Air cushion vehicle exhaust gas seal structure

Abstract

The application discloses a structure of a tail gas seal of an air cushion vehicle, which comprises a tail gas seal body installed at the tail of a ship body, a partition plate in the tail gas seal body, a plurality of capsules formed by the partition plate, a plurality of air holes formed on the partition plate, a slant side of the tail gas seal body, an arc side of the tail gas seal body, and a plurality of air outlets formed on the tail gas seal body. The tail gas seal body has a plurality of layers and has high strength. The slant side of the tail gas seal body can be matched with the sailing direction and the air flow direction of the air cushion vehicle, and the tail gas seal body can effectively reduce the resistance. When the tail gas seal body is pressed by an obstacle, the tail gas seal body can discharge the excess gas through the air outlets, so that the buffer and the impact force are reduced. The structure of the tail gas seal of the air cushion vehicle can better match the sailing of the air cushion vehicle, reduce the sailing resistance, improve the sailing stability, better cope with the obstacle environment, and improve the sailing safety.

Description

Technical Field

[0001] This invention relates to hovercraft, and more particularly to the structure of the tail gas seal of a hovercraft. Background Technology

[0002] A hovercraft is a high-speed vessel that uses the surface effect principle to create an air cushion, allowing the hull to detach from a supporting surface and achieve navigation. In addition to an engine and propulsion system, a hovercraft has an air chamber with an exhaust port at the bottom and a skirt surrounding its edges. High-pressure air is delivered into the air chamber through pipes and then ejected from the exhaust port. The skirt simultaneously obstructs the ejected airflow, forming an air cushion layer to support the hull. The engine then drives the propulsion system to keep the vessel close to the supporting surface. However, because the forces acting on the bow, sides, and stern of a hovercraft differ in direction and interaction with the airflow, the stern skirt is prone to generating wave-making drag during navigation, affecting the stability and safety of the hovercraft and negatively impacting its power and speed. Furthermore, existing skirts have poor deformation capacity, making them prone to swaying when encountering impacts or crossing obstacles, further affecting speed and stability. Summary of the Invention

[0003] The purpose of this invention is to provide a deformable tail gas seal structure so that the hovercraft can deform in time when encountering emergencies, reduce the resistance of navigation, and improve the stability of the hovercraft.

[0004] The tail gas seal structure of the hovercraft described in this invention includes a tail gas seal body installed at the stern of the hull. The tail gas seal body is hollow inside and its top is connected to the air supply device of the hovercraft. The inner side of the tail gas seal body is an inclined surface. The outer side of the tail gas seal body includes several bladder segments that are connected end to end and protrude outward in the middle. A partition is connected to the inner wall at the junction of adjacent bladder segments. The partition extends to the inner wall surface of each side of the tail gas seal body. The partition has a vent hole connecting the upper and lower ends. The bottom bladder segment also has an outlet hole for discharging high-pressure gas.

[0005] Furthermore, a stern opening is provided on the bottom sac segment, and a baffle is installed on the inner wall of the sac segment above the stern opening. The lower end of the baffle hangs down naturally and can cover the inside of the stern opening.

[0006] Furthermore, the air outlet is located at the bottom of the bottom bladder section, and the slope or the bottom of the bladder section is provided with an anti-wear plate extending towards the stern and covering the outside of the air outlet.

[0007] Furthermore, an adjustable regulator with an adjustable opening diameter is installed on the bottom bladder segment, and the air outlet is located on the regulator.

[0008] Furthermore, the top of the exhaust gas seal body is hinged to the hull.

[0009] Furthermore, a clamping plate is installed at the bottom of the hull, and the end of the clamping plate is provided with a horizontally arranged clamping hole. The clamping plate is also provided with a slot that connects the outer wall and the clamping hole. The diameter of the top end of the exhaust gas seal body is greater than the width of the slot and less than the diameter of the clamping hole. The top end of the exhaust gas seal body is provided with a fixing hole parallel to the direction of the clamping hole. The clamping strip passes through the fixing hole and rotatably fixes the top end of the exhaust gas seal body in the clamping hole.

[0010] Furthermore, the clamping strip is a rubber strip.

[0011] Furthermore, a reinforcing plate is installed on the outer wall at the junction of adjacent cyst segments.

[0012] Furthermore, the reinforcing sheet is made of the same material as the exhaust gas seal body, and the reinforcing sheet is bonded to the recessed position on the outer wall at the junction of the two bladder sections.

[0013] Furthermore, the junction of the two septal segments extends upwards and slopes towards the inner wall of the sloping surface.

