CN114655435A - Oil-electricity hybrid power cross-medium unmanned aircraft with variable structure - Google Patents

Oil-electricity hybrid power cross-medium unmanned aircraft with variable structure Download PDF

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CN114655435A
CN114655435A CN202210298705.0A CN202210298705A CN114655435A CN 114655435 A CN114655435 A CN 114655435A CN 202210298705 A CN202210298705 A CN 202210298705A CN 114655435 A CN114655435 A CN 114655435A
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aircraft
wing
water
propulsion device
storage compartment
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CN114655435B (en
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钟文荣
杨俊男
马威龙
刘蒙永
蔡琦琳
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Suzhou University
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C35/00Flying-boats; Seaplanes
    • B64C35/008Amphibious sea planes
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B63SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63GOFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
    • B63G8/00Underwater vessels, e.g. submarines; Equipment specially adapted therefor
    • B63G8/001Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B63SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63GOFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
    • B63G8/00Underwater vessels, e.g. submarines; Equipment specially adapted therefor
    • B63G8/08Propulsion
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B63SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63GOFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
    • B63G8/00Underwater vessels, e.g. submarines; Equipment specially adapted therefor
    • B63G8/14Control of attitude or depth
    • B63G8/22Adjustment of buoyancy by water ballasting; Emptying equipment for ballast tanks
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof
    • B64C3/56Folding or collapsing to reduce overall dimensions of aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C35/00Flying-boats; Seaplanes
    • B64C35/005Flying-boats; Seaplanes with propellers, rudders or brakes acting in the water
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C37/00Convertible aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02Aircraft characterised by the type or position of power plants
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02Aircraft characterised by the type or position of power plants
    • B64D27/026Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/40Arrangements for mounting power plants in aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B63SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63GOFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
    • B63G8/00Underwater vessels, e.g. submarines; Equipment specially adapted therefor
    • B63G8/001Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations
    • B63G2008/002Underwater vessels adapted for special purposes, e.g. unmanned underwater vessels; Equipment specially adapted therefor, e.g. docking stations unmanned

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
  • Arrangement Or Mounting Of Propulsion Units For Vehicles (AREA)

Abstract

本发明涉及一种可变结构的油电混合动力跨介质无人航行器,包括机身,其内部设置有第一收纳舱和第二收纳舱,收纳舱设置有舱门,收纳舱中分别设置有第一伸缩装置和第二伸缩装置;可折叠式的机翼;可变构型尾翼;动力装置,动力装置包括燃油发电机组、蓄电池、第一推进装置和第二推进装置,第一推进装置与燃油发电机组连接,蓄电池与第二推进装置连接,第一推进装置和第二推进装置通过伸缩装置可收回至收纳舱中;进排水装置,进排水装置包括依次连接的压载水舱、空压机和储气罐,压载水舱连接有输送水口,本航行器具有更好的续航能力和更高的稳定性,无需单独附带氧化剂,且在水下航行时受到的阻力更小,能够快速灵活地在水中运行,适于实用。

Figure 202210298705

The invention relates to an oil-electric hybrid power cross-medium unmanned vehicle with a variable structure, comprising a fuselage, a first storage compartment and a second storage compartment are arranged inside the storage compartment, the storage compartment is provided with a hatch, and the storage compartments are respectively provided with There are a first telescopic device and a second telescopic device; foldable wings; variable configuration tail; It is connected with the fuel-fired generator set, the battery is connected with the second propulsion device, and the first propulsion device and the second propulsion device can be retracted into the storage compartment through the telescopic device; The compressor and air storage tank, and the ballast water tank is connected with a water delivery port. The aircraft has better endurance and higher stability, without the need for a separate oxidant, and has less resistance when sailing underwater. Fast and flexible operation in water, suitable for practical use.

Figure 202210298705

Description

一种可变结构的油电混合动力跨介质无人航行器A Variable-Structure Hydroelectric Hybrid Trans-medium Unmanned Vehicle

技术领域technical field

本发明涉及跨介质航行器技术领域,尤其是指一种可变结构的油电混合动力跨介质无人航行器。The invention relates to the technical field of cross-medium vehicles, in particular to a variable-structure oil-electric hybrid power cross-medium unmanned vehicle.

背景技术Background technique

跨介质航行器是一种可在空中和水中两栖巡航并能够自由穿越水-空界面的新概念两栖航行器,有着多方面的军民应用前景。尤其在军事上有海上躲避监视、侦察打击等多种作用。它结合了空中航行器和水下航行器的优点,与传统的单一介质航行器相比具有明显的优势。同时,不同于具有单次水空介质“穿越能力”的航行器(如空投鱼雷、潜射导弹等),它不仅具有空中飞行能力和水下潜航能力,还具有多次自由穿越水空界面的能力。目前,跨介质航行器根据不同的入水方式分为直接入水的跨介质航行器与先停留在水面上再下潜的跨介质航行器。Trans-medium vehicle is a new concept amphibious vehicle that can cruise in the air and water and can freely cross the water-air interface. It has various military and civilian application prospects. Especially in the military, it has many functions such as avoiding surveillance at sea, reconnaissance and strike. It combines the advantages of air vehicles and underwater vehicles, and has obvious advantages compared with traditional single-medium vehicles. At the same time, different from the aircraft with a single water-air medium "traversal ability" (such as air-dropped torpedoes, submarine-launched missiles, etc.), it not only has the ability to fly in the air and underwater diving, but also has the ability to freely traverse the water-air interface multiple times. ability. At present, trans-medium vehicles are classified into trans-medium vehicles that directly enter the water and trans-medium vehicles that stay on the water surface and then dive according to different water entry methods.

但是,现有的跨介质航行器多为纯电式或纯燃料式的航行器,其中纯电式航行器的续航能力较弱,且在低温条件下的可靠性较差,而纯燃料式航行器在水下航行时都需要单独附带氧化剂,增加了航行器的体积及使用成本;同时现有的跨介质航行器在水下航行时,其机身上的机翼、推进装置等外部结构会给航行器带来较大的阻力,影响航行器在水中的快速运行。However, the existing trans-medium vehicles are mostly pure electric or pure fuel vehicles, among which the pure electric vehicles have weak endurance and poor reliability under low temperature conditions, while pure fuel sailing vehicles The oxidant needs to be attached separately when the vehicle is sailing underwater, which increases the volume and cost of the vehicle; at the same time, when the existing trans-medium vehicle is sailing underwater, the external structures such as the wings and propulsion devices on the fuselage will be damaged. It brings greater resistance to the aircraft and affects the rapid operation of the aircraft in the water.

