Cross-medium aircraft

Abstract

The cross-medium aircraft comprises an aircraft body, a partition plate is arranged in the aircraft body and divides an inner cavity of the aircraft body into a water storage cabin section and an equipment cabin section, and the water storage cabin section and the equipment cabin section are arranged in series in the length direction of the aircraft body; the water storage cabin section is provided with a normally open air inlet / outlet and a water inlet / outlet, the air inlet / outlet is positioned above the waterline of the fuselage, and the water inlet / outlet is positioned below the waterline of the fuselage. The communicating vessel principle and the inertia principle are utilized, when the cross-medium aircraft floats on the water surface and is prepared to dive, water can automatically flow into the water storage cabin section through the gravity action and the communicating vessel principle, and it is guaranteed that the aircraft has enough weight and can dive into water; when the cross-medium aircraft floats on the water surface and prepares to take off, water can automatically flow out of the water storage cabin section under the action of gravity and inertia, so that the weight of the aircraft is reduced, and the cruising ability of the aircraft is guaranteed.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, concretely relates to a cross-media aircraft. BACKGROUND

[0002] The cross-media aircraft can move in water and air simultaneously, has the moving operation ability in two different media of water and air, and has a very broad application prospect.

[0003] One technical difficulty of the cross-media aircraft is how to separate from water and fly into air during the water-air transition period. At present, the cross-media aircraft mainly controls the buoyancy of the aircraft in water through a water discharge device similar to a submarine to realize floating in water to the water surface and then starting the power device to fly into air. For example, a multifunctional cross-media variable aircraft disclosed in CN117141170A and a water-air cross-media aircraft and system disclosed in CN119160428A. In actual production activities, the cross-media aircraft with the water submerging and floating control and the execution mechanism has the problems of complex structure and high failure rate, which is not conducive to long-term work. At the same time, the related submerging and floating control mechanism also increases the weight of the aircraft and reduces the air endurance of the aircraft.

[0004] Therefore, how to realize convenient adjustment of the buoyancy of the cross-media aircraft has become a technical problem to be solved by the technical personnel in the field. SUMMARY

[0005] Therefore, the utility model aims at providing a cross-media aircraft to solve the technical problems of the existing cross-media aircraft, such as complex structure and high failure rate.

[0006] The utility model adopts the technical scheme that a cross-media aircraft comprises a fuselage, a partition plate is arranged inside the fuselage, the partition plate divides the inner cavity of the fuselage into a water storage cabin section and an equipment cabin section, and the water storage cabin section and the equipment cabin section are arranged in series along the length direction of the fuselage; a normally open air inlet and outlet and a water inlet and outlet are arranged on the water storage cabin section, the air inlet and outlet are located above the waterline of the fuselage, and the water inlet and outlet are located below the waterline of the fuselage.

[0007] Preferably, along the length direction of the fuselage, the air inlet and outlet are located upstream of part or all of the water inlet and outlet.

[0008] Preferably, an auxiliary inlet and outlet are arranged on the water storage cabin section, and the auxiliary inlet and outlet are located at the position of the waterline of the fuselage.

[0009] Preferably, the air inlet and outlet, the water inlet and outlet and the auxiliary inlet and outlet are strip-shaped holes arranged along the length direction of the fuselage.

[0010] Preferably, the strip-shaped hole is an oval or rectangular hole.

[0011] Preferably, the length-width ratio of the strip-shaped hole is 1.5:1-6.5:1.

[0012] Preferably, the air inlet and outlet, the water inlet and outlet and the auxiliary inlet and outlet are arranged on both sides of the water storage cabin section.

[0013] Preferably, the partition plate comprises a front partition plate, an intermediate partition plate and a rear partition plate, the front partition plate is sealingly connected with the front end of the water storage cabin section, the rear partition plate is sealingly connected with the rear end of the water storage cabin section, the intermediate partition plate is sealingly connected between the front partition plate and the rear partition plate and divides the inner cavity of the water storage cabin section into a lower water storage cabin and an upper connecting passage, the top of the water storage cabin section is provided with a cabin door, and the upper connecting passage is in communication with the cabin door.

