CN213035813U

CN213035813U - Cabin air heat dissipation device for small and medium sized hovercraft

Info

Publication number: CN213035813U
Application number: CN202022145285.1U
Authority: CN
Inventors: 王岩; 刘超; 刘立光; 姜佳奇
Original assignee: Harbin Chuangqi Tourism Equipment Technology Development Co ltd
Current assignee: Harbin Chuangqi Tourism Equipment Technology Development Co ltd
Priority date: 2020-09-25
Filing date: 2020-09-25
Publication date: 2021-04-23
Anticipated expiration: 2030-09-25

Abstract

The utility model provides a middle-size and small-size hovercraft cabin air heat abstractor, marine engineering technical field, includes hydrophobic board, a plurality of air intake and a plurality of baffle, the top surface is the inclined plane on the housing, top surface one end is provided with the housing groove on the housing, fixedly connected with hydrophobic board on the housing groove, the housing side is provided with a plurality of air outlets, every the air outlet all rotates and is connected with a baffle, the housing up end is provided with a plurality of air intakes, the housing internal rotation is connected with supplementary heat abstractor. The utility model discloses can solve the radiating problem of engine, still protect the engine not intake in radiating, can also carry out radiating regulation according to hovercraft's speed.

Description

Cabin air heat dissipation device for small and medium sized hovercraft

Technical Field

The utility model belongs to the technical field of marine engineering, especially, middle-size and small-size hovercraft cabin air heat abstractor.

Background

A hovercraft is a vehicle that can travel over a variety of complex terrains. It can be used for running on water, land, ice and snow, and also for running on marsh, mud and other complicated landforms. The hovercraft needs to be propelled after the boat bolsters are lifted, which requires a very large power for the engine. The faster the speed, the larger the heat generated by the engine is, the smaller the space in the engine cabin is, the difficult heat dissipation is, if the hot air and smoke generated in the engine cabin are not discharged in time, the performance of the engine ECU can be reduced, even the engine ECU is damaged.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a middle-size and small-size hovercraft cabin air heat abstractor for solving the above-mentioned problem that prior art exists.

The purpose is achieved, the utility model adopts the following technical proposal:

the utility model provides a middle-size and small-size hovercraft cabin air heat abstractor, includes the housing, its characterized in that: the housing includes: the heat dissipation device comprises a hydrophobic plate, a plurality of air inlets and a plurality of baffles, wherein the upper top surface of the housing is an inclined plane, one end of the upper top surface of the housing is provided with a housing groove, the hydrophobic plate is fixedly connected to the housing groove, a plurality of air outlets are arranged on the side surface of the housing, each air outlet is rotatably connected with one baffle, the upper end surface of the housing is provided with a plurality of air inlets, and the interior of the housing is rotatably connected with an auxiliary heat dissipation device.

Compared with the prior art, the beneficial effects of the utility model are that:

the utility model provides a middle-size and small-size hovercraft cabin air heat abstractor can solve the radiating problem of engine, protects the engine not intake in the radiating, can also carry out radiating regulation according to hovercraft's speed.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a rear view of the housing;

FIG. 3 is a side view of the housing;

FIG. 4 is a schematic view of the internal structure of the housing;

fig. 5 is a schematic view of a heat sink plate structure.

The names and reference numbers of the components referred to in the above figures are as follows:

the heat dissipation device comprises a housing 1, a hydrophobic plate 1-1, an air outlet 1-2, an air inlet 1-5, a baffle 1-3, a transverse water blocking strip 1-4, a water chute 1-6, a filter screen 1-7, an auxiliary heat dissipation device 2, a rotating shaft 2-1, a heat dissipation disc 2-2, two cover plates 2-2-1 and heat dissipation fins 2-2-2.

Detailed Description

The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiment of the present invention, and it is obvious that the described embodiment is only a part of the embodiments of the present invention, rather than all embodiments, and all other embodiments obtained by a person of ordinary skill in the art without creative work belong to the protection scope of the present invention based on the embodiments of the present invention.

