Three-body triphibian aircraft and triphibian form switching method thereof

Abstract

The invention relates to the technical field of aircrafts, and discloses a triphibian aircraft and a triphibian form switching method thereof. Comprising an aircraft main body, a left auxiliary body and a right auxiliary body, retractable wings are arranged between the aircraft main body and the left auxiliary body and the right auxiliary body, sliding wheel assemblies are arranged at the bottoms of the three bodies respectively, foldable rotor wing mechanisms are arranged at the tops of the left auxiliary body and the right auxiliary body, a propeller is arranged at the tail of the aircraft main body, and foldable small wings are arranged on the outer sides of the left auxiliary body and the right auxiliary body. During take-off, the wings and the winglets are unfolded, the rotor mechanisms are started, and rising is achieved; during air cruise, the sliding wheel assemblies and the rotor mechanisms are stored, the propellers are started, and smooth flight is ensured; when the unmanned aerial vehicle runs on land, the sliding wheel assemblies are opened, the rotor mechanisms are stored, the wings and the winglets are folded, wind resistance is reduced, and the propellers are started to run; when sailing on the water, the three-body structure ensures buoyancy, and the propeller is pushed to move forwards; through the three-body structure, seamless switching of air, land and water triphibian scenes is achieved, the system adapts to multiple environments, the use flexibility is improved, and the application range is widened.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aircraft, and particularly relates to a three-body tri-copter and a tri-copter mode switching method thereof. BACKGROUND

[0002] In the field of modern transportation, a single vehicle in a single environment cannot meet the needs of complex scenarios. Traditional aircraft, such as fixed-wing aircraft and helicopters, can achieve efficient air travel, but they require strict landing sites and have little access to land and water environments. Once they leave the airport and other dedicated facilities, they cannot move flexibly. Land vehicles, such as cars and off-road vehicles, can adapt to most landforms, but they are limited by water and air obstacles and cannot cross natural barriers such as rivers and lakes. They also cannot achieve rapid air transfer. Water vehicles, such as ships and speedboats, can only operate in water and lose all access to land. They also need to rely on other transportation tools for assistance during water transfer, which is inefficient.

[0003] Although some amphibious vehicles have appeared in some fields, such as amphibious vehicles, their functions still have significant limitations. Most amphibious vehicles can only switch between land and water and lack air travel capabilities. Their speed, stability on land, and maneuverability on water are far inferior to those of professional single-vehicle vehicles.

[0004] With the increasing demand for multi-environment transportation tools in emergency rescue, field exploration, and cross-domain logistics, the development of a vehicle that can seamlessly switch between air, land, and water and maintain good performance in each scenario has become a focus in the industry. The functional fragmentation and scenario limitations of traditional vehicles have driven the development of new vehicles with multi-scenario adaptability. The invention of the three-body tri-copter addresses the above issues by innovative structural design and component coordination mechanisms, enabling efficient switching and stable operation in different scenarios and filling the technical gap in cross-domain transportation.

[0005] Therefore, the present application is proposed. SUMMARY

[0006] To solve the above technical problems, the basic idea of the technical solution of the present application is as follows: A three-body tri-copter includes a main body, a left auxiliary body, and a right auxiliary body. The main body is connected to the left and right auxiliary bodies by wings. The left and right auxiliary bodies are symmetrical. The main body, the left auxiliary body, and the right auxiliary body are each provided with a sliding wheel assembly at the bottom. The top of the left and right auxiliary bodies is provided with a rotor mechanism. The tail of the main body is provided with a propeller.

[0007] As a preferred embodiment of the present application, the outer side of the left auxiliary body and the right auxiliary body of the aircraft is respectively provided with a winglet, the winglet is rotationally connected with the left auxiliary body and the right auxiliary body of the aircraft, and the winglet can be folded to a vertically downward state or a horizontal state.

[0008] As a preferred embodiment of the present application, the aircraft body is provided with a manned cabin, and the rear of the aircraft body is provided with a propeller, which is a jet engine or a rocket engine for generating thrust.

[0009] As a preferred embodiment of the present application, the left auxiliary body and the right auxiliary body of the aircraft carry batteries or fuel, and the left auxiliary body and the right auxiliary body are respectively connected to the aircraft body through lines and pipelines in the wings.