发明内容SUMMARY OF THE INVENTION

为此,本发明所要解决的技术问题在于克服现有技术中跨介质航行器多为纯电式或纯燃料式的航行器,其中纯电式航行器的续航能力较弱,且在低温条件下的可靠性较差,而纯燃料式航行器在水下航行时都需要单独附带氧化剂,增加航行器的体积及使用成本,同时现有的跨介质航行器在水下航行时,其机翼及推进装置等外部结构会给航行器带来较大的阻力,影响航行器在水中快速运行的问题;本发明提供一种可变结构的油电混合动力跨介质无人航行器,具有更好的续航能力和更高的稳定性,无需单独附带氧化剂,且在水下航行时受到的阻力更小,航行器能够快速灵活地在水中运行。Therefore, the technical problem to be solved by the present invention is to overcome the fact that most of the medium-span medium-span vehicles in the prior art are purely electric or pure-fuel vehicles, and the pure electric vehicle has a relatively weak endurance and is under low temperature conditions. The reliability of the vehicle is poor, and the pure fuel vehicle needs a separate oxidant when sailing underwater, which increases the volume and cost of the vehicle. External structures such as propulsion devices will bring greater resistance to the aircraft, which affects the problem of rapid operation of the aircraft in water; the present invention provides a variable-structure oil-electric hybrid power trans-medium unmanned vehicle, which has better performance. Endurance and higher stability, without the need for a separate oxidant, and less resistance when navigating underwater, the vehicle can operate quickly and flexibly in the water.

为解决上述技术问题,本发明提供了一种可变结构的油电混合动力跨介质无人航行器,包括,In order to solve the above-mentioned technical problems, the present invention provides an oil-electric hybrid power trans-medium unmanned vehicle with variable structure, including:

机身,所述机身设有输送水口以及位于机身内部的腔体,所述腔体内设置有第一收纳舱、第二收纳舱以及进排水装置,所述第一收纳舱和第二收纳舱中分别设置有第一伸缩装置和第二伸缩装置,所述进排水装置包括压载水舱,所述压载水舱与所述输送水口相连;The fuselage, the fuselage is provided with a conveying nozzle and a cavity inside the fuselage, the cavity is provided with a first storage compartment, a second storage compartment and a water inlet and outlet device, the first storage compartment and the second storage compartment A first telescopic device and a second telescopic device are respectively arranged in the tank, and the water intake and drainage device includes a ballast water tank, and the ballast water tank is connected with the water delivery port;

机翼,所述机翼为可折叠式机翼;a wing, the wing is a foldable wing;

尾翼;tail;

动力装置,所述动力装置设置于腔体内,所述动力装置包括燃油发电机组、蓄电池、第一推进装置和第二推进装置,所述第一推进装置与燃油发电机组连接,所述第二推进装置与蓄电池连接,且所述第一推进装置和第二推进装置分别与第一伸缩装置和第二伸缩装置连接;a power unit, the power unit is arranged in the cavity, the power unit includes a fuel-fired generator set, a battery, a first propulsion device and a second propulsion device, the first propulsion device is connected to the fuel-fired generator set, and the second propulsion device the device is connected to the battery, and the first propulsion device and the second propulsion device are respectively connected to the first telescopic device and the second telescopic device;

航行器飞行前,打开所述第一收纳舱,所述第一伸缩装置将所述第一推进装置推出第一收纳舱外,为航行器提供飞行时的动力;航行器从空中潜入水下前,所述第一伸缩装置带动所述第一推进装置收回至所述第一收纳舱内,且将所述第一收纳舱封闭,同时打开所述输送水口,使水进入所述压载水舱中以辅助航行器下潜;航行器进入水中后,所述第二收纳舱打开,所述第二伸缩装置将第二推进装置推出第二收纳舱外,为航行器提供水下航行时的动力。Before the aircraft flies, the first storage compartment is opened, and the first telescopic device pushes the first propulsion device out of the first storage compartment to provide power for the aircraft during flight; before the aircraft dives into the water from the air , the first telescopic device drives the first propulsion device to retract into the first storage compartment, closes the first storage compartment, and simultaneously opens the water delivery port to allow water to enter the ballast water tank China-Israel assists the craft to dive; after the craft enters the water, the second storage compartment is opened, and the second telescopic device pushes the second propulsion device out of the second storage compartment to provide the craft with power during underwater navigation .

在本发明的一个实施例中,所述腔体内设置有用于贮存机翼的机翼存储舱,所述机翼靠近机身的一端设置于所述机翼存储舱内,所述机身上设置有与机翼存储舱匹配的存储舱舱门。In an embodiment of the present invention, a wing storage compartment for storing wings is arranged in the cavity, and one end of the wing close to the fuselage is arranged in the wing storage compartment, and a wing storage compartment is arranged on the fuselage. There are storage bay doors that match the wing storage bays.

在本发明的一个实施例中,所述机翼包括主翼和副翼,所述主翼包括多个翼板,多个所述翼板依次活动连接组成所述主翼,所述主翼远离机身的一个翼板作为第一翼板,所述副翼设置于第一翼板上,且除所述第一翼板外的其它各翼板上均设置有襟翼。In an embodiment of the present invention, the wing includes a main wing and an aileron, the main wing includes a plurality of wing plates, and the plurality of wing plates are movably connected in sequence to form the main wing, and the main wing is far from one of the fuselage. The wing plate is used as the first wing plate, the aileron is arranged on the first wing plate, and the other wing plates except the first wing plate are provided with flaps.

在本发明的一个实施例中,所述机身包括依次连接的机头、机腹和机尾,所述水口设置于所述机头上,所述机翼连接于所述机腹上,所述尾翼安装于所述机尾上。In an embodiment of the present invention, the fuselage includes a nose, a belly and a tail that are connected in sequence, the nozzle is arranged on the nose, and the wings are connected to the belly, so The tail is mounted on the tail of the aircraft.

