of the bottom of the hovercraft by adhesive bonding. The inflation pump is fixed to the inside of the bottom plate of the hovercraft by bolts and is connected to the flexible airbag through an air tube. The pressure sensor is embedded in the inner wall of the flexible airbag and is connected to the central control unit through a signal line to monitor the air pressure changes inside the flexible airbag in real time.
[0012] The hydraulic drive mechanism includes a hydraulic cylinder, a piston rod, and a hydraulic oil tank. The hydraulic cylinder is fixed to the frame of the side wall of the hovercraft by bolts. One end of the piston rod is connected to the output end of the hydraulic cylinder by a threaded connection, and the other end is connected to the bottom of the adjustable guide plate by a ball joint. The hydraulic oil tank is connected to the hydraulic cylinder by a pipeline and the flow direction of the hydraulic oil is controlled by a solenoid valve.
[0013] The elastic suspension system includes a spring, a shock absorber, and a connecting seat. The two ends of the spring are fixed to the connecting seat by threaded connection. The shock absorber is fixed to the middle of the spring by bolts and connected to the bottom plate of the hovercraft by a pin. The connecting seat is fixed to the top of the flexible airbag by welding and is used to transfer the supporting force of the flexible airbag to the bottom plate of the hovercraft.
[0014] This invention uses an attitude detection module to collect real-time lateral attitude data of the hovercraft. This data is then analyzed and processed by the central control unit, which sends commands to the active control component and the auxiliary support component. The adjustable deflectors in the active control component adjust their angle according to the commands, changing the airflow distribution on both sides of the hovercraft to balance the lateral forces on the hull. The flexible airbags in the auxiliary support component use inflation pumps to regulate air pressure, providing additional support to counteract the hull's tilting tendency. The hydraulic drive mechanism and the elastic suspension system provide power support and shock absorption to the active control component and the auxiliary support component, respectively, ensuring stable operation of the entire device under complex working conditions.
[0015] This invention solves the problems of insufficient adaptability, delayed response, and lack of real-time attitude control mechanism of the existing hovercraft anti-capsule device through the above-mentioned technical means. When the hovercraft is sailing at high speed or in complex waters, it can effectively prevent the tilting accident caused by the shift of the center of gravity or external disturbance, and significantly improve the navigation safety and handling stability of the hovercraft. Attached Figure Description
[0016] Figure 1 This is a schematic diagram of the overall structure of this utility model.
[0017] Figure 2 This is a schematic diagram of the overall structure of this utility model from another angle.
[0018] Figure 3 yes Figure 1 A magnified diagram of region A.
[0019] Figure 4 yes Figure 2 A magnified diagram of region B.
[0020] The attached figures are labeled as follows: 1. Attitude detection module; 2. Central control unit; 3. Active control component; 4. Auxiliary support component; 5. Hydraulic drive mechanism; 6. Elastic suspension system; 11. Gyroscope sensor; 12. Accelerometer; 13. Data processing unit; 14. Detection module housing; 21. Microprocessor; 22. Signal amplifier; 23. Communication interface; 24. Control unit housing; 31. Adjustable guide vane; 32. Drive motor; 33. Transmission mechanism; 34. Hinge; 35. Fixed bracket; 36. Coupling; 41. Flexible airbag; 42. Inflation pump; 43. Pressure sensor; 44. Air pipe; 51. Hydraulic cylinder; 52. Piston rod; 53. Hydraulic oil tank; 54. Ball joint; 61. Spring; 62. Shock absorber; 63. Connecting seat. Detailed Implementation
[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.
[0022] Specific implementation examples are given below.
