Turbofan amphibious aircraft

Abstract

The invention discloses a turbofan amphibious aircraft, and relates to the technical field of amphibious aircrafts. The experience effect of the airplane is improved. Comprising an aircraft body, a steering assembly and a takeoff and landing assembly, the steering assembly and the takeoff and landing assembly are installed at the bottom of the aircraft body, the aircraft body comprises an aircraft body, a cockpit and an aircraft head part, the aircraft head part is integrally formed at one end of the aircraft body, the cockpit is integrally formed at the top of the aircraft body, a water rudder is installed at the tail of the aircraft body, and straight wings are fixed to the top of the cockpit; and a V-shaped empennage is mounted at the tail of the aircraft body. According to the invention, the turbofan engine is adopted as power, so that the problems of propeller beating and propeller collision between water or objects and people on the water and the aircraft caused by a traditional propeller are avoided, people can move around the aircraft in a close range, meanwhile, noise is reduced, a parallel double-row control function is adopted in a cockpit, and the functions of entertainment flight and driver training are met; and a global satellite communication system and a small-sized air anti-collision early warning system are arranged.

Description

Technical Field

[0001] The present invention relates to the technical field of amphibious aircraft, and in particular to a turbofan amphibious aircraft. Background Art

[0002] In the prior art, an amphibious aircraft refers to an aircraft that can take off, land and park on the water surface. It can adapt to two different environments, on water and in the air. It is suitable for tasks such as maritime patrol, anti-submarine, rescue and forest fire fighting. It has good maneuverability and flexibility, and is suitable for complex industrial control on the water surface and on the ground, demonstrating its adaptability and application potential in extreme environments. Most of the amphibious aircraft on the market are powered by electricity. There is a lack of low-noise turbofan amphibious aircraft that can be used for water takeoff, water entertainment, and land takeoff. Most of the aircraft that have been certified, operated, and delivered are two-seaters. Due to the electric drive, this type of aircraft has a small passenger capacity, high noise, and poor comfort. At the same time, the fuselage and pontoons of traditional amphibious aircraft are made of metal aluminum alloy or carbon fiber and glass fiber composite materials, which are not corrosion-resistant and have a short structural life; Based on this, the present application proposes a turbofan amphibious aircraft, which can achieve long life, low noise, large space, and has the functions of both a yacht and an aircraft. Summary of the invention

[0003] The purpose of the present invention is to solve the shortcomings of the prior art and to propose a turbofan amphibious aircraft.

[0004] In order to achieve the above object, the present invention adopts the following technical solutions: A turbofan amphibious aircraft comprises an aircraft body and a steering assembly and a landing assembly installed at the bottom of the aircraft body, the aircraft body comprises a fuselage, a cockpit and a nose, the nose is integrally formed at one end of the fuselage, the cockpit is integrally formed at the top of the fuselage, a water rudder is installed at the tail of the fuselage, a straight wing is fixed on the top of the cockpit, a V-shaped tail is installed at the tail of the fuselage, a turbofan engine is installed at the rear of the fuselage through a bracket, and floating platforms are fixed on both sides of the fuselage.

[0005] Preferably: the landing assembly includes a mounting frame and a double-headed motor, the mounting frame is fixed to the bottom inner wall of the aircraft body, and the double-headed motor is fixed to the top outer wall of the mounting frame, the output end of the double-headed motor is connected to a lead screw through a coupling, a guide rod is fixed to the top inner wall of the mounting frame, and a drive plate is movably connected to the outer wall of the guide rod, and a landing wheel mechanism is installed at the bottom of the drive plate.

[0006] Furthermore: a connecting plate is welded at the bottom of the driving plate, and a plug-in rod is fixed to the inner wall of the through hole opened on the surface of the connecting plate by embedding, and a support plate is movably connected to the circumferential outer wall of the plug-in rod, and a deceleration cover is welded at the bottom of the support plate, and a torsion spring is clamped between the outer wall of the plug-in rod and the side wall of the support plate.

[0007] Furthermore: the lifting and lowering wheel mechanism includes a hollow rod, a wheel, a bracket and a rotating shaft, the hollow rod is welded to the outer wall of the bottom of the driving plate, and the bracket is welded to the bottom of the hollow rod, the rotating shaft is movably connected to the inner walls of the through holes opened on both sides of the bracket, and the wheel and the outer wall of the rotating shaft are fixedly connected.

