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

Abstract

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.

Description

A Variable-Structure Hydroelectric Hybrid Trans-medium Unmanned Vehicle

technical field

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.

Background technique

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.

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.

SUMMARY OF THE INVENTION

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.

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:

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;

a wing, the wing is a foldable wing;

tail;

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;

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 .

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.

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.

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.

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.

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.

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.

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.

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.

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.

The above-mentioned technical scheme of the present invention has the following advantages compared with the prior art:

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.

Description of drawings

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

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;

Fig. 2 is a side view of the oil-electric hybrid trans-medium unmanned vehicle with variable structure shown in Fig. 1;

FIG. 3 is a top view of the oil-electric hybrid trans-medium unmanned vehicle with variable structure shown in FIG. 1;

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;

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 .

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.

Detailed ways

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.

Example 1

1-4, a variable-structure oil-electric hybrid trans-medium unmanned vehicle of the present invention includes,

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;

Wing 2, wing 2 is a foldable wing;

tail 3;

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;

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.

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.

It is conceivable that the first telescopic device may be a small telescopic device such as an air cylinder or an electric push rod.

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.

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.

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.

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.

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.

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.

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 .

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.

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.

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.

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 .

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 .

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.

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.

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.

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.

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.

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.

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 .

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.

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.

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 .

Embodiment 2

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.

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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