[0023] This utility model provides an anti-capsulation stabilization device for hovercraft, combined with... Figures 1 to 4As shown, its specific implementation is as follows: Attitude detection module 1 is installed inside the central hull of the hovercraft near the center of gravity. Attitude detection module 1 includes a gyroscope sensor 11, an accelerometer 12, and a data processing unit 13. The gyroscope sensor 11 and accelerometer 12 are bolted to the inner wall of the detection module housing 14. The detection module housing 14 is welded to the bottom plate of the central hull of the hovercraft. The data processing unit 13 is embedded in the middle of the detection module housing 14 and electrically connected to the gyroscope sensor 11 and accelerometer 12 via a circuit board. Central control unit 2 is located on one side of attitude detection module 1 and connected to attitude detection module 1 via a signal line. The central control unit 2 includes a microprocessor 21, a signal amplifier 22, and a communication interface 23. The microprocessor 21 is installed in the control unit housing 24 via a slot. The signal amplifier 22 is fixed to the side wall of the control unit housing 24 with screws and connected to the microprocessor 21 via a wire. The communication interface 23 is embedded in the outer wall of the control unit housing 24 for communication with external devices. The active control components 3 are symmetrically distributed on the outer contours of both sides of the hovercraft and are fixedly connected to the hull frame via a hydraulic drive mechanism 5. The active control components 3 include an adjustable guide vane 31, a drive motor 32, and a transmission mechanism 33. The adjustable guide vane 31 is connected to a fixed bracket on the side wall of the hovercraft via a hinge 34. 35 is connected, and the drive motor 32 is fixed to the top of the fixed bracket 35 by bolts, and its output shaft is connected to the transmission mechanism 33 through the coupling 36. The transmission mechanism 33 includes a gear set 331 and a rack 332. The gear set 331 is fixed to the output shaft of the drive motor 32 by a key connection, and the rack 332 is slidably connected to the inner wall of the fixed bracket 35 through a slide rail 333 and engages with the gear set 331 by meshing. The auxiliary support assembly 4 is located at the bottom of the hovercraft near the edge area and is connected to the bottom plate of the hovercraft through the elastic suspension system 6. The auxiliary support assembly 4 includes a flexible airbag 41, an inflation pump 42, and a pressure sensor 43. The flexible airbag 41 is fixed to the bottom of the hovercraft by adhesive bonding. At the edge of the bottom of the hovercraft, an air pump 42 is bolted to the inside of the hovercraft's bottom plate and connected to a flexible airbag 41 via an air pipe 44. A pressure sensor 43 is embedded in the inner wall of the flexible airbag 41 and connected to the central control unit 2 via a signal line. The hydraulic drive mechanism 5 includes a hydraulic cylinder 51, a piston rod 52, and a hydraulic oil tank 53. The hydraulic cylinder 51 is bolted to the frame of the hovercraft's side wall. One end of the piston rod 52 is connected to the output end of the hydraulic cylinder 51 via a threaded connection, and the other end is connected to the bottom of the adjustable guide plate 31 via a ball joint 54. The hydraulic oil tank 53 is connected to the hydraulic cylinder 51 via a pipe 55 and the flow direction of the hydraulic oil is controlled by a solenoid valve 56.The elastic suspension system 6 includes a spring 61, a shock absorber 62, and a connecting seat 63. The two ends of the spring 61 are fixed to the connecting seat 63 via threaded connections. The shock absorber 62 is bolted to the middle of the spring 61 and connected to the bottom plate of the hovercraft via a pin 64. The connecting seat 63 is fixed to the top of the flexible airbag 41 by welding.
[0024] During actual operation, the gyroscope sensor 11 and accelerometer 12 in the attitude detection module 1 collect real-time data on the changes in the lateral attitude of the hovercraft and transmit the signals to the data processing unit 13. The data processing unit 13 integrates the signals and transmits the attitude change data to the central control unit 2 via a signal line. The signal amplifier 22 in the central control unit 2 amplifies the received signals and transmits them to the microprocessor 21. The microprocessor 21 analyzes the attitude change data according to a preset algorithm and generates control commands. The control commands are sent to the active control component 3 and the auxiliary support component 4 via the communication interface 23. When the hovercraft tilts, the drive motor 32 in the active control component 3 starts after receiving the control command. The output shaft of the drive motor 32 drives the gear set 331 in the transmission mechanism 33 to rotate through the coupling 36. The gear set 331 drives the rack 332 to move along the slide rail 333 through meshing. The movement of the rack 332 pushes the adjustable guide plate 31 to rotate around the hinge 34 to adjust the speed. The angle is adjusted to change the airflow distribution on both sides of the hovercraft to balance the lateral force. At the same time, the pressure sensor 43 in the auxiliary support component 4 monitors the air pressure change in the flexible airbag 41 in real time and feeds the signal back to the central control unit 2. The central control unit 2 generates an inflation command based on the feedback signal and sends it to the inflation pump 42 through the communication interface 23. The inflation pump 42 inflates or deflates the flexible airbag 41 through the air pipe 44 to adjust the air pressure. The air pressure change of the flexible airbag 41 is transmitted to the bottom plate of the hovercraft through the elastic suspension system 6 to provide additional support force to counteract the tilting tendency. The hydraulic oil tank 53 in the hydraulic drive mechanism 5 supplies oil to the hydraulic cylinder 51 through the pipe 55. The solenoid valve 56 controls the flow direction of the hydraulic oil according to the command of the central control unit 2. The hydraulic cylinder 51 drives the adjustable guide plate 31 to adjust its angle through the extension and retraction of the piston rod 52. The spring 61 and the shock absorber 62 in the elastic suspension system 6 work together to absorb the impact force and ensure that the support force of the flexible airbag 41 is smoothly transmitted to the bottom plate of the hovercraft.