在本发明的一个实施例中,所述尾翼包括垂直尾翼和水平尾翼,所述垂直尾翼竖直设置于机尾上,所述垂直尾翼上设置有第一方向舵,所述水平尾翼水平设置于机尾上,所述水平尾翼包括位于机身两侧的翻折段,所述翻折段上均设置有第二方向舵,所述翻折段用于在其翻折至竖直方向后对航行器的运动方向进行控制。In one embodiment of the present invention, the tail includes a vertical tail and a horizontal tail, the vertical tail is vertically arranged on the tail, the vertical tail is provided with a first rudder, and the horizontal tail is horizontally arranged on the tail , the horizontal stabilizer includes a folded section located on both sides of the fuselage, and a second rudder is arranged on the said folded section, and the said folded section is used for the movement of the aircraft after it is folded to the vertical direction direction control.

在本发明的一个实施例中,所述第一收纳舱上设置有进气口,所述进气口通过气管与燃油发电机组连接,且所述气管内设置有鼓风装置和电子阀门。In an embodiment of the present invention, the first storage compartment is provided with an air inlet, the air inlet is connected to the fuel generator set through an air pipe, and a blower device and an electronic valve are arranged in the air pipe.

在本发明的一个实施例中,所述进排水装置还包括压力装置,所述压力装置包括空压机和储气罐,所述空压机连接所述储气罐,所述储气罐连接所述压载水舱。In an embodiment of the present invention, the water intake and drainage device further includes a pressure device, the pressure device includes an air compressor and an air storage tank, the air compressor is connected to the air storage tank, and the air storage tank is connected to the ballast water tank.

在本发明的一个实施例中,所述第二收纳舱通过管道与压载水舱连接,且所述管道中设置有单向阀。In an embodiment of the present invention, the second storage compartment is connected to the ballast water tank through a pipeline, and a one-way valve is provided in the pipeline.

在本发明的一个实施例中,还包括辅助装置,所述辅助装置包括应急电源和信号装置,所述应急电源用于紧急供电,所述信号装置用于接收指令并回传航行器状态信息。In an embodiment of the present invention, an auxiliary device is further included, the auxiliary device includes an emergency power supply and a signal device, the emergency power supply is used for emergency power supply, and the signal device is used for receiving commands and returning aircraft state information.

在本发明的一个实施例中,所述第一推进装置为电驱动涵道风扇发动机,所述第二推进装置为电驱动涵道式螺旋桨水推进器。In an embodiment of the present invention, the first propulsion device is an electrically driven ducted fan engine, and the second propulsion device is an electrically driven ducted propeller water propeller.

本发明的上述技术方案相比现有技术具有以下优点:The above-mentioned technical scheme of the present invention has the following advantages compared with the prior art:

本发明所述的一种可变结构的油电混合动力跨介质无人航行器,采用油电混合动力,相比于纯电动式航行器或纯燃料式航行器具有更好的续航能力和运行稳定性,并且在航行时,无需单独携带氧化剂,可以节省航行器的内部空间,减小航行器的整体体积及使用成本;且将机翼设置为可折叠的机翼,同时将推进装置分为飞行推进装置和水下航行推进装置,航行器在水下航行时,机翼及飞行推进装置可以收回,减小航行器在水下航行时受到的阻力,节省能源的同时,航行器具有了更快的航行速度和灵活性,适于实用。The oil-electric hybrid power trans-medium unmanned vehicle with variable structure according to the present invention adopts the oil-electric hybrid power, and has better endurance and operation than pure electric aircraft or pure fuel aircraft. It is stable, and when sailing, there is no need to carry an oxidant separately, which can save the interior space of the aircraft, reduce the overall volume and use cost of the aircraft; and the wings are set as foldable wings, and the propulsion device is divided into Flight propulsion device and underwater navigation propulsion device, when the aircraft is sailing underwater, the wings and flight propulsion device can be retracted, reducing the resistance of the aircraft when sailing underwater, saving energy, and the aircraft has more features. Fast sailing speed and flexibility, suitable for practical use.

附图说明Description of drawings

为了使本发明的内容更容易被清楚的理解,下面根据本发明的具体实施例并结合附图,对本发明作进一步详细的说明,其中In order to make the content of the present invention easier to understand clearly, the present invention will be described in further detail below according to specific embodiments of the present invention and in conjunction with the accompanying drawings, wherein

图1为本发明优选实施例的可变结构的油电混合动力跨介质无人航行器的整体结构示意图;FIG. 1 is a schematic diagram of the overall structure of an oil-electric hybrid trans-medium unmanned vehicle with a variable structure according to a preferred embodiment of the present invention;

图2为图1所示可变结构的油电混合动力跨介质无人航行器的侧视图;Fig. 2 is a side view of the oil-electric hybrid trans-medium unmanned vehicle with variable structure shown in Fig. 1;

图3为图1所示可变结构的油电混合动力跨介质无人航行器的俯视图;FIG. 3 is a top view of the oil-electric hybrid trans-medium unmanned vehicle with variable structure shown in FIG. 1;

图4为图1所示可变结构的油电混合动力跨介质无人航行器的内部结构的示意图;FIG. 4 is a schematic diagram of the internal structure of the oil-electric hybrid power trans-medium unmanned vehicle with variable structure shown in FIG. 1;

图5为图1所示可变结构的油电混合动力跨介质无人航行器的部分结构的示意图。FIG. 5 is a schematic diagram of part of the structure of the variable-structure oil-electric hybrid trans-medium unmanned aerial vehicle shown in FIG. 1 .

说明书附图标记说明:1、机身;11、输送水口;12、腔体;13、第一收纳舱;131、进气口;14、第二收纳舱;15、进排水装置;151、压载水舱;152、空压机;153、储气罐;16、前起落架;17、后起落架;2、机翼;21、主翼;211、翼板;22、副翼;23、襟翼;3、尾翼;31、垂直尾翼;311、第一方向舵;32、水平尾翼;321、翻折段;322、第二方向舵;4、动力装置;41、燃油发电机组;42、蓄电池;43、第一推进装置;44、第二推进装置。Description of reference numerals in the manual: 1. Body; 11. Water inlet; 12. Cavity; 13. First storage compartment; 131. Air inlet; 14. Second storage compartment; 15. Intake and drainage device; water tank; 152, air compressor; 153, air storage tank; 16, nose landing gear; 17, rear landing gear; 2, wing; 21, main wing; 211, wing plate; 22, aileron; 23, flap Wing; 3. Tail; 31. Vertical Tail; 311, First Rudder; 32, Horizontal Tail; 321, Folding Section; 322, Second Rudder; 4. Power Plant; 41, Fuel Generator Set; 42, Battery; 43 , the first propulsion device; 44, the second propulsion device.