[0008] As a preferred solution of the present invention: the through hole opened in the top of the mounting frame is movably connected with a deceleration rod, and a lifting plate is welded on the top of the deceleration rod, a deceleration plate is fixed on the bottom of the deceleration rod, the output end two of the double-headed motor is connected with lead screw two through a coupling, and a friction disk used in conjunction with the deceleration plate is fixed on the circumferential outer wall of the rotating shaft.

[0009] As a further solution of the present invention: a magnetic-insulating plate is fixed to the inner wall of the bottom of the deceleration cover body, and a permanent magnet is movably connected to the through hole opened on the surface of the magnetic-insulating plate, and a spring is clamped between one end of the permanent magnet and the magnetic-insulating plate, a side plate is welded to one end of the permanent magnet, and a resistance plate is welded between the two side plates.

[0010] As a further solution of the present invention: a mounting plate is welded to the inner wall of the bottom of the deceleration cover, and an electromagnet used in conjunction with the permanent magnet is fixed to the outer wall of one side of the mounting plate by screws.

[0011] On the basis of the above scheme: the steering assembly includes an electric telescopic rod and a frame, the electric telescopic rod is fixed to the inner wall of the bottom of the body, and the electric telescopic rod is fixed to the outer wall of the top of the frame, and an intermediate block is fixed to the output end of the electric telescopic rod.

[0012] On the basis of the above-mentioned solution: a steering motor is fixed on the top of the intermediate block, and the output end of the steering motor is connected to a steering wheel through a coupling.

[0013] On the basis of the above-mentioned solution: a double-headed motor 2 is fixed inside the middle block, and a sealing plate is fixed at the output end of the double-headed motor 2.

[0014] The beneficial effects of the present invention are: A turbofan amphibious aircraft adopts a turbofan engine as a power source to avoid the problem of propellers hitting or colliding with water or objects on the water, people and the aircraft caused by traditional propellers. People can move around the aircraft at close range, while reducing noise.

[0015] A turbofan amphibious aircraft with a parallel double-row cockpit control function to meet the needs of recreational flying and pilot training; it is equipped with a global satellite communication system and a small air collision avoidance warning system to improve flight safety in mountainous areas and waterways.

[0016] A turbofan amphibious aircraft is provided with a floating platform for water entertainment. The aircraft stops on the water surface for fishing, floating and emergency rescue.

[0017] A turbofan amphibious aircraft, in view of different scenarios of the aircraft body landing on the water surface or on the ground, a deceleration cover body, a drag plate and other structures are arranged to decelerate the aircraft body when landing on the water surface; when the aircraft body needs to land on the ground, the deceleration cover body is unfolded so that the wheels installed inside it can contact the ground to realize the landing of the aircraft body on the ground.

[0018] A turbofan amphibious aircraft, which uses an electric telescopic rod to drive a steering wheel to move downward so that the steering wheel extends out from the bottom of the aircraft body, and then uses a steering motor to drive the steering wheel to rotate to achieve the steering of the aircraft body, and uses a sealing plate to seal between the steering wheel and the aircraft body to prevent water from entering the interior of the aircraft body when the aircraft body lands on the water. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the overall structure of a turbofan amphibious aircraft proposed by the present invention; Figure 2 It is a schematic diagram of the bottom structure of a turbofan amphibious aircraft proposed by the present invention; Figure 3 It is a schematic diagram of the internal structure of a turbofan amphibious aircraft proposed by the present invention; Figure 4 It is a schematic diagram of the structure of a landing assembly of a turbofan amphibious aircraft proposed by the present invention; Figure 5 It is a schematic diagram of the partial structure of a landing assembly of a turbofan amphibious aircraft proposed by the present invention; Figure 6 It is a schematic diagram of the exploded structure of a landing assembly of a turbofan amphibious aircraft proposed by the present invention; Figure 7 It is a schematic diagram of the installation structure of a deceleration mechanism of a turbofan amphibious aircraft proposed by the present invention; Figure 8 It is a schematic diagram of the deceleration cover structure of a turbofan amphibious aircraft proposed by the present invention; Fig. 9 It is a schematic diagram of the main structure of a deceleration mechanism of a turbofan amphibious aircraft proposed by the present invention; Fig.10 It is a schematic structural diagram of a steering assembly of a turbofan amphibious aircraft proposed by the present invention; Fig.11 It is a schematic diagram of a control system of a turbofan amphibious aircraft proposed by the present invention.