[0025] In complex aquatic environments, such as during high-speed navigation or when encountering wind and waves, the aforementioned device can respond quickly and effectively prevent the hovercraft from tilting due to a shift in its center of gravity or external disturbances. For example, during high-speed navigation, if the hovercraft tilts to the left due to a large wave impact, the gyroscope sensor 11 and accelerometer 12 in the attitude detection module 1 will immediately detect this change and transmit the signal to the central control unit 2. After analysis, the central control unit 2 sends a command to the active control component 3 to deflect the adjustable guide vane 31 on the left downwards to increase airflow resistance on the left, and simultaneously sends a command to the adjustable guide vane 31 on the right to deflect it upwards to increase airflow resistance on the left. The system reduces airflow resistance on the right side, thereby quickly balancing the lateral forces on the hull. At the same time, the pressure sensor 43 in the auxiliary support assembly 4 detects a decrease in air pressure in the left flexible airbag 41 and sends a signal to the central control unit 2. The central control unit 2 then sends a command to the air pump 42 to inflate the left flexible airbag 41 to increase the support force, while appropriately deflating the right flexible airbag 41 to reduce the support force, thereby further counteracting the hull tilting tendency. The hydraulic drive mechanism 5 and the elastic suspension system 6 provide power support and shock absorption functions for the active control assembly 3 and the auxiliary support assembly 4, ensuring the stable operation of the entire device under complex working conditions.
[0026] In the specific assembly process, firstly, the detection module housing 14 of the attitude detection module 1 is fixed to the bottom plate of the central cabin of the hovercraft by welding. Then, the gyroscope sensor 11 and the accelerometer 12 are fixed to the inner wall of the detection module housing 14 by bolts, and the data processing unit 13 is embedded in the middle of the detection module housing 14. The gyroscope sensor 11, the accelerometer 12 and the data processing unit 13 are electrically connected by a circuit board. Next, the control unit housing 24 of the central control unit 2 is fixed to the side of the central cabin of the hovercraft near the attitude detection module 1 by bolts, and the microprocessor 21 is installed in the control unit through a slot. The signal amplifier 22 is fixed to the side wall of the control unit housing 24 with screws. The signal amplifier 22 is connected to the microprocessor 21 by wires, and the communication interface 23 is embedded in the outer wall of the control unit housing 24. Then, the fixing bracket 35 of the active control component 3 is fixed to the outer contour of the side wall of the hovercraft with bolts. The adjustable guide plate 31 is connected to the fixing bracket 35 by hinge 34, and the drive motor 32 is fixed to the top of the fixing bracket 35 with bolts. The output shaft of the drive motor 32 is connected to the gear set 331 in the transmission mechanism 33 by coupling 36. 1. The rack 332 is fixed to the output shaft of the drive motor 32 by key connection, and the rack 332 is slidably connected to the inner wall of the fixed bracket 35 via the slide rail 333. The gear set 331 and the rack 332 are engaged by meshing. The flexible airbag 41 of the auxiliary support component 4 is fixed to the edge area of the bottom of the hovercraft by adhesive bonding, and the air pump 42 is fixed to the inner side of the bottom plate of the hovercraft by bolts. The air pump 42 is connected to the flexible airbag 41 through the air pipe 44, and the pressure sensor 43 is embedded in the inner wall of the flexible airbag 41. The pressure sensor 43 is connected to the central control unit 2 through the signal line. The hydraulic drive mechanism 5 is connected to the rack 332 by key connection. The hydraulic cylinder 51 is fixed to the frame of the side wall of the hovercraft with bolts, and one end of the piston rod 52 is connected to the output end of the hydraulic cylinder 51 by a threaded connection. The other end is connected to the bottom of the adjustable guide plate 31 by a ball joint 54. The hydraulic oil tank 53 is connected to the hydraulic cylinder 51 through the pipe 55, and the solenoid valve 56 is installed on the pipe 55. Finally, the connecting seat 63 of the elastic suspension system 6 is fixed to the top of the flexible airbag 41 by welding, and the two ends of the spring 61 are fixed to the connecting seat 63 by a threaded connection. The shock absorber 62 is fixed to the middle of the spring 61 by bolts and connected to the bottom plate of the hovercraft by a pin 64.