The first embodiment is as follows: as shown in fig. 1 to 5, the present embodiment discloses a small and medium sized hovercraft cabin air heat dissipation device, which includes a housing 1, and is characterized in that: the housing 1 includes: the heat dissipation device comprises a hydrophobic plate 1-1, a plurality of air inlets 1-5 and a plurality of baffles 1-3, wherein the upper top surface of a housing 1 is an inclined plane, a housing groove is formed in one end of the upper top surface of the housing 1, the hydrophobic plate 1-1 is fixedly connected to the housing groove, a plurality of air outlets 1-2 are formed in the side surface of the housing 1, each air outlet 1-2 is rotatably connected with one baffle 1-3, the baffles 1-3 are made of aluminum alloy or carbon fiber materials to ensure that the mass of the baffles is light, the upper end surface of the housing 1 is provided with the plurality of air inlets 1-5, and an auxiliary heat dissipation device 2 is rotatably connected to the interior of the housing 1.

The second embodiment is as follows: as shown in fig. 1, this embodiment is further described as a first embodiment, and the housing 1 further includes: the water-resistant water purifier comprises transverse water-resistant strips 1-4, water guide grooves 1-6 and a plurality of filter screens 1-7, wherein the transverse water-resistant strips 1-4 are fixedly connected to the top surface of the housing 1, the transverse water-resistant strips 1-4 are positioned between a hydrophobic plate 1-1 and a plurality of air inlets 1-5, the upper end of each air inlet 1-5 is fixedly connected with one filter screen 1-7, and the water guide grooves 1-6 are arranged along the outer periphery of the plurality of air inlets 1-5.

The third concrete implementation mode: as shown in fig. 3 and 4, the present embodiment is further described with respect to the first embodiment, and the auxiliary heat sink 2 includes: the heat dissipation device comprises a rotating shaft 2-1 and a plurality of heat dissipation discs 2-2, wherein the rotating shaft 2-1 fixedly penetrates through the plurality of heat dissipation discs 2-2, two inner side walls of the housing 1 are rotatably connected with the rotating shaft 2-1, and the plurality of heat dissipation discs 2-2 penetrate through the housing grooves.

The fourth concrete implementation mode: as shown in fig. 5, the present embodiment is further described with respect to the first embodiment, and each of the plurality of heat dissipation plates 2-2 includes: the two cover plates 2-2-1 are coaxial, the middle portions of the two cover plates 2-2-1 are provided with cover plate holes 2-2-3, the rotating shaft 2-1 penetrates through the cover plate holes 2-2-3 to be fixedly connected with the two cover plates 2-2-1, and the plurality of radiating fins 2-2-2 are uniformly and fixedly connected on the opposite inner side faces of the two cover plates 2-2-1.

The fifth concrete implementation mode: as shown in fig. 5, the present embodiment is further described with respect to the first embodiment, and the plurality of heat dissipation fins 2-2-2 are made of copper.

The utility model discloses the theory of operation is: the method comprises the following steps that a cover 1 is arranged above an engine cabin, when the hovercraft starts to operate, negative pressure is formed to enable air to enter the engine cabin through an air inlet 1-5, then airflow pushes a plurality of baffles 1-3 to discharge hot air and smoke through an air outlet 1-2, and the purpose of heat dissipation is achieved; when the hovercraft runs for a period of time or the speed is accelerated, the heat generated by the engine is increased, the speed of the hovercraft is accelerated, the flow speed of air entering the air inlet 1-5 is higher, the air flows into the housing 1 and drives the plurality of radiating discs 2-2 to rotate through the rotating shaft 2-1, the plurality of radiating discs 2-2 rotate to play a role of a fan, hot air and smoke in an engine room can be discharged through a housing groove, meanwhile, the plurality of radiating fins 2-2-2 are made of copper and play a role of radiating, the plurality of radiating discs 2-2 can play a role of turbulence to achieve the purpose of noise reduction, and at the moment, the plurality of radiating discs 2-2 and the air outlet 1-2 simultaneously radiate heat and can quickly cool the engine room; the filter screens 1-7 can filter air to prevent dust from entering an engine compartment, and prevent the dust from attaching to the surface of an engine to cause the temperature of the engine to rise.