[0020] In the figure: fuselage 1; cockpit 2; bracket 3; V-shaped tail 4; floating platform 5; turbofan engine 6; straight wing 7; nose 8; deceleration rod 9; mounting frame 10; deceleration cover 11; lead screw 12; double-headed motor 1 13; lead screw 2 14; lifting plate 15; drive plate 16; guide rod 17; hollow rod 18; wheel 19; mounting plate 20; bracket 21; rotating shaft 22; friction plate 23; deceleration plate 24; resistance plate 25; torsion spring 26; plug-in rod 27; supporting plate 28; connecting plate 29; electromagnet 30; spring 31; magnetic insulation plate 32; permanent magnet 33; lateral plate 34; electric telescopic rod 35; steering motor 36; frame 37; middle block 38; steering wheel 39; sealing plate 40; double-headed motor 2 41; water rudder 42. DETAILED DESCRIPTION

[0021] The technical solution of this patent is further described in detail below in conjunction with specific implementation methods.

[0022] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention. Example 1

[0023] A turbofan amphibious aircraft, such as Figures 1 to 11 As shown, it includes an aircraft body and a steering assembly 100 and a landing assembly 200 installed at the bottom of the aircraft body. The landing assembly 200 includes a mounting frame 10 and a double-headed motor 13. The mounting frame 10 is fixed to the inner wall of the bottom of the aircraft body by bolts, and the double-headed motor 13 is fixed to the outer wall of the top of the mounting frame 10 by bolts. The output end of the double-headed motor 13 is connected to a lead screw 12 through a coupling. The inner wall of the top of the mounting frame 10 is fixed to a guide rod 17 by bolts, and the outer wall of the guide rod 17 is fixed to the inner wall of the top of the mounting frame 10 by bolts. A driving plate 16 is slidably connected, and the driving plate 16 and the lead screw 12 are connected by a nut 1, a lifting wheel mechanism is installed at the bottom of the driving plate 16, a connecting plate 29 is welded at the bottom of the driving plate 16, and a plug-in rod 27 is fixed to the inner wall of the through hole opened on the surface of the connecting plate 29 by embedding, and a support plate 28 is rotatably connected to the outer wall of the circumference of the plug-in rod 27, and a deceleration cover 11 is welded to the bottom of the support plate 28, and a torsion spring 26 is clamped between the outer wall of the plug-in rod 27 and the side wall of the support plate 28; When the aircraft body lands on the water, after the aircraft body contacts the water surface, the double-headed motor 13 is used to drive the lead screw 12 to rotate so that the driving plate 16 moves downward along the vertical direction under the guidance of the guide rod 17, and the connecting plate 29 drives the deceleration cover 11 to move downward along the bottom of the aircraft body for a certain distance. After the deceleration cover 11 protrudes from the bottom of the aircraft body, the water body generates resistance to the deceleration cover 11, so that the aircraft body uses the deceleration cover 11 to decelerate after landing on the water surface, thereby reducing the landing time of the aircraft body on the water surface; When the aircraft body needs to land on the ground, when the double-headed motor 13 is used to drive the screw 12 to rotate, the distance that the deceleration cover 11 moves along the bottom of the aircraft body is increased. When the conical arc surface area on the top of the deceleration cover 11 moves to separate from the bottom of the aircraft body, the deceleration cover 11 rotates a certain angle along the insertion rod 27 under the action of the rebound force of the torsion spring 26. During this process, the two deceleration covers 11 are unfolded to both sides, so that the take-off and landing wheel mechanism located at the bottom of the driving plate 16 is exposed to the outside, and the take-off and landing wheel mechanism is used to allow the aircraft body to land on the ground.