[0027] In the above specific embodiments, the connection relationships, positional relationships, and mutual cooperation relationships between the various components are described in detail, enabling those skilled in the art to accurately implement the technical solution of this utility model based on the contents of this specification.
[0028] To enable those skilled in the art to fully understand and implement this utility model, the specific implementation principle of this utility model is further explained below in conjunction with a specific application scenario.
[0029] During high-speed navigation of the hovercraft, if the port side is impacted by large waves causing the hull to tilt to the left, the gyroscope sensor 11 and accelerometer 12 in the attitude detection module 1 will first detect this change. At this time, the gyroscope sensor 11 obtains the tilt angle of the hull by detecting the angular velocity signal, while the accelerometer 12 determines the lateral acceleration change of the hull by measuring the acceleration signal. These two signals are integrated by the data processing unit 13 and transmitted to the central control unit 2 via a signal line. The signal amplifier 22 in the central control unit 2 amplifies the received signal, and then the microprocessor 21 analyzes the attitude change data based on a preset algorithm and generates control commands.
[0030] The control command is sent to the active control component 3 and the auxiliary support component 4 via the communication interface 23. Upon receiving the command, the drive motor 32 in the active control component 3 starts, and its output shaft drives the gear set 331 in the transmission mechanism 33 to rotate via the coupling 36. The gear set 331 meshes with the rack 332, which moves along the slide rail 333, pushing the adjustable guide vane 31 to rotate around the hinge 34. The adjustable guide vane 31 on the left deflects downward to increase airflow resistance on the left, while the adjustable guide vane 31 on the right deflects upward to reduce airflow resistance on the right, thereby quickly balancing the lateral forces on the hull.
[0031] Meanwhile, pressure sensor 43 in auxiliary support assembly 4 monitors the air pressure changes inside flexible airbag 41 in real time. When the air pressure in the left flexible airbag 41 decreases due to the hull tilting to the left, pressure sensor 43 sends a signal back to central control unit 2. Central control unit 2 then sends a command to air pump 42. Left air pump 42 inflates flexible airbag 41 through air pipe 44 to increase its support force; while right air pump 42 deflates appropriately according to the command to reduce the support force of flexible airbag 41, thereby further counteracting the hull tilting trend. The air pressure change in flexible airbag 41 is transmitted to the bottom plate of the hovercraft through elastic suspension system 6. Spring 61 and shock absorber 62 work together to absorb impact force and ensure smooth transmission of support force.
[0032] The hydraulic drive mechanism 5 provides power during this process. The hydraulic oil tank 53 supplies oil to the hydraulic cylinder 51 via pipe 55, and the solenoid valve 56 controls the flow direction of the hydraulic oil according to the instructions of the central control unit 2. The hydraulic cylinder 51 adjusts the angle of the adjustable guide plate 31 through the extension and retraction of the piston rod 52, ensuring rapid response to control commands. The connecting seat 63 in the elastic suspension system 6 is fixed to the top of the flexible airbag 41 by welding. The spring 61 and shock absorber 62 are connected to the bottom plate of the hovercraft via threaded connections and bolts, respectively, working together to enhance the system's stability.
[0033] In complex aquatic environments, the aforementioned device can respond quickly and effectively prevent the hovercraft from tilting due to center of gravity shift or external disturbances. For example, when encountering strong crosswinds, the attitude detection module 1 collects real-time data on changes in the hull's attitude, the central control unit 2 quickly generates control commands, the active control component 3 changes the airflow distribution by adjusting the angle of the adjustable guide vane 31, the auxiliary support component 4 provides additional support by adjusting the air pressure of the flexible airbag 41, and the hydraulic drive mechanism 5 and the elastic suspension system 6 provide power and buffering functions for active control and auxiliary support, ensuring the stable operation of the entire device under complex working conditions.
[0034] All content not described in detail in this specification is prior art known to those skilled in the art, and the model parameters of each electrical appliance are not specifically limited; conventional equipment can be used. Electrical control components not mentioned in this technical solution are not shown in the figures because they are prior art, and will not be described further here.
[0035] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.
Claims
1. A stabilizing device for a hovercraft to prevent capsizing, characterized in that, The system includes an attitude detection module (1), a central control unit (2), an active control component (3), and an auxiliary support component (4). The attitude detection module (1) is installed inside the central hull of the hovercraft near the center of gravity to monitor changes in the lateral attitude of the hull. The central control unit (2) is located on one side of the attitude detection module (1) and is connected to the attitude detection module (1) via a signal line. The active control component (3) is symmetrically distributed on the outer contours of both sides of the hovercraft and is fixedly connected to the hull frame via a hydraulic drive mechanism (5). The auxiliary support component (4) is located at the bottom of the hovercraft near the edge and is connected to the bottom plate of the hovercraft via an elastic suspension system (6).