具体实施方式Detailed ways

下面结合附图和具体实施例对本发明作进一步说明,以使本领域的技术人员可以更好地理解本发明并能予以实施,但所举实施例不作为对本发明的限定。The present invention will be further described below with reference to the accompanying drawings and specific embodiments, so that those skilled in the art can better understand the present invention and implement it, but the embodiments are not intended to limit the present invention.

实施例一Example 1

参照图1-图4所示,本发明的一种可变结构的油电混合动力跨介质无人航行器,包括,1-4, a variable-structure oil-electric hybrid trans-medium unmanned vehicle of the present invention includes,

机身1,机身1设有输送水口11以及位于机身1内部的腔体12,腔体12内设置有第一收纳舱13、第二收纳舱14以及进排水装置15,第一收纳舱13和第二收纳舱14中分别设置有第一伸缩装置和第二伸缩装置,进排水装置15包括压载水舱151,压载水舱151与输送水口11相连;The fuselage 1 is provided with a delivery nozzle 11 and a cavity 12 located inside the fuselage 1. The cavity 12 is provided with a first storage compartment 13, a second storage compartment 14 and an intake and drainage device 15. The first storage compartment 13 and the second storage compartment 14 are respectively provided with a first telescopic device and a second telescopic device, the intake and drainage device 15 includes a ballast water tank 151, and the ballast water tank 151 is connected to the water delivery port 11;

机翼2,机翼2为可折叠式机翼;Wing 2, wing 2 is a foldable wing;

尾翼3;tail 3;

动力装置4,动力装置4设置于腔体12内,动力装置4包括燃油发电机组41、蓄电池42、第一推进装置43和第二推进装置44,第一推进装置43与燃油发电机组41连接,第二推进装置44与蓄电池42连接,且第一推进装置43和第二推进装置44分别与第一伸缩装置和第二伸缩装置连接;The power unit 4 is arranged in the cavity 12. The power unit 4 includes a fuel-fired generator set 41, a battery 42, a first propulsion device 43 and a second propulsion device 44. The first propulsion device 43 is connected to the fuel-fired generator set 41. The second propulsion device 44 is connected to the battery 42, and the first propulsion device 43 and the second propulsion device 44 are respectively connected to the first telescopic device and the second telescopic device;

航行器飞行前,打开第一收纳舱13,第一伸缩装置将第一推进装置43推出第一收纳舱13外,为航行器提供飞行时的动力;航行器从空中潜入水下前,第一伸缩装置带动第一推进装置43收回至第一收纳舱13内,且将第一收纳舱13封闭,同时打开输送水口11,使水进入压载水舱151中以辅助航行器下潜;航行器进入水中后,第二收纳舱14打开,第二伸缩装置将第二推进装置44推出第二收纳舱14外,为航行器提供水下航行时的动力。Before the aircraft flies, the first storage compartment 13 is opened, and the first telescopic device pushes the first propulsion device 43 out of the first storage compartment 13 to provide power for the aircraft during flight; before the aircraft dives into the water from the air, the first The telescopic device drives the first propulsion device 43 to retract into the first storage compartment 13, closes the first storage compartment 13, and simultaneously opens the delivery nozzle 11 to allow water to enter the ballast water tank 151 to assist the aircraft to dive; After entering the water, the second storage compartment 14 is opened, and the second telescopic device pushes the second propulsion device 44 out of the second storage compartment 14 to provide the vehicle with power during underwater navigation.

具体的,机身1上设置有分别与第一收纳舱13和第二收纳舱14位置相对应的第一舱门和第二舱门;第一收纳舱13在机身1的宽度方向上对称设置有多个,机身1上与第一收纳舱13对应的第一舱门同样也设置有多个,每个第一收纳舱13中均设置有第一伸缩装置,第一伸缩装置连接第一推进装置43,第一推进装置43可以是电驱动涵道风扇发动机;第一舱门打开时,第一伸缩装置可以将第一推进装置43顶出第一收纳舱13外为航行器提供飞行时的动力,且第一伸缩装置也可以将第一推进装置43收回第一收纳舱13中,并通过第一舱门将第一收纳舱13封闭起来;可以想到的是,在航行器进入水下航行时,若将第一推进装置43收回机身1内部,可以减小航行器在水下运动时受到的阻力,保证航行器快速灵活地运动;同时可以想到的是,通过第一舱门将第一推进装置43封闭在第一收纳舱13中,可以在水下航行时将第一推进装置43很好地保护起来。Specifically, the fuselage 1 is provided with a first cabin door and a second cabin door corresponding to the positions of the first storage cabin 13 and the second storage cabin 14 respectively; the first storage cabin 13 is symmetrical in the width direction of the fuselage 1 . There are a plurality of first doors on the fuselage 1 corresponding to the first storage compartments 13. A first telescopic device is provided in each of the first storage compartments 13, and the first telescopic device is connected to the first compartment. A propulsion device 43, the first propulsion device 43 can be an electric drive ducted fan engine; when the first hatch is opened, the first telescopic device can push the first propulsion device 43 out of the first storage compartment 13 to provide flight for the aircraft and the first telescopic device can also retract the first propulsion device 43 into the first storage compartment 13, and close the first storage compartment 13 through the first hatch; it is conceivable that when the aircraft enters underwater When sailing, if the first propulsion device 43 is retracted into the fuselage 1, the resistance of the aircraft during underwater movement can be reduced, and the aircraft can move quickly and flexibly; A propulsion device 43 is enclosed in the first storage compartment 13, so that the first propulsion device 43 can be well protected during underwater navigation.

可以想到的是,第一伸缩装置可以是气缸或电动推杆等小型伸缩装置。It is conceivable that the first telescopic device may be a small telescopic device such as an air cylinder or an electric push rod.