[0024] Further, the aircraft body includes a fuselage 1, a cockpit 2 and a nose 8, the nose 8 is integrally formed at one end of the fuselage 1, and the cockpit 2 is integrally formed at the top of the fuselage 1, and a water rudder 42 is installed at the tail of the fuselage 1, a straight wing 7 is fixed on the top of the cockpit 2, and a V-shaped tail 4 is installed at the tail of the fuselage 1, a turbofan engine 6 is installed at the rear of the fuselage 1 through a bracket 3, and floating platforms 5 are fixed on both sides of the fuselage 1, and the aircraft body 1 is provided with a control panel, an elevator, a rudder and a flap, and the control panel is used to control it; The fuselage 1 can be used to accommodate and install the steering assembly 100 and the landing assembly 200. The cockpit 2 is used for passengers to sit and drive. In this embodiment, the layout of the cockpit 2 is preferably a double-row five-seat layout. The entire aircraft body can be made of aluminum alloy or basalt composite frame, long stringer and skin. The skin can be made of basalt fiber to reduce weight while enhancing the load-bearing capacity of the fuselage. The use of a turbofan engine 6 as a power source avoids the problem of traditional propellers causing water or objects on the water, people and aircraft to hit or bump the propellers. When the turbofan engine is working, it first Air intake and diversion, air is inhaled through the large fan at the front end, and the inhaled air is divided into two airflows after the fan: the inner airflow and the outer airflow. The inner airflow enters the compressor and is further compressed. The compressed air enters the combustion chamber, mixes with the fuel and burns to produce high-temperature and high-pressure combustion gas. The high-temperature and high-pressure combustion gas enters the turbine part, first drives the high-pressure turbine to rotate, and the high-pressure turbine drives the compressor to rotate through the shaft connection. The combustion gas continues to flow through the low-pressure turbine, driving the low-pressure turbine to rotate. The low-pressure turbine drives the fan to rotate through the shaft connection, and finally the combustion gas is discharged from the tail nozzle at high speed, producing The ducted airflow is the air after the fan that is directly discharged into the atmosphere through the ducted airflow or discharged from the nozzle together with the internal combustion gas. This part of the airflow is compressed by the fan, the pressure is increased, and it expands and accelerates in the tail nozzle, and flows out of the nozzle at a certain speed, thus also generating thrust. The turbofan engine 6 allows people to move around the aircraft at a close distance, while reducing noise. The cockpit 2 adopts a parallel double-row control function to meet the functions of entertainment flight and driver training. The water rudder 42 can be used to control the movement route of the entire aircraft. It is equipped with a global satellite communication system and a small The air collision avoidance warning system improves flight safety in mountainous areas and waterways. The straight wing 7 is connected to the cockpit 2 through the central wing box. The main structure can be composed of front and rear beams connecting the fuselage frame. The wing ribs can be made of high-strength aviation foam and carbon fiber plates. The skin and beams are formed by basalt fiber pultrusion. The V-shaped tail 4 can be made of similar structural forms and materials, and the two are made as a whole. The flight control system adopts a steel cable system, the cockpit includes a joystick and pedals, and the left and right floating platforms 5 provide the media needed for water entertainment. The aircraft can be parked on the water for fishing, floating and emergency rescue.

[0025] Furthermore, the lifting and lowering wheel mechanism includes a hollow rod 18, a wheel 19, a bracket 21 and a rotating shaft 22, wherein the hollow rod 18 is welded to the outer wall of the bottom of the driving plate 16, and the bracket 21 is welded to the bottom of the hollow rod 18, and the rotating shaft 22 is rotatably connected to the inner wall of the through hole opened on both sides of the bracket 21, and the wheel 19 and the outer wall of the rotating shaft 22 are fixedly connected; After the aircraft body lands on the ground, the wheels 19 are used to slide the aircraft body on the ground.

[0026] Furthermore, the through hole opened at the top of the mounting frame 10 is slidably connected with a deceleration rod 9, and a lifting plate 15 is welded on the top of the deceleration rod 9, and a deceleration plate 24 is fixed at the bottom of the deceleration rod 9, and the output end 2 of the double-headed motor 13 is connected with a lead screw 2 14 through a coupling, and the lead screw 2 14 and the lifting plate 15 are connected through a nut 2, and a friction disc 23 used in conjunction with the deceleration plate 24 is fixed on the circumferential outer wall of the rotating shaft 22; When the double-headed motor 13 drives the lead screw 2 14 to rotate, the reduction rod 9 and the reduction plate 24 move downward in the vertical direction under the guidance of the mounting frame 10. The thread pitches of the lead screw 12 and the lead screw 2 14 are different, so that there is a difference between the speed at which the lead screw 12 drives the wheel 19 to move downward and the speed at which the lead screw 2 14 drives the reduction plate 24 to move downward. The speed difference between the two is utilized so that when the reduction plate 24 moves to contact the surface of the friction disk 23, it acts as a brake to decelerate the friction disk 23, thereby accelerating the braking rate of the aircraft body on the ground.