[0010] As a preferred embodiment of the present application, the sliding wheel assembly can be respectively accommodated into the aircraft body, the left auxiliary body and the right auxiliary body.

[0011] As a preferred embodiment of the present application, the left auxiliary body and the right auxiliary body of the aircraft are respectively provided with a storage cover, and a lifting mechanism for adjusting the height of the storage cover is arranged between the storage cover and the left auxiliary body and the right auxiliary body; the edge of the storage cover is provided with a storage baffle, and the inside of the storage cover and the storage baffle forms a storage cavity; the rotor mechanism has rotor blades, and the rotor mechanism and the rotor blades can be accommodated in the storage cavity.

[0012] As a preferred embodiment of the present application, the wing includes a main wing and an auxiliary wing, one end of the main wing is installed on the outer wall of the aircraft body, the other end of the main wing is provided with a clamping mechanism, the inside of the main wing is provided with a contraction groove, a driving mechanism for adjusting the auxiliary wing and the clamping mechanism is arranged in the contraction groove, one end of the auxiliary wing is inserted into the contraction groove and connected with the driving mechanism, and the other end of the auxiliary wing is connected with the left auxiliary body and the right auxiliary body of the aircraft.

[0013] A three-body triphibian aircraft triphibian form switching method: When the aircraft is switched to an aerial form, first, the wing is unfolded, the rotor mechanism is started, and the aircraft takes off; when the aircraft reaches a predetermined height, the sliding wheel assembly is accommodated, the rotor mechanism is accommodated, and the propeller is started, so that the aircraft cruises in the air; When the aircraft is switched to a land form, the wing is contracted, the rotor mechanism is accommodated, the sliding wheel assembly is opened, and the propeller is started, so that the aircraft drives on land; When the aircraft is switched to a water form, the sliding wheel assembly is accommodated, the rotor mechanism is accommodated, the wing is unfolded, and the propeller is started, so that the aircraft cruises in water.

[0014] Compared with the prior art, the present application has the following beneficial effects: The present application realizes sea, land and air tri-service through a three-body structure; when taking off, the wings, ailerons are unfolded, the rotor mechanism is started, vertical take-off is realized; when cruising in the air, the sliding wheel assembly is stored, the rotor mechanism is stored, the wings are unfolded, the ailerons are unfolded, the propeller is started, smooth flight is ensured; when driving on land, the sliding wheel assembly is opened, the rotor mechanism is stored, the wings are folded, the ailerons are hung down, wind resistance is reduced, the propeller provides power for efficient driving; when sailing on water, the sliding wheel assembly is stored, the rotor mechanism is stored, the three-body structure ensures buoyancy, the propeller drives forward; therefore, seamless switching among air, land and water scenes can be realized, multiple environments can be adapted, and use flexibility and application range are improved.

[0015] The specific embodiments of the present application will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0016] In the drawings: Figure 1 It is a three-dimensional structure of the present application. The rotor blade opening state schematic diagram; Figure 2 It is a three-dimensional structure of the present application. The rotor blade storage state schematic diagram; Figure 3 It is a three-dimensional structure of the present application. The wing contraction state schematic diagram; Figure 4 It is a detailed schematic diagram of the wing contraction structure of the present application; Figure 5 It is a three-dimensional structure of the present application. The ground state below the lower view schematic diagram.

[0017] In the drawings: 1, aircraft main body; 2, aircraft left auxiliary body; 3, aircraft right auxiliary body; 4, wing; 5, sliding wheel assembly; 6, rotor mechanism; 7, propeller; 8, aileron; 9, storage cover; 10, lifting mechanism; 11, storage baffle; 12, storage cavity; 13, rotor blade; 14, main wing; 15, aileron; 16, clamping mechanism; 17, contraction groove, 18, driving mechanism. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical scheme and advantages of the embodiments of the present application more clear, the technical scheme in the embodiments will be clearly and completely described below with reference to the drawings in the embodiments of the present application. The following embodiments are used to illustrate the present application.