具体的,第二收纳舱14设置于靠近机尾的位置,第二推进装置44设置于第二收纳舱14中,且第二推进装置44连接第二伸缩装置;当航行器在进入水下航行时,第一推进装置43收回第一收纳舱13中并通过第一舱门进行封闭隔离;第二舱门打开,第二伸缩装置将第二推进装置44顶出,为航行器提供水下航行时的动力。Specifically, the second storage compartment 14 is arranged near the tail of the aircraft, the second propulsion device 44 is arranged in the second storage compartment 14, and the second propulsion device 44 is connected to the second telescopic device; when the aircraft enters underwater sailing At the time, the first propulsion device 43 is retracted into the first storage compartment 13 and closed and isolated through the first hatch; the second hatch is opened, and the second telescopic device pushes out the second propulsion device 44 to provide underwater navigation for the aircraft power of time.

具体的,当航行器要在水中下潜时,输送水口11打开使水灌入压载水舱151中,在水进入压载水舱151的过程中,空压机152运行,将压载水舱151内的空气抽进储气罐153中,当压载水舱151中具有一定量的水时,航行器的自重增加,方便下潜;当航行器上浮时,空压机152运行,将储气罐153中存储的高压气体输入压载水舱151中,使压载水舱151中的水从输送水口11处排出,以使航行器可以进行上浮。Specifically, when the aircraft is about to dive in the water, the water delivery port 11 is opened so that the water is poured into the ballast water tank 151 . During the process of water entering the ballast water tank 151 , the air compressor 152 runs, and the ballast water is poured into the ballast water tank 151 . The air in the cabin 151 is pumped into the air storage tank 153. When there is a certain amount of water in the ballast water tank 151, the weight of the aircraft increases, which is convenient for diving; when the aircraft floats, the air compressor 152 runs to The high-pressure gas stored in the gas storage tank 153 is input into the ballast water tank 151, so that the water in the ballast water tank 151 is discharged from the water delivery port 11, so that the aircraft can float.

航行器采用油电混合的动力方式,兼具燃料式和纯电式航行器的优点,具有较好的续航能力以及稳定性,不需要单独设置氧化剂;且在航行器飞行时,第二推进装置44可以收回机身1内部,降低航行器受到的阻力,同时航行器在水下运动时,第一推进装置43也可以收回机身1的内部,减小航行器在水下受到的阻力,减少能源消耗的同时,在一定程度上可以使航行器运动的过程更稳定、更灵活。The aircraft adopts a hybrid power mode of oil and electricity, which combines the advantages of fuel-based and pure-electric aircraft, with good endurance and stability, and does not require a separate oxidant; and when the aircraft is flying, the second propulsion device 44 can be retracted inside the fuselage 1 to reduce the resistance of the aircraft. At the same time, when the aircraft is moving underwater, the first propulsion device 43 can also be retracted into the interior of the fuselage 1 to reduce the underwater resistance of the aircraft and reduce the At the same time of energy consumption, it can make the process of vehicle movement more stable and flexible to a certain extent.

进一步的,腔体12内设置有用于贮存机翼2的机翼存储舱,机翼2靠近机身1的一端设置于机翼存储舱内,机身1上设置有与机翼存储舱匹配的存储舱舱门。Further, the cavity 12 is provided with a wing storage compartment for storing the wing 2, the end of the wing 2 close to the fuselage 1 is arranged in the wing storage compartment, and the fuselage 1 is provided with a matching wing storage compartment. Storage compartment door.

具体的,机身1内部的腔体12中设置有机翼存储舱,机翼2在折叠后可以收回机翼存储舱内,并通过存储舱舱门将机翼2封闭在机翼存储舱中;可以想到的是,在航行器进入水下航行时,展开的机翼2会受到较大的阻力,影响航行器的快速航行;在将机翼2折叠收入机身1内部后,航行器受到的阻力会大大减小,可以提高航行器的运动速度,并降低电源的消耗,同时也可以避免机翼2在水下受到侵蚀和损伤。Specifically, the cavity 12 inside the fuselage 1 is provided with a wing storage compartment, the wing 2 can be retracted into the wing storage compartment after being folded, and the wing 2 is enclosed in the wing storage compartment through the storage compartment door; What comes to mind is that when the aircraft enters underwater sailing, the unfolded wings 2 will be subject to greater resistance, which will affect the speed of the aircraft; will be greatly reduced, the movement speed of the aircraft can be increased, the power consumption can be reduced, and the erosion and damage of the wing 2 under water can also be avoided.

更优的,存储舱舱门、第一舱门和第二舱门均可以设置为电动滑盖式的舱门,并在舱门与机身1结合处设置密封条,保证舱门关闭后的密封性。More preferably, the storage cabin door, the first cabin door and the second cabin door can all be set as electric sliding lid type cabin doors, and a sealing strip is arranged at the joint of the cabin door and the fuselage 1 to ensure that the cabin door is closed. tightness.

参照图3所示,进一步的,机翼2包括主翼21和副翼22,主翼21包括多个翼板211,多个翼板211依次活动连接组成主翼21,主翼21远离机身1的一个翼板211作为第一翼板,副翼22设置于第一翼板上,且除第一翼板外的其它各翼板211上均设置有襟翼23。Referring to FIG. 3 , further, the wing 2 includes a main wing 21 and an aileron 22 , the main wing 21 includes a plurality of wing plates 211 , and the plurality of wing plates 211 are movably connected in turn to form the main wing 21 , and the main wing 21 is far from a wing of the fuselage 1 . The plate 211 is used as the first wing plate, the ailerons 22 are arranged on the first wing plate, and the other wing plates 211 except the first wing plate are provided with flaps 23 .