[0027] Further, a magnetic-insulating plate 32 is fixed to the inner wall of the bottom of the deceleration cover 11 by bolts, and a permanent magnet 33 is slidably connected to a through hole opened on the surface of the magnetic-insulating plate 32, and a spring 31 is clamped between one end of the permanent magnet 33 and the magnetic-insulating plate 32, a lateral plate 34 is welded to one end of the permanent magnet 33, and a resistance plate 25 is welded between the two lateral plates 34, a mounting plate 20 is welded to the inner wall of the bottom of the deceleration cover 11, and an electromagnet 30 used in conjunction with the permanent magnet 33 is fixed to the outer wall of one side of the mounting plate 20 by screws; When the aircraft body needs to land on the water, in order to further improve the deceleration effect on the aircraft body, the electromagnet 30 and the permanent magnet 33 repel each other when energized, so that the resistance plate 25 moves a certain distance outward along the deceleration cover 11 under the action of the repulsive force. When the resistance plate 25 protrudes out of the deceleration cover 11, the resistance plate 25 is used to increase the contact area with the water body, thereby improving the deceleration effect. When the electromagnet 30 is powered off, the rebound force of the spring 31 is used to reset the resistance plate 25.

[0028] Further, the steering assembly 100 includes an electric telescopic rod 35 and a frame 37, the electric telescopic rod 35 is fixed to the bottom inner wall of the body 1 by bolts, and the electric telescopic rod 35 is fixed to the top outer wall of the frame 37 by bolts, the output end of the electric telescopic rod 35 is fixed with an intermediate block 38 by bolts, and the top of the intermediate block 38 is fixed with a steering motor 36, and the output end of the steering motor 36 is connected to a steering wheel 39 through a coupling; When the aircraft body needs to turn after landing on the ground, the electric telescopic rod 35 is used to drive the steering wheel 39 to move downward, so that the steering wheel 39 extends from the bottom of the body 1, and the steering motor 36 is used to drive the steering wheel 39 to rotate to realize the steering of the aircraft body.

[0029] Furthermore, a second double-headed motor 41 is fixed inside the middle block 38, and a sealing plate 40 is fixed to the output end of the second double-headed motor 41; When the aircraft body lands on the water, the sealing plate 40 is used to seal the steering wheel 39 and the fuselage 1 to prevent water from entering the fuselage 1. When the aircraft body needs to land on the ground, the electric telescopic rod 35 drives the steering wheel 39 to extend from the bottom of the fuselage 1, and the double-headed motor 41 is used to drive the sealing plate 40 to rotate so that the sealing plate 40 is detached from the bottom of the steering wheel 39, so that the steering wheel 39 is in contact with the ground.

[0030] When the present embodiment is in use, when the aircraft body needs to land on the water, the double-headed motor 13 is used to drive the lead screw 12 to rotate so that the two groups of deceleration covers 11 move a certain distance along the bottom of the body 1 under the guidance of the guide rod 17, but ensure that the two deceleration covers 11 are in a closed state. When the deceleration cover 11 extends from the bottom of the body 1, the electromagnet 30 is energized, and the repulsive force between the electromagnet 30 and the permanent magnet 33 is used to make the resistance plate 25 move a certain distance outward along the deceleration cover 11, and the deceleration cover 11 and the resistance plate 25 play a role in decelerating the aircraft body. When the main body of the aircraft needs to land on the ground, the moving distance of the two groups of deceleration covers 11 is adjusted so that when the top of the deceleration cover 11 is detached from the bottom of the body 1, the two groups of deceleration cover 11 are expanded outward by utilizing the resilience of the torsion spring 26. After the two groups of deceleration cover 11 are expanded, the wheels 19 are in contact with the ground. At the same time, the electric telescopic rod 35 is used to drive the steering wheel 39 to move downward. When the sealing plate 40 is detached from the bottom of the body 1, the double-headed motor 41 is used to drive the sealing plate 40 to flip over, so that the steering wheel 39 is in contact with the ground. The steering wheel 39 and the wheel 19 are used to facilitate the landing of the main body of the aircraft on the ground.

[0031] The above is a preferred specific implementation manner of the present invention, and the protection scope of the present invention is not limited thereto. Any modification, equivalent substitution and improvement made by any technician familiar with the field within the technical scope disclosed by the present invention in combination with the prior art or public common sense, within the spirit and principle of the present invention, shall be covered by the protection scope of the present invention.