[0019] As Figures 1 to 5As shown, the tripartite tri-copter includes an aircraft main body 1, an aircraft left auxiliary body 2 and an aircraft right auxiliary body 3 are arranged on both sides of the aircraft main body 1 respectively, the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3 are symmetrical to each other, and the aircraft main body 1 is connected with the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3 through wings 4. The bottom of the aircraft main body 1, the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3 is provided with a sliding wheel assembly 5. The top of the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3 is provided with a rotor mechanism 6. The tail of the aircraft main body 1 is provided with a propeller 7.

[0020] Further, the outer side of the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3 is respectively provided with an aileron 8, the aileron 8 is rotatably connected with the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3, and the aileron 8 can be folded to a vertical downward state or a horizontal state.

[0021] Further, the sliding wheel assembly 5 can be stored in the aircraft main body 1, the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3 as in the prior art, or can be released.

[0022] Further, the rotor mechanism 6 has a storage structure. A storage cover 9 is installed above the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3 respectively, a lifting mechanism 10 for adjusting the height of the storage cover 9 is arranged between the storage cover 9 and the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3; the edge of the storage cover 9 is provided with a storage baffle 11, and the inside of the storage cover 9 and the storage baffle 11 forms a storage cavity 12; the rotor mechanism 6 has rotor blades 13, and the rotor mechanism 6 and the rotor blades 13 can be stored in the storage cavity 12.

[0023] Further, the wing 4 has a retractable structure. The wing 4 includes a main wing 14 and an auxiliary wing 15, one end of the main wing 14 is installed on the outer wall of the aircraft main body 1, the other end of the main wing 14 is provided with a clamping mechanism 16, the inside of the main wing 14 is provided with a retraction groove 17, a driving mechanism 18 for adjusting the auxiliary wing 15 and the clamping mechanism 16 is arranged in the retraction groove 17, one end of the auxiliary wing 15 is inserted into the retraction groove 17 and connected with the driving mechanism 18, and the other end of the auxiliary wing 15 is connected with the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3.

[0024] When taking off, the wing 4 is unfolded, the aileron 8 is unfolded, the rotor mechanism 6 is started, and vertical lift is realized; when cruising in the air, the sliding wheel assembly 5 is stored, the rotor mechanism 6 is stored, the wing 4 is unfolded, the aileron 8 is unfolded, and the propeller 7 is started to ensure smooth flight; when driving on land, the sliding wheel assembly 5 is opened, the rotor mechanism 6 is retracted, the wing 4 is retracted, and the aileron 8 is lowered to reduce wind resistance and use the propeller 7 to assist efficient driving; when sailing on water, the sliding wheel assembly 5 is stored, the rotor mechanism 6 is retracted, the tripartite structure ensures buoyancy, and the propeller 7 propels forward; therefore, seamless switching among air, land and water scenes can be realized, multiple environments can be adapted, and use flexibility and application range can be improved.

[0025] In the specific embodiment, the aircraft body 1 is used for carrying people, and the aircraft body 1 is provided with a propeller 7 at the rear, which can be a jet engine for generating thrust. In this arrangement, the installation position of the jet engine is determined.

[0026] In the specific embodiment, the aircraft body 1 is provided with a cabin for carrying people, and the aircraft body 1 is provided with a propeller 7 at the rear, which can be a jet engine, a rocket engine, or other type of thrust generating mechanism for generating thrust.

[0027] In the specific embodiment, the aircraft left body 2 and the aircraft right body 3 are provided with batteries or fuel, and the aircraft left body 2 and the aircraft right body 3 are connected to the aircraft body 1 through lines and pipes in the wings 4.

[0028] The implementation principle of the three-body amphibious aircraft of the present embodiment is as follows: The aircraft is designed as a three-body structure in the present application, the middle aircraft body 1 carries people, and the batteries and fuel are placed in the aircraft left body 2 and the aircraft right body 3, or a large amount of batteries and fuel are placed in the aircraft left body 2 and the aircraft right body 3, while a small amount of batteries and fuel are placed in the middle aircraft body 1, and the aircraft left body 2 and the aircraft right body 3 are connected to the middle aircraft body 1 through lines and pipes in the wings 4 for power supply and oil supply. The advantage of this structure is high safety. If an explosion occurs, it will only affect the two side bodies, and the personnel in the middle body will be relatively safe.

[0029] The present application can be structurally changed to achieve triad.