具体的,主翼21包括多个单块式的翼板211,相邻的翼板211活动连接组成主翼21,主翼21可以进行风琴式的折叠使各个翼板211在竖直方向上堆叠起来,以方便在机翼2折叠后收回机身1内部;且将距离机身1最远的一个翼板211作为第一翼板,并在第一翼板靠近机尾的一侧设置副翼22,副翼22用于控制航行器进行翻转,同时在除第一翼板以外的其它翼板211上均设置襟翼23,襟翼23可以起到增加升力的作用。Specifically, the main wing 21 includes a plurality of single-piece wing plates 211, and adjacent wing plates 211 are movably connected to form the main wing 21, and the main wing 21 can be folded in an accordion style so that each wing plate 211 is vertically stacked to form the main wing 21. It is convenient to retract the inside of the fuselage 1 after the wing 2 is folded; and the one wing plate 211 farthest from the fuselage 1 is used as the first wing plate, and the aileron 22 is set on the side of the first wing plate close to the tail The wings 22 are used to control the aircraft to turn over, and at the same time, flaps 23 are provided on the other wing plates 211 except the first wing plate, and the flaps 23 can play the role of increasing lift.

可以想到的是,机翼2可以设置为能够自动进行收放的机翼2,以提高整个航行器的自动化程度,保证航行器在两种介质中运行时形态的快速转换。机翼2采用轻质材料制成,如聚丙烯材料。It is conceivable that the wing 2 can be set as the wing 2 that can be retracted and retracted automatically, so as to improve the automation degree of the entire aircraft and ensure the rapid change of the shape of the aircraft when it operates in the two media. The wing 2 is made of lightweight material such as polypropylene.

参照图2所示,进一步的,机身1包括依次连接的机头、机腹和机尾,输送水口11设置于机头上,机翼2连接于机腹上,尾翼3安装于机尾上。机腹上设置有断阶,以增大航行器在水面滑行时的承受能力,也便于航行器从水面进行起飞。Referring to Figure 2, further, the fuselage 1 includes a nose, a belly and a tail that are connected in sequence, the delivery nozzle 11 is arranged on the nose, the wing 2 is connected to the belly, and the tail 3 is installed on the tail. There are broken steps on the belly of the aircraft to increase the bearing capacity of the aircraft when it is gliding on the water surface, and it is also convenient for the aircraft to take off from the water surface.

可以想到的是,因为机身1为空腔式的结构,所以整个机身1是可以浮在水面上的,并且配合动力装置4可以在水面上进行滑行。It is conceivable that because the fuselage 1 has a cavity-type structure, the entire fuselage 1 can float on the water surface, and can glide on the water surface with the power device 4 .

同时还可以想到的是,在机身1内设置各个部件时,应当考虑整个航行器的平衡性,对各部件的位置进行合理的分配。例如,第一收纳舱13设置在靠近机翼2的位置,第二收纳舱14的位置应当设置在靠近机尾的位置,以平衡机身1。At the same time, it is also conceivable that when arranging various components in the fuselage 1, the balance of the entire aircraft should be considered, and the positions of each component should be reasonably allocated. For example, the first storage compartment 13 should be arranged near the wing 2 , and the second storage compartment 14 should be arranged near the tail of the aircraft to balance the fuselage 1 .

参照图1、图2、图3和图5所示,进一步的,尾翼3包括垂直尾翼31和水平尾翼32,垂直尾翼31竖直设置于机尾上,垂直尾翼31上设置有第一方向舵311,水平尾翼32水平设置于机尾上,水平尾翼32包括位于机身1两侧的翻折段321,翻折段321上均设置有第二方向舵322,翻折段321用于在其翻折至竖直方向后对航行器的运动方向进行控制。1, 2, 3 and 5, further, the tail 31 includes a vertical tail 31 and a horizontal tail 32, the vertical tail 31 is vertically arranged on the tail, and the vertical tail 31 is provided with a first rudder 311, The horizontal tail 32 is horizontally arranged on the tail of the aircraft. The horizontal tail 32 includes folding sections 321 located on both sides of the fuselage 1. The folding sections 321 are all provided with second rudders 322, and the folding sections 321 are used to be folded vertically. Control the movement direction of the vehicle after the straight direction.

具体的,尾翼3采用可变构型尾翼,当航行器进入水下时,水平尾翼32的两个翻折段321可以向下翻折至竖直状态,此时水平尾翼32的两个翻折段321与垂直尾翼31平行,通过控制垂直尾翼31和水平尾翼32上的第一方向舵311和第二方向舵322,可以对航行器的航行方向进行控制,其中,当第一方向舵311和第二方向舵322向同方向偏转时,航向器做偏转运动;当第一方向舵311和第二方向舵322的偏转方向相反时,航行器做滚转运动。Specifically, the tail 3 adopts a variable configuration tail. When the aircraft enters the water, the two folded sections 321 of the horizontal tail 32 can be folded down to a vertical state. At this time, the two folded sections of the horizontal tail 32 The section 321 is parallel to the vertical tail 31. By controlling the first rudder 311 and the second rudder 322 on the vertical tail 31 and the horizontal tail 32, the sailing direction of the aircraft can be controlled, wherein when the first rudder 311 and the second rudder When the 322 is deflected in the same direction, the navigator makes a yaw motion; when the deflection directions of the first rudder 311 and the second rudder 322 are opposite, the navigator makes a roll motion.

可以想到的是,航行器在水下运动时,水平尾翼32的翻折段321翻折至与垂直尾翼31平行的状态,可以增加航行在水中运行时的稳定性;同时,水平尾翼32的翻折段321可以当做垂直尾翼31的扩展,在一定程度上增加了垂直尾翼31的面积,使航行器在偏转时更加灵活。且航行器通过滚转运动,可以进行调整平衡等动作。尾翼3也采用轻质材料,如聚丙烯等材料。It is conceivable that when the aircraft is moving underwater, the folded section 321 of the horizontal tail 32 is folded to a state parallel to the vertical tail 31, which can increase the stability of sailing in the water; at the same time, the turning of the horizontal tail 32 The folded section 321 can be used as an extension of the vertical tail 31, which increases the area of the vertical tail 31 to a certain extent and makes the aircraft more flexible when deflecting. And the aircraft can adjust the balance and other actions through the rolling motion. The rear wing 3 is also made of lightweight materials such as polypropylene.

可以想到的是,在机尾中靠近尾翼3的位置可以设置驱动组件,以驱动水平尾翼32的两个翻折段321可以进行旋转翻折;驱动组件可以为由驱动源驱动转的旋转件,通过旋转件带动与其连接的翻折段321进行转动。It is conceivable that a drive assembly can be provided in the tail near the tail 3 to drive the two turning segments 321 of the horizontal tail 32 to rotate and fold; the drive assembly can be a rotating member driven by a drive source, The turn-over segment 321 connected with the turn-over segment 321 is driven to rotate by the rotating member.