[0014] Preferably, the water storage cabin section comprises a middle water storage cabin section, and the middle water storage cabin section is arranged in the middle of the fuselage.

[0015] Preferably, the water storage cabin section comprises a nose water storage cabin section and a tail water storage cabin section, and the nose water storage cabin section and the tail water storage cabin section are symmetrically arranged on both sides of the center of gravity of the fuselage.

[0016] The utility model discloses the beneficial effect:

[0017] The utility model discloses utilize the principle of communicating vessel and inertia principle, first through the partition plate installed in the inner cavity of fuselage and divide the inner cavity of fuselage into the water storage cabin section and equipment cabin section of series arrangement, then through the water inlet and outlet and the air inlet and outlet of water storage cabin section, when the cross - medium aircraft floats on the water surface and prepares to dive, utilize gravity and the principle of communicating vessel, water can automatically flow into the water storage cabin section, guarantee aircraft has enough weight and can dive into the water, when the cross - medium aircraft floats on the water surface and prepares to take off, utilize gravity and inertia effect, water can automatically flow from the water storage cabin section, thereby reduced the weight of aircraft, guarantee the endurance of aircraft. ACCURACY OF DRAWINGS

[0018] Figure 1 It is one of the structure schematic drawing of the cross - medium aircraft of the utility model;

[0019] Figure 2 It is the second structure schematic drawing of the cross - medium aircraft of the utility model;

[0020] Figure 3 It is the first perspective schematic drawing of water storage cabin section;

[0021] Figure 4is a second perspective view of the water storage cabin section;

[0022] Figure 5 is a top view of the water storage cabin section;

[0023] Figure 6 is a bottom view of the water storage cabin section;

[0024] Figure 7 is a structural schematic view of the water storage cabin section.

[0025] Explanation of reference signs in the drawings:

[0026] 100, fuselage;

[0027] 110, water storage cabin section; 110a, nose water storage cabin section; 110b, middle water storage cabin section; 110c, tail water storage cabin section; 111, air inlet and outlet; 112, water inlet and outlet; 113, auxiliary inlet and outlet; 114, cabin door; 115, lower water storage cabin; 116, upper connecting passage; 120, equipment cabin section; 120a, nose equipment cabin section; 120b, middle equipment cabin section; 120c, tail equipment cabin section;

[0028] 200, partition; 210, front partition; 220, middle partition; 230, rear partition;

[0029] 300, wing. DETAILED DESCRIPTION

[0030] The specific embodiments of the present application will be further described in detail below with reference to the accompanying drawings. These embodiments are only used to illustrate the present application, and are not a limitation on the present application.

[0031] In the description of the present application, it should be noted that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0032] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0033] Furthermore, in the description of this utility model, unless otherwise stated, "a plurality of" means two or more.

[0034] Examples, such as Figures 1-7 As shown, a transmedia aircraft includes a fuselage 100 and wings 300, with the two wings 300 fixedly mounted on both sides of the fuselage 100 in the width direction.

[0035] A partition 200 is installed inside the fuselage 100, which divides the inner cavity of the fuselage 100 into a water storage compartment 110 and an equipment compartment 120, and the water storage compartment 110 and the equipment compartment 120 are arranged in series along the length of the fuselage 100.

[0036] An air inlet / outlet 111 and a water inlet / outlet 112 are provided on the water storage tank section 110. The air inlet / outlet 111 is located above the waterline of the fuselage 100, and the water inlet / outlet 112 is located below the waterline of the fuselage 100.

[0037] This invention utilizes the principles of communicating vessels and inertia. First, a partition 200 installed in the inner cavity of the fuselage 100 divides the inner cavity into a water storage compartment 110 and an equipment compartment 120 arranged in series. Then, by opening air inlets / outlets 111 and water inlets / outlets 112 on the water storage compartment 110, when the transmedium aircraft is floating on the water surface and preparing to submerge, water can automatically flow into the water storage compartment 110 using gravity and the principle of communicating vessels, ensuring that the aircraft has sufficient weight to submerge. When the transmedium aircraft is floating on the water surface and preparing to take off, water can automatically flow out of the water storage compartment 110 using gravity and inertia, thereby reducing the weight of the aircraft and ensuring its endurance.