[0030] When taking off from the ground, the staff can control the wings 4 to be in an unfolded state rather than a folded state, and control the ailerons 8 to gradually turn from a vertical state to a horizontal state; the storage cover 9 is moved upward by the lifting mechanism 10, so that the storage cover 9 no longer covers the rotor mechanism 6 and the rotor blades 13, the rotor blades 13 rotate to generate lift, and vertical take-off is performed.

[0031] When in the air cruising state, the rotor mechanism 6 stops rotating, the storage cover 9 is lowered by the lifting mechanism 10 to store the rotor mechanism 6 and the rotor blades 13, and the sliding wheel assembly 5 is stored in the aircraft body 1, the aircraft left body 2, and the aircraft right body 3 to reduce wind resistance in a streamlined shape, and the propeller 7 is started to ensure smooth air cruising flight.

[0032] When it is needed to travel on land, at this time the staff can open the sliding wheel assembly 5 arranged at the aircraft main body 1, the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3, so that the sliding wheel assembly 5 is in contact with the ground; and the same is true for the rotor mechanism 6; at the same time, the driving mechanism 18 is controlled to open the upper and lower parts of the clamping mechanism 16, and the driving mechanism 18 is controlled to move the aileron 15 into the contraction slot 17 of the main wing 14, when the contraction reaches the limit state, the driving mechanism 18 is controlled to close the upper and lower parts of the clamping mechanism 16 to clamp the aileron 15, and the winglet 8 is in a hanging state; in this way, the shape of the aircraft is more compact, so as to ensure that the wind resistance is reduced during travel, and the aircraft can be pushed to travel on the road surface with the assistance of the propeller 7.

[0033] When it is needed to travel in water, at this time the staff can control the sliding wheel assembly 5 to be respectively stored in the aircraft main body 1, the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3, and at the same time the staff can store the rotor mechanism 6, and at this time the aircraft main body 1, the aircraft left auxiliary body 2 and the aircraft right auxiliary body 3 float on the water surface in a trimaran structure, and can be pushed to travel at high speed on the water surface with the assistance of the propeller 7.

Claims

1. A three-body amphibious aircraft, comprising an aircraft body (1), characterized in that: A left auxiliary body (2) and a right auxiliary body (3) of the aircraft are respectively provided on both sides of the aircraft main body (1); the aircraft main body (1) is connected to the left auxiliary body (2) and the right auxiliary body (3) of the aircraft through wings (4); the left auxiliary body (2) and the right auxiliary body (3) of the aircraft are symmetrical to each other; sliding wheel assemblies (5) are respectively provided at the bottom of the aircraft main body (1), the left auxiliary body (2) and the right auxiliary body (3); rotor mechanisms (6) are provided at the tops of the left auxiliary body (2) and the right auxiliary body (3); and a propeller (7) is provided at the tail of the aircraft main body (1).

2. The three-body amphibious aircraft according to claim 1, characterized in that: Winglets (8) are respectively provided on the outer sides of the left auxiliary body (2) and the right auxiliary body (3) of the aircraft. The winglets (8) are rotatably connected to the left auxiliary body (2) and the right auxiliary body (3) of the aircraft. The winglets (8) can be folded to a vertical downward state or a horizontal state.

3. The three-body amphibious aircraft according to claim 1, characterized in that: A manned cabin is provided in the aircraft body (1), and a propeller (7) is provided at the rear of the aircraft body (1). The propeller (7) is a jet engine or a rocket engine for generating thrust.

4. The three-body amphibious aircraft according to claim 1, characterized in that: Batteries or fuel are carried in the left auxiliary body (2) and the right auxiliary body (3) of the aircraft. The left auxiliary body (2) and the right auxiliary body (3) of the aircraft are connected to the aircraft main body (1) via lines and pipes in the wings (4).

5. The three-body amphibious aircraft according to claim 1, characterized in that: The sliding wheel assembly (5) can be respectively accommodated in the aircraft main body (1), the aircraft left auxiliary body (2) and the aircraft right auxiliary body (3).

6. The three-body amphibious aircraft according to claim 1, characterized in that: A storage cover (9) is installed above the left sub-body (2) and the right sub-body (3) of the aircraft, respectively; a lifting mechanism (10