[0014] The tail gas seal structure of the hovercraft described in this invention involves the hovercraft delivering high-pressure air into an air chamber at the bottom of the hull, forming a cushion layer. The tail gas seal body can block and enclose the airflow of the cushion layer, thereby creating a more effective cushion to support the hull. Simultaneously, the inner side of the tail gas seal body, facing the bow, is designed as a slope, which, in conjunction with the hovercraft's sailing direction and airflow direction, effectively reduces drag. When encountering an obstacle and causing pressure on the tail gas seal body, excess gas can be discharged through the vent, thus achieving buffering and reducing impact force. After passing the obstacle, the air supply device inside the hovercraft can refill the tail gas seal body with high-pressure air, causing it to re-inflate. Furthermore, the outer side of the tail gas seal body, facing away from the bow, is designed with multiple bladder segments, which, together with internal partitions, divide the internal space of the tail gas seal body into multiple bladders. This improves the structural strength of the tail gas seal body, the upper bladders provide a stronger buffering effect, and the lower bladders have a faster deformation capability, thereby improving impact resistance. Therefore, by setting up this type of air-cushioned vehicle stern air seal structure, it can better cooperate with the navigation of the air-cushioned vehicle, reduce navigation resistance and improve navigation stability, and better cope with obstacle environments, thereby improving navigation safety. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the stern air seal structure of a hovercraft.

[0016] Figure 2 This is a schematic diagram of the air seal structure at the stern of the hovercraft being installed on the hovercraft.

[0017] Figure 3 This is a cross-sectional schematic diagram of the stern air seal structure of an air-cushioned vehicle.

[0018] Figure 4 , 5 They are Figure 3 The diagram shows a partial structural schematic of the stern air seal structure of the hovercraft. Detailed Implementation

[0019] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0020] It should be noted that if the embodiments of the present invention involve directional indicators (such as up, down, left, right, front, back, top, bottom, inside, outside, vertical, horizontal, longitudinal, counterclockwise, clockwise, circumferential, radial, axial, etc.), the directional indicators are only used to explain the relative positional relationship and movement of the components in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicators will also change accordingly.

[0021] If the embodiments of this invention involve descriptions such as "first" or "second," such descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, features defined with "first" or "second" may explicitly or implicitly include at least one of those features. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. If the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0022] This invention proposes a tail gas seal structure for hovercraft.

[0023] The tail gas seal structure of the hovercraft in this embodiment includes a tail gas seal body 2 installed at the stern of the hull 1. The tail gas seal body is hollow inside and its top is connected to the air supply device of the hovercraft. The inner side of the tail gas seal body is an inclined surface 3. The outer side of the tail gas seal body includes several bladder segments 4 that are connected end to end and protrude outward in the middle. A partition 5 is connected to the inner wall at the junction of adjacent bladder segments. The partition extends to the inner wall surface of each side of the tail gas seal body. The partition has a vent hole 51 that connects the upper and lower ends. The bottom bladder segment also has an outlet hole 6 for discharging high-pressure gas.

[0024] like Figure 1-5As shown, the hovercraft delivers high-pressure air into an air chamber at the bottom of the hull, forming an air cushion layer. The tail gas seal body blocks and encloses the airflow of the air cushion layer, creating a more effective air cushion to support the hull. Simultaneously, the inner side of the tail gas seal body, facing the bow, is sloped, which, in conjunction with the hovercraft's direction of travel and airflow, effectively reduces drag. When encountering an obstacle and causing pressure on the tail gas seal body, excess gas can be expelled through the vents, thus buffering and reducing impact. After passing the obstacle, the air supply device inside the hovercraft can refill the tail gas seal body with high-pressure air, causing it to re-inflate. Furthermore, the outer side of the tail gas seal body, facing away from the bow, is divided into multiple bladder segments, which, together with internal partitions, divide the internal space of the tail gas seal body into multiple bladders. This improves the structural strength of the tail gas seal body, provides stronger cushioning for the upper bladders, and allows for faster deformation of the lower bladders, thus enhancing impact resistance.

[0025] The tail gas seal structure of the hovercraft described above can have its top fixedly installed on the hull, or it can be hinged to the hull 1 via a pivot, hook, or other means. Specifically, it can be as follows: Figure 3 , 4 As shown, a retaining plate 11 is installed at the bottom of the hull 1. The end of the retaining plate has a horizontally arranged retaining hole 12. The retaining plate also has a slot 13 connecting the outer wall and the retaining hole. The diameter of the top end of the exhaust gas seal body 2 is larger than the width of the slot but smaller than the diameter of the retaining hole. A fixing hole parallel to the direction of the retaining hole is opened at the top end of the exhaust gas seal body. A clamping strip 7 passes through the fixing hole and expands the top end of the exhaust gas seal body, thereby rotatably fixing it within the retaining hole of the retaining plate. This achieves a hinged effect, utilizes the deformability of the exhaust gas seal body for fixing, and ensures the deformation and buffering capacity of the exhaust gas seal body when encountering obstacles. Furthermore, its installation, fixing, and disassembly are convenient. Simultaneously, the clamping strip 7 is a rubber strip, thus better ensuring deformation capacity.