[0038] Specific embodiment 1, such as Figure 1 , Figures 3-7 As shown, a transmedia aircraft includes a fuselage 100 and wings 300, with the two wings 300 fixedly mounted on both sides of the fuselage 100 in the width direction.

[0039] Two groups of partitions 200 are installed inside the fuselage 100, and are arranged at intervals along the length direction of the fuselage 100 to divide the inner cavity of the fuselage 100 into the nose equipment cabin section 120a, the nose water storage cabin section 110a, the middle equipment cabin section 120b, the tail water storage cabin section 110c and the tail equipment cabin section 120c, and the nose equipment cabin section 120a, the nose water storage cabin section 110a, the middle equipment cabin section 120b, the tail water storage cabin section 110c and the tail equipment cabin section 120c are arranged in series along the length direction of the fuselage 100, that is, from the nose to the tail direction, the nose equipment cabin section 120a, the nose water storage cabin section 110a, the middle equipment cabin section 120b, the tail water storage cabin section 110c and the tail equipment cabin section 120c are sequentially arranged, and the nose water storage cabin section 110a and the tail water storage cabin section 110c are symmetrically arranged on both sides of the gravity center position of the fuselage 100, so that the trans-medium aircraft has the same gravity center position in the air and in the water.

[0040] The in-out air ports 111 and the in-out water ports 112 are arranged on the nose water storage cabin section 110a and the tail water storage cabin section 110c, the in-out air ports 111 are located above the waterline of the fuselage 100, and two in-out air ports 111 are arranged on both sides of the water storage cabin section 110 in the width direction of the fuselage 100; the in-out water ports 112 are located below the waterline of the fuselage 100, and two or four in-out water ports 112 are symmetrically arranged on both sides of the water storage cabin section 110 in the width direction of the fuselage 100.

[0041] The in-out water ports 112 are arranged below the waterline of the fuselage 100, and the in-out air ports 111 are arranged above the waterline of the fuselage 100, when the trans-medium aircraft floats on the water surface and is ready to dive, water will automatically flow into the water storage cabin section 110 under the action of the communicating vessel, and the air in the water storage cabin section 110 will be automatically exhausted through the in-out air ports 111, thereby increasing the weight of the trans-medium aircraft, facilitating the sinking of the trans-medium aircraft into the water; when the trans-medium aircraft floats on the water surface and is ready to take off, water will flow out of the water storage cabin section 110 through the in-out water ports 112 under the action of gravity, and air will automatically flow into the water storage cabin section 110 through the in-out air ports 111, thereby reducing the weight of the trans-medium aircraft, facilitating the take-off of the trans-medium aircraft, and having good endurance.

[0042] Preferably, as shown in Figure 3 The in-out air ports 111 are located upstream of part or all of the in-out water ports 112 along the length direction of the fuselage 100, that is, when the bottom of the water storage cabin section 110 is provided with two in-out water ports 112, the in-out air ports 111 are arranged at the head of the water storage cabin section 110, and the in-out water ports 112 are arranged at the tail of the water storage cabin section 110; when the bottom of the water storage cabin section 110 is provided with four in-out water ports 112, the four in-out water ports 112 are arranged at the four top corners of the rectangle or trapezoid.

[0043] The reason for this arrangement is that, along the flight direction of the cross-medium aircraft, when the air inlet 111 is located upstream of the water inlet 112, the water in the water storage cabin section 110 can be more smoothly discharged by inertia when the aircraft takes off.

[0044] More preferably, as shown in Figure 7 Each set of partitions 200 includes a front partition 210, a middle partition 220, and a rear partition 230, the front and rear partitions 210 and 230 are arranged along the width direction of the fuselage 100, and the front partition 210 is sealingly connected to the front end of the water storage cabin section 110, and the rear partition 230 is sealingly connected to the rear end of the water storage cabin section 110; the middle partition 220 is arranged along the length direction of the fuselage 100, and is sealingly connected between the front and rear partitions 210 and 230, so that the inner cavity of the water storage cabin section 110 is divided into a lower water storage cabin 115 and an upper connecting passage 116 that are not connected to each other, the lower water storage cabin 115 is in communication with the air inlet 111 and the water inlet 112, and is used for temporarily storing water entering the cross-medium aircraft when in water. The upper connecting passage 116 communicates two equipment cabin sections 120 before and after the water storage cabin section 110, and is used to arrange related equipment lines.