参照图2所示,进一步的,第一收纳舱13上设置有进气口131,进气口131通过气管与燃油发电机组41连接,且气管内设置有鼓风装置和电子阀门。具体的,当航行器要进行飞行时,机身1上的第一舱门打开,空气通过第一收纳舱13连接的气管进入燃油发电机组41中为其提供氧化剂;同时气管内的鼓风装置和电子阀门配合,可以对进气量进行控制;具体的,当电子阀门打开时,空气可以通过气管进入燃油发电机组41中,同时通过鼓风机的作用,可以对进气量的大小进行控制;当电子阀门关闭时,空气无法进入燃油发电机组41中。Referring to FIG. 2 , further, the first storage compartment 13 is provided with an air inlet 131 , and the air inlet 131 is connected to the fuel generator set 41 through a gas pipe, and a blower device and an electronic valve are arranged in the gas pipe. Specifically, when the aircraft is about to fly, the first hatch on the fuselage 1 is opened, and air enters the fuel generator set 41 through the trachea connected to the first storage compartment 13 to provide oxidant for it; at the same time, the blower device in the trachea In cooperation with the electronic valve, the intake air volume can be controlled; specifically, when the electronic valve is opened, the air can enter the fuel generator set 41 through the air pipe, and at the same time, the intake air volume can be controlled by the action of the blower; When the electronic valve is closed, air cannot enter the fuel generator set 41.

参照图4所示,进一步的,进排水装置15还包括压力装置,压力装置包括空压机152和储气罐153,空压机152连接储气罐153,储气罐153连接压载水舱151。Referring to FIG. 4 , further, the water intake and drainage device 15 further includes a pressure device, the pressure device includes an air compressor 152 and an air storage tank 153 , the air compressor 152 is connected to the air storage tank 153 , and the air storage tank 153 is connected to the ballast water tank 151.

进一步的,第二收纳舱14通过管道与压载水舱151连接,且管道中设置有单向阀。具体的,单向阀限制水可以从第二收纳舱14端进入压载水舱151中,但是压载水舱151中的水不能进入第二收纳舱14中。Further, the second storage compartment 14 is connected to the ballast water tank 151 through a pipeline, and a one-way valve is arranged in the pipeline. Specifically, the one-way valve restricts that water can enter the ballast water tank 151 from the end of the second storage compartment 14 , but the water in the ballast water tank 151 cannot enter the second storage compartment 14 .

进一步的,还包括辅助装置,辅助装置包括应急电源和信号装置,应急电源用于紧急供电,信号装置用于接收指令并回传航行器状态信息。可以想到的是,当航行器中的燃料及蓄电池42的电力均被耗尽时,可以通过航行器内的应急电源对航行器进行紧急供电。Further, an auxiliary device is also included. The auxiliary device includes an emergency power supply and a signal device. The emergency power supply is used for emergency power supply, and the signal device is used for receiving commands and returning the state information of the aircraft. It is conceivable that when both the fuel in the aircraft and the power of the battery 42 are exhausted, the aircraft can be powered by an emergency power supply in the aircraft.

进一步的,第一推进装置43为电驱动涵道风扇发动机,第二推进装置44为电驱动涵道式螺旋桨水推进器。航行器在飞行时,通过电驱动涵道风扇发动机提供动力,航行器在水下航行时,通过涵道式螺旋桨水推进器提供动力。其中,燃油发电机组41为第一推进装置43提供电力,蓄电池42主要为第二推进装置44提供电力,同时也可在燃油发电机组41燃料箱内的燃料耗尽时为第一推进装置43提供电力。Further, the first propulsion device 43 is an electrically driven ducted fan engine, and the second propulsion device 44 is an electrically driven ducted propeller water propeller. When the vehicle is flying, it is powered by an electrically driven ducted fan engine, and when the vehicle is sailing underwater, it is powered by a ducted propeller water propulsion. The fuel-fired generator set 41 provides power for the first propulsion device 43 , and the battery 42 mainly provides power for the second propulsion device 44 , and can also provide power for the first propulsion device 43 when the fuel in the fuel tank of the fuel-fired generator set 41 is exhausted. electricity.

更优的,燃油发电机组41与蓄电池42连接,蓄电池42与第一推进装置43连接。可以想到的是,当航行器的燃料箱中的燃料在运动过程中燃料耗尽时,蓄电池42可以为第一推进装置43继续供电,以免因燃料突然耗尽造成航行器坠落损坏。具体的,当航行器在低空飞行时,燃油发电机组41通过汲取燃料箱中的燃料以及从外部吸入的空气燃烧发电,并将其中大部分电力(约95%)用来提供涵道风扇发动机所需的电力,少部分电力(约5%)用于补充蓄电池42的电力。More preferably, the fuel generator set 41 is connected to the battery 42 , and the battery 42 is connected to the first propulsion device 43 . It is conceivable that when the fuel in the fuel tank of the aircraft runs out of fuel during the movement, the battery 42 can continue to supply power to the first propulsion device 43, so as to avoid falling damage to the aircraft due to the sudden exhaustion of fuel. Specifically, when the aircraft is flying at a low altitude, the fuel-fired generator set 41 generates electricity by drawing fuel in the fuel tank and the air sucked in from the outside, and uses most of the electricity (about 95%) to provide the power required by the ducted fan engine. A small part of the power (about 5%) is used to supplement the power of the battery 42 .