2. The anti-capsulation stabilization device for a hovercraft according to claim 1, characterized in that, The attitude detection module (1) includes a gyroscope sensor (11), an accelerometer (12) and a data processing unit (13). The gyroscope sensor (11) and the accelerometer (12) are respectively fixed to the inner wall of the detection module housing (14) by bolts. The detection module housing (14) is fixed to the bottom plate of the central cabin of the hovercraft by welding. The data processing unit (13) is embedded in the middle of the detection module housing (14) and electrically connected to the gyroscope sensor (11) and the accelerometer (12) through a circuit board.
3. The anti-capsulation stabilization device for a hovercraft according to claim 1, characterized in that, The central control unit (2) includes a microprocessor (21), a signal amplifier (22), and a communication interface (23). The microprocessor (21) is installed in the control unit housing (24) through a slot. The signal amplifier (22) is fixed to the side wall of the control unit housing (24) by screws and connected to the microprocessor (21) through a wire. The communication interface (23) is embedded in the outer wall of the control unit housing (24).
4. The anti-capsulation stabilization device for a hovercraft according to claim 1, characterized in that, The active control component (3) includes an adjustable guide plate (31), a drive motor (32), and a transmission mechanism (33). The adjustable guide plate (31) is connected to a fixed bracket (35) on the side wall of the hovercraft via a hinge (34). The drive motor (32) is fixed to the top of the fixed bracket (35) by bolts, and the output shaft of the drive motor (32) is connected to the transmission mechanism (33) via a coupling (36). The transmission mechanism (33) includes a gear set (331) and a rack (332). The gear set (331) is fixed to the output shaft of the drive motor (32) by a key connection. The rack (332) is slidably connected to the inner wall of the fixed bracket (35) via a slide rail (333) and engages with the gear set (331) by meshing.
5. The anti-capsulation stabilization device for a hovercraft according to claim 1, characterized in that, The auxiliary support component (4) includes a flexible airbag (41), an inflation pump (42), and a pressure sensor (43). The flexible airbag (41) is fixed to the edge area of the bottom of the hovercraft by adhesive bonding. The inflation pump (42) is fixed to the inner side of the bottom plate of the hovercraft by bolts and is connected to the flexible airbag (41) through an air pipe (44). The pressure sensor (43) is embedded in the inner wall of the flexible airbag (41) and is connected to the central control unit (2) through a signal line.
6. The anti-capsulation stabilization device for a hovercraft according to claim 1, characterized in that, The hydraulic drive mechanism (5) includes a hydraulic cylinder (51), a piston rod (52), and a hydraulic oil tank (53). The hydraulic cylinder (51) is fixed to the frame of the side wall of the hovercraft by bolts. One end of the piston rod (52) is connected to the output end of the hydraulic cylinder (51) by a threaded connection, and the other end is connected to the bottom of the adjustable guide plate (31) by a ball joint (54). The hydraulic oil tank (53) is connected to the hydraulic cylinder (51) by a pipe (55) and the flow direction of the hydraulic oil is controlled by a solenoid valve (56).
7. The anti-capsulation stabilization device for a hovercraft according to claim 1, characterized in that, The elastic suspension system (6) includes a spring (61), a shock absorber (62) and a connecting seat (63). The two ends of the spring (61) are fixed to the connecting seat (63) by threaded connection. The shock absorber (62) is fixed to the middle of the spring (61) by bolts and connected to the bottom plate of the hovercraft by a pin (64). The connecting seat (63) is fixed to the top of the flexible airbag (41) by welding.
8. The anti-capsulation stabilization device for a hovercraft according to claim 4, characterized in that, The rack (332) in the transmission mechanism (33) is slidably connected to the inner wall of the fixed bracket (35) through the slide rail (333), and one end of the rack (332) is engaged with the gear set (331) in a meshing manner.
9. The anti-capsulation stabilization device for a hovercraft according to claim 5, characterized in that, The inner wall of the flexible airbag (41) is fitted with a pressure sensor (43), which is connected to the central control unit (2) via a signal line.
10. The anti-capsulation stabilization device for a hovercraft according to claim 6, characterized in that, The hydraulic oil tank (53) is connected to the hydraulic cylinder (51) through a pipe (55), and a solenoid valve (56) is installed on the pipe (55).