[0045] An openable cabin door 114 is provided at the top of the water storage cabin section 110, and the upper connecting passage 116 is in communication with the cabin door 114.

[0046] Specific embodiment 2, as shown in Figures 2-7 A cross-medium aircraft includes a fuselage 100 and wings 300, and two wings 300 are fixedly installed on the two sides of the width direction of the fuselage 100 one by one.

[0047] Two partitions 200 are installed in the middle of the inner cavity of the fuselage 100, and the two partitions 200 are arranged at intervals along the length direction of the fuselage 100 to divide the inner cavity of the fuselage 100 into a nose equipment cabin section 120a, a middle water storage cabin section 110b, and a tail equipment cabin section 120c, and the nose equipment cabin section 120a, the middle water storage cabin section 110b, and the tail equipment cabin section 120c are arranged in series along the length direction of the fuselage 100, that is, from the nose to the tail direction, the nose equipment cabin section 120a, the middle water storage cabin section 110b, and the tail equipment cabin section 120c are sequentially arranged, and the center of gravity of the middle water storage cabin section 110b coincides with the center of gravity position of the fuselage 100, so that the cross-medium aircraft has the same center of gravity position in the air and in the water.

[0048] Specifically, the partition 200 includes a front partition 210 and a rear partition 230, both of which are arranged along the width direction of the fuselage 100. The front partition 210 is sealed to the front end of the water storage tank section 110, and the rear partition 230 is sealed to the rear end of the water storage tank section 110, so that the front partition 210, the rear partition 230 and the fuselage 100 form a temporary water storage chamber.

[0049] The central water storage tank section 110b is provided with normally open air inlets / outlets 111 and water inlets / outlets 112. The air inlets / outlets 111 are located above the waterline of the fuselage 100, and two air inlets / outlets 111 are arranged one-to-one on both sides of the water storage tank section 110 in the width direction of the fuselage 100. The water inlets / outlets 112 are located below the waterline of the fuselage 100, and two or four water inlets / outlets 112 are symmetrically arranged on both sides of the water storage tank section 110 in the width direction of the fuselage 100. Along the length direction of the fuselage 100, the air inlets / outlets 111 are located upstream of some or all of the water inlets / outlets 112.

[0050] Preferred, such as Figures 3-5 As shown, auxiliary inlets and outlets 113 are also provided on the central water storage tank section 110. The auxiliary inlets and outlets 113 are located at the waterline of the fuselage 100, and the two auxiliary inlets and outlets 113 are arranged one-to-one on both sides of the water storage tank section 110 in the width direction of the fuselage 100.

[0051] This configuration is because: after the auxiliary inlet / outlet 113 is opened at the waterline position of the water storage section 110, when the fuselage 100 takes in water through the inlet / outlet 112 and submerges, the water can automatically enter the water storage section 110 through the auxiliary inlet / outlet 113, thereby accelerating the speed at which the water automatically flows into the water storage section 110; when the fuselage 100 takes in air through the air inlet / outlet 111 and takes off, the air can automatically enter the water storage section 110 through the auxiliary inlet / outlet 113, thereby accelerating the speed at which the water flows out of the water storage section 110.

[0052] More preferably, such as Figures 3-6 As shown, the air inlet / outlet 111, water inlet / outlet 112, and auxiliary inlet / outlet 113 are all strip-shaped holes, such as elliptical or rectangular holes, arranged along the length of the body 100.

[0053] More preferably, the aspect ratio of the strip hole is 1.5:1 to 6.5:1.

[0054] The working principle of this transmedium aircraft is as follows:

[0055] The water storage cabin section is isolated from the equipment cabin section of the fuselage and is used as a temporary water storage cabin to assist the trans-medium aircraft to sink and float on the water surface.