[0026] The aforementioned hovercraft stern gas seal structure features a centrally protruding arc-shaped structure within the bladder segment. A reinforcing plate 8 can be installed on the outer wall at the junction of adjacent bladder segments 4. The reinforcing plate 8 is made of the same material as the main body 2 of the stern gas seal and is bonded to a recessed position on the outer wall at the junction of the two bladder segments 4. Its shape is selected according to the requirements of the stern gas seal, for example... Figure 3 As shown, the reinforcing plate 8 has a V-shaped structure, with its bottom located at the recess where the two bladder segments 4 meet, and its two sides tightly attached to the outer walls of the two bladder segments, thereby improving the structural strength of the exhaust gas seal body. The partition plate 5 extends upwards and inclines from the junction of the two bladder segments 4 toward the inner wall of the inclined plane 3, aligning with the inclination direction of the inclined plane, thus better matching the hovercraft's navigation direction and the impact direction when encountering obstacles, forming a more effective and stable buffering effect.

[0027] The aforementioned hovercraft stern air seal structure features an air outlet 6 located at the bottom of the bottom bladder section 4. This allows for the formation of an air film during exhaust and facilitates the drainage of accumulated water. Simultaneously, an anti-wear plate 9 extending towards the stern and covering the outside of the air outlet is located at the bottom of the inclined surface 3 or the bottom of the bladder section 4, in front of the air outlet (facing the bow). This ensures both exhaust performance and air outlet safety, preventing blockage. The anti-wear plate 9 can be made of the same material as the stern air seal body 2, or it can be integrally formed with the stern air seal body. It can also be made of wear-resistant material to improve its service life. Furthermore, an adjustable aperture regulator can be installed on the bottom bladder section 4, with the air outlet 6 positioned on the regulator. This allows for changing the aperture of the air outlet, thereby adjusting the responsiveness of the hovercraft's skirt. Higher responsiveness results in better deformation capability. In addition, a stern opening 41 is provided on the bottom bladder section 4. A baffle 42 is installed on the inner wall of the bladder section above the stern opening. The lower end of the baffle hangs down naturally and can cover the inside of the stern opening. When the air pressure inside the exhaust gas seal body is sufficient, the lower end of the baffle will be pressed tightly against the stern opening by the air pressure, thereby sealing the stern opening. However, when the exhaust gas seal body undergoes violent deformation, a large amount of air pressure is exhausted from the exhaust gas seal body, the internal air pressure decreases, and the baffle will no longer be able to press tightly against the stern opening, thus exposing a gap for exhaust. This can help to expel the internal gas more quickly and improve the buffering effect.

[0028] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

Claims

1. A stern air seal structure for a hovercraft, characterized in that: The system includes a tail gas seal body (2) installed at the stern of the hull (1). The tail gas seal body is hollow inside and connected to the air supply device of the hovercraft at the top. The inner side of the tail gas seal body is an inclined surface (3). The outer side of the tail gas seal body includes several bladder sections (4) that are connected end to end and protrude outward in the middle. A partition (5) is connected to the inner wall at the junction of adjacent bladder sections. The partition extends to the inner wall of each side of the tail gas seal body. The partition has a vent (51) that connects the upper and lower ends. The bottom bladder section also has an outlet (6) for discharging high-pressure gas. The bottom bladder section (4) has a stern hole (41). A baffle (42) is installed on the inner wall of the bladder section above the stern hole. The lower end of the baffle hangs down naturally and can cover the inner side of the stern hole. The outlet (6) is located at the bottom of the bottom bladder section (4). The bottom of the inclined surface (3) or the bladder section (4) is provided with an anti-wear plate (9) extending towards the stern and covering the outside of the bladder section (4) at the front of the vent. An adjustable regulator with an adjustable opening diameter is installed on the bladder section (4) at the bottom, and the vent (6) is set on the regulator. The top of the tail gas seal body (2) is hinged to the hull (1). The bottom of the hull (1) is equipped with a clamping plate (11), and the end of the clamping plate is provided with a horizontally arranged clamping hole (12). The clamping plate is also provided with a slot (13) connecting the outer wall and the clamping hole. The diameter of the top end of the tail gas seal body (2) is greater than the width of the slot and less than the diameter of the clamping hole. The top end of the tail gas seal body is provided with a fixing hole parallel to the direction of the clamping hole. The clamping strip (7) passes through the fixing hole and rotatably fixes the top end of the tail gas seal body in the clamping hole.

2. The stern air seal structure for a hovercraft according to claim 1, characterized in that: The clamping strip (7) is a rubber strip.

3. The stern air seal structure for a hovercraft according to claim 1, characterized in that: A reinforcing plate (8) is installed on the outer wall at the junction of adjacent cyst segments (4).

4. The stern air seal structure for a hovercraft according to claim 3, characterized in that: The reinforcing sheet (8) is made of the same material as the exhaust gas seal body (2), and the reinforcing sheet is bonded to the recessed position of the outer wall at the junction of adjacent bladder segments (4).

5. The stern air seal structure for a hovercraft according to claim 1, characterized in that: The septum (5) extends upward at an angle from the junction of the adjacent sac segments (4) toward the inner wall of the slope (3).

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