Claims

1. A turbofan amphibious aircraft, comprising an aircraft body and a steering assembly (100) and a landing assembly (200) mounted on the bottom of the aircraft body, characterized in that: The aircraft body comprises a fuselage (1), a cockpit (2) and a nose (8), the nose (8) being integrally formed at one end of the fuselage (1), the cockpit (2) being integrally formed at the top of the fuselage (1), a water rudder (42) being installed at the tail of the fuselage (1), a straight wing (7) being fixed at the top of the cockpit (2), a V-shaped tail (4) being installed at the tail of the fuselage (1), a turbofan engine (6) being installed at the rear of the fuselage (1) via a bracket (3), and floating platforms (5) being fixed on both sides of the fuselage (1).

2. The turbofan amphibious aircraft according to claim 1, characterized in that: The landing assembly (200) comprises a mounting frame (10) and a double-headed motor (13); the mounting frame (10) is fixed to the bottom inner wall of the aircraft body, and the double-headed motor (13) is fixed to the top outer wall of the mounting frame (10); an output end (1) of the double-headed motor (13) is connected to a lead screw (12) via a coupling; a guide rod (17) is fixed to the top inner wall of the mounting frame (10), and a drive plate (16) is movably connected to the outer wall of the guide rod (17); a landing wheel mechanism is installed at the bottom of the drive plate (16).

3. The turbofan amphibious aircraft according to claim 2, characterized in that: A connecting plate (29) is welded to the bottom of the driving plate (16), and a plug-in rod (27) is fixed to the inner wall of a through hole formed on the surface of the connecting plate (29) by embedding, and a support plate (28) is movably connected to the circumferential outer wall of the plug-in rod (27), and a deceleration cover (11) is welded to the bottom of the support plate (28), and a torsion spring (26) is clamped between the outer wall of the plug-in rod (27) and the side wall of the support plate (28).

4. The turbofan amphibious aircraft according to claim 3, characterized in that: The lifting and lowering wheel mechanism comprises a hollow rod (18), a wheel (19), a bracket (21) and a rotating shaft (22); the hollow rod (18) is welded to the outer wall of the bottom of the driving plate (16), and the bracket (21) is welded to the bottom of the hollow rod (18); the rotating shaft (22) is movably connected to the inner walls of through holes opened on both sides of the bracket (21), and the wheel (19) and the outer wall of the rotating shaft (22) are fixedly connected.

5. The turbofan amphibious aircraft according to claim 4, characterized in that: A through hole opened at the top of the mounting frame (10) is movably connected to a deceleration rod (9), and a lifting plate (15) is welded to the top of the deceleration rod (9), and a deceleration plate (24) is fixed to the bottom of the deceleration rod (9), and the output end 2 of the double-headed motor 1 (13) is connected to the lead screw 2 (14) via a coupling, and a friction disc (23) used in conjunction with the deceleration plate (24) is fixed to the circumferential outer wall of the rotating shaft (22).

6. The turbofan amphibious aircraft according to claim 5, characterized in that: A magnetic-isolating plate (32) is fixed to the inner wall of the bottom of the deceleration cover (11), and a permanent magnet (33) is movably connected to a through hole provided on the surface of the magnetic-isolating plate (32), and a spring (31) is clamped between one end of the permanent magnet (33) and the magnetic-isolating plate (32), a lateral plate (34) is welded to one end of the permanent magnet (33), and a resistance plate (25) is welded between the two lateral plates (34).

7. The turbofan amphibious aircraft according to claim 6, characterized in that: A mounting plate (20) is welded to the inner wall of the bottom of the deceleration cover (11), and an electromagnet (30) used in conjunction with a permanent magnet (33) is fixed to an outer wall of one side of the mounting plate (20) by means of screws.

8. The turbofan amphibious aircraft according to claim 7, characterized in that: The steering assembly (100) comprises an electric telescopic rod (35) and a frame (37); the electric telescopic rod (35) is fixed to the bottom inner wall of the body (1), and the electric telescopic rod (35) is fixed to the top outer wall of the frame (37); an intermediate block (38) is fixed to the output end of the electric telescopic rod (35).

9. The turbofan amphibious aircraft according to claim 8, characterized in that: A steering motor (36) is fixed on the top of the middle block (38), and an output end of the steering motor (36) is connected to a steering wheel (39) via a coupling.

10. The turbofan amphibious aircraft according to claim 9, characterized in that: A second double-headed motor (41) is fixed inside the middle block (38), and a sealing plate (40) is fixed to the output end of the second double-headed motor (41).

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