[0056] Meanwhile, during the water intake and discharge process, the air inlet and outlet 111 always intakes and discharges air, the water inlet and outlet 112 always intakes and discharges water, and the auxiliary inlet and outlet 113 intakes and discharges both water and air according to the water level in the cabin, thereby improving the water intake and discharge efficiency.

[0057] Compared with the prior art, the utility model has at least the following beneficial technical effects:

[0058] The utility model skillfully uses the fuselage of a fixed-wing aircraft, designs part of the fuselage as a temporary water storage cabin, fills the temporary water storage cabin with water when the trans-medium aircraft sinks into the water, guarantees that the aircraft has enough weight to dive into the water, discharges the temporary water storage cabin when preparing to fly on the water surface, reduces the flight weight, guarantees the endurance of the aircraft, has no complicated control mechanism, has high reliability, and can be used in the fields of environmental detection, sea-air reconnaissance, marine biology research and the like.

[0059] The above is only the preferred embodiment of the utility model, and it should be pointed out that, for ordinary skilled persons in the technical field, several improvements and replacements can be made without departing from the technical principle of the utility model, and the improvements and replacements should also be regarded as the protection range of the utility model.

Claims

1. A trans-medium aircraft, characterized in that, The utility model relates to a kind of water storage cabin and equipment cabin, including: The fuselage (100) is internally provided with bulkhead (200), the bulkhead (200) separates the cavity in the fuselage (100) into water storage cabin section (110) and equipment cabin section (120), and the water storage cabin section (110) and equipment cabin section (120) are arranged in series along the length direction of the fuselage (100);Constantly open inlet and outlet air port (111) and inlet and outlet water port (112) are arranged on the water storage cabin section (110), the inlet and outlet air port (111) is located above the waterline of the fuselage (100), and the inlet and outlet water port (112) is located below the waterline of the fuselage (100).

2. A trans-medium vehicle according to claim 1, wherein, Along the length direction of the fuselage (100), the inlet and outlet air port (111) is located upstream of part or all of the inlet and outlet water port (112).

3. A trans-medium vehicle according to claim 2, wherein, The water storage cabin section (110) is provided with a constantly open auxiliary inlet and outlet (113), and the auxiliary inlet and outlet (113) is located at the waterline position of the fuselage (100).

4. A trans-medium vehicle according to claim 3, wherein, The inlet and outlet air port (111), the inlet and outlet water port (112) and the auxiliary inlet and outlet (113) are all strip-shaped holes arranged along the length direction of the fuselage (100).

5. A trans-medium vehicle according to claim 4, wherein, The strip-shaped hole is an oval or rectangular hole.

6. A trans-medium vehicle according to claim 4, wherein, The length-width ratio of the strip-shaped hole is 1.5:1~6.5:

1.

7. A trans-medium vehicle according to claim 4, wherein, The inlet and outlet air port (111), the inlet and outlet water port (112) and the auxiliary inlet and outlet (113) are all arranged on both sides of the water storage cabin section (110).

8. The trans-medium vehicle of claim 1, wherein, The bulkhead (200) includes a front bulkhead (210), an intermediate bulkhead (220) and a rear bulkhead (230), the front bulkhead (210) is sealingly connected to the front end of the water storage cabin section (110), the rear bulkhead (230) is sealingly connected to the rear end of the water storage cabin section (110), and the intermediate bulkhead (220) is sealingly connected between the front bulkhead (210) and the rear bulkhead (230) and separates the inner cavity of the water storage cabin section (110) into a lower water storage cabin (115) and an upper connecting passage (116), the top of the water storage cabin section (110) is provided with a hatch (114), and the upper connecting passage (116) communicates with the hatch (114).

9. A trans-medium vehicle according to any one of claims 1-8, wherein, The water storage cabin section (110) includes a middle water storage cabin section (110b), and the middle water storage cabin section (110b) is arranged at the middle of the fuselage (100).

10. A trans-medium vehicle according to any one of claims 1-8, wherein, The water storage cabin section (110) includes a nose water storage cabin section (110a) and a tail water storage cabin section (110c), and the nose water storage cabin section (110a) and the tail water storage cabin section (110c) are symmetrically arranged on both sides of the center of gravity of the fuselage (100).

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