实施例二Embodiment 2

参照图1和图2所示,在实施例一的基础上,进一步的,在机身1内部靠近机头的位置设置前轮贮藏舱,在机身1内部靠近机尾的位置对称设置多个后轮贮藏舱,并且在机身1底部的位置分别设置与前轮贮藏舱和后轮贮藏舱相对应的前舱门和后仓门,同时在前轮贮藏舱和后轮贮藏舱中分别设置前起落架16和后起落架17,前起落架16和后起落架17能够在航行器起飞后分别收回前轮贮藏舱和后轮贮藏舱中,并通过前舱门和后仓门封闭在前轮贮藏舱和后轮贮藏舱中,方便航行器在地上滑行起飞的同时,进一步减小了航行器在空中飞行时受到的阻力,可以提高航行器的飞行速度和飞行灵活性,同时在一定程度上也可以起到节省燃料的作用。Referring to FIGS. 1 and 2 , on the basis of Embodiment 1, further, a front wheel storage compartment is arranged inside the fuselage 1 near the nose, and a plurality of storage compartments are symmetrically arranged inside the fuselage 1 near the tail The rear wheel storage compartment, and the front and rear compartment doors corresponding to the front wheel storage compartment and the rear wheel storage compartment are respectively provided at the position of the bottom of the fuselage 1, and are respectively arranged in the front wheel storage compartment and the rear wheel storage compartment. The front landing gear 16 and the rear landing gear 17, the front landing gear 16 and the rear landing gear 17 can be respectively retracted into the front wheel storage compartment and the rear wheel storage compartment after the aircraft takes off, and are closed in the front through the front door and the rear door. The wheel storage compartment and the rear wheel storage compartment are convenient for the aircraft to glide and take off on the ground, and further reduce the resistance of the aircraft when flying in the air, which can improve the flight speed and flight flexibility of the aircraft. It can also save fuel.

显然,上述实施例仅仅是为清楚地说明所作的举例,并非对实施方式的限定。对于所属领域的普通技术人员来说,在上述说明的基础上还可以做出其它不同形式变化或变动。这里无需也无法对所有的实施方式予以穷举。而由此所引伸出的显而易见的变化或变动仍处于本发明创造的保护范围之中。Obviously, the above-mentioned embodiments are only examples for clear description, and are not intended to limit the implementation manner. For those of ordinary skill in the art, other different forms of changes or modifications can also be made on the basis of the above description. There is no need and cannot be exhaustive of all implementations here. And the obvious changes or changes derived from this are still within the protection scope of the present invention.

Claims (10)

1. An oil-electricity hybrid medium-crossing unmanned aircraft with a variable structure is characterized by comprising,
the water supply and drainage device comprises a machine body, a water supply port and a cavity, wherein the machine body is provided with the water supply port and the cavity positioned in the machine body, a first containing cabin, a second containing cabin and a water supply and drainage device are arranged in the cavity, a first expansion device and a second expansion device are respectively arranged in the first containing cabin and the second containing cabin, the water supply and drainage device comprises a water ballast tank, and the water ballast tank is connected with the water supply port;
the wings are foldable wings;
a tail wing;
the power device is arranged in the cavity and comprises a fuel generator set, a storage battery, a first propulsion device and a second propulsion device, the first propulsion device is connected with the fuel generator set, the second propulsion device is connected with the storage battery, and the first propulsion device and the second propulsion device are respectively connected with a first telescopic device and a second telescopic device;
before the aircraft flies, the first containing cabin is opened, and the first telescopic device pushes the first propelling device out of the first containing cabin to provide power for the aircraft during flying; before the aircraft submerges into the water from the air, the first telescopic device drives the first propulsion device to retract into the first containing cabin, the first containing cabin is closed, and meanwhile, the conveying water gap is opened, so that water enters the water ballast tank to assist the aircraft submerge; after the aircraft enters the water, the second containing cabin is opened, and the second telescopic device pushes the second propelling device out of the second containing cabin to provide power for the aircraft during underwater navigation.
2. The hybrid oil-electric medium unmanned aircraft with variable structure according to claim 1, characterized in that: the aircraft wing storage cabin is characterized in that a wing storage cabin used for storing wings is arranged in the cavity, one end, close to the fuselage, of each wing is arranged in the wing storage cabin, and a storage cabin door matched with the wing storage cabin is arranged on the fuselage.
3. The hybrid oil-electric vehicle according to claim 1, characterized in that: the wing includes main wing and aileron, the main wing includes a plurality of pterygoid lamina, and is a plurality of pterygoid lamina swing joint in proper order constitutes the main wing, a pterygoid lamina of fuselage is kept away from to the main wing is as first pterygoid lamina, the aileron sets up on first pterygoid lamina, and removes all be provided with the flap on other each pterygoid lamina outside the first pterygoid lamina.
4. The hybrid oil-electric medium unmanned aircraft with variable structure according to claim 1, characterized in that: the fuselage is including the aircraft nose, the ventral and the tail that connect gradually, carry the water gap set up in on the aircraft nose, the wing connect in on the ventral, the fin install in on the tail.
5. The hybrid oil-electric vehicle according to claim 4, characterized in that: the empennage includes vertical empennage and tailplane, vertical empennage is vertical to be set up on the tail, be provided with first rudder on the vertical empennage, the tailplane level sets up on the tail, tailplane is including the section of turning over that is located the fuselage both sides, it all is provided with the second rudder to turn over on the section, it is used for turning over the direction of motion to the navigation after turning over to vertical direction and controlling to turn over the section.
6. The hybrid oil-electric vehicle according to claim 1, characterized in that: the first storage cabin is provided with an air inlet, the air inlet is connected with the fuel generator set through an air pipe, and a blower device and an electronic valve are arranged in the air pipe.
7. The hybrid oil-electric medium unmanned aircraft with variable structure according to claim 1, characterized in that: the water inlet and outlet device further comprises a pressure device, the pressure device comprises an air compressor and an air storage tank, the air compressor is connected with the air storage tank, and the air storage tank is connected with the ballast water tank.
8. The hybrid oil-electric medium unmanned aircraft with variable structure according to claim 1, characterized in that: the second storage tank is connected with the ballast water tank through a pipeline, and a one-way valve is arranged in the pipeline.
9. The hybrid oil-electric medium unmanned aircraft with variable structure according to claim 1, characterized in that: the aircraft emergency power supply system further comprises an auxiliary device, wherein the auxiliary device comprises an emergency power supply and a signal device, the emergency power supply is used for supplying power in an emergency mode, and the signal device is used for receiving instructions and transmitting state information of the aircraft back.
10. The hybrid oil-electric medium unmanned aircraft with variable structure according to claim 1, characterized in that: the first propulsion device is an electrically-driven ducted fan engine, and the second propulsion device is an electrically-driven ducted propeller water propeller.
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