The transverse water-blocking strips 1-4 and the water guide grooves 1-6 have the following functions: when raining or the hovercraft is too fast, water mist is brought up, the rainwater or the water mist falls on the hydrophobic plate 1-1, the rainwater or the water mist flows downwards along the hydrophobic plate 1-1 under the action of gravity, and the rainwater and the water mist respectively flow downwards through two sides of the transverse water-blocking strips 1-4 under the blocking action of the transverse water-blocking strips 1-4, so that the rainwater or the water mist can be prevented from entering an engine compartment to cause the damage of the engine; the water guide grooves 1-6 have the function of enabling rainwater and water mist to flow out through the water guide grooves 1-6, so that the function of guiding the water is achieved, and the rainwater and the water mist are prevented from entering the engine room through the plurality of air inlets 1-5; meanwhile, the transverse water-blocking strips 1-4 play a role in shunting, so that excessive water flowing down through the hydrophobic plate 1-1 is prevented from entering the water guide grooves 1-6 to cause no time for guiding the water, and the water is poured into the engine to cause the damage of the engine.

It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.

Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.

Claims

1. The utility model provides a middle-size and small-size hovercraft cabin air heat abstractor, includes housing (1), its characterized in that: the casing (1) comprises: the heat-radiating cover comprises a hydrophobic plate (1-1), a plurality of air inlets (1-5) and a plurality of baffles (1-3), wherein the upper top surface of the cover shell (1) is an inclined plane, a cover shell groove is formed in one end of the upper top surface of the cover shell (1), the hydrophobic plate (1-1) is fixedly connected to the cover shell groove, a plurality of air outlets (1-2) are formed in the side surface of the cover shell (1), each air outlet (1-2) is rotatably connected with one baffle (1-3), the plurality of air inlets (1-5) are formed in the upper end surface of the cover shell (1), and an auxiliary heat-radiating device (2) is rotatably connected to the inner portion of the cover shell (1).

2. The small and medium sized hovercraft cabin air heat dissipating device of claim 1, wherein: the casing (1) further comprises: the water-resistant water purifier comprises transverse water-resistant strips (1-4), water guide chutes (1-6) and a plurality of filter screens (1-7), wherein the transverse water-resistant strips (1-4) are fixedly connected to the top surface of the housing (1), the transverse water-resistant strips (1-4) are located between the hydrophobic plate (1-1) and the plurality of air inlets (1-5), one filter screen (1-7) is fixedly connected to the upper end of each air inlet (1-5), and the water guide chutes (1-6) are arranged along the outer peripheries of the plurality of air inlets (1-5).

3. The air cooling device for the small and medium sized hovercraft cabin according to claim 1 or 2, wherein: the auxiliary heat sink (2) includes: axis of rotation (2-1) and a plurality of heat dissipation dish (2-2), a plurality of heat dissipation dishes (2-2) are fixed to pass in axis of rotation (2-1), cover (1) is double-phase to be connected with axis of rotation (2-1) to the inside wall rotation, a plurality of heat dissipation dishes (2-2) are worn out the cover groove.

4. The small and medium sized hovercraft cabin air heat dissipating device of claim 3, wherein: the plurality of heat dissipation discs (2-2) each include: two apron (2-2-1) and a plurality of fin (2-2-2), two apron (2-2-1) are coaxial, and the middle part is provided with apron hole (2-2-3), axis of rotation (2-1) pass apron hole (2-2-3) and two apron (2-2-1) fixed connection, two apron (2-2-1) relative medial surface equipartition fixed connection have a plurality of fin (2-2-2).

5. The small and medium sized hovercraft cabin air heat dissipating device of claim 4, wherein: the plurality of radiating fins (2-2-2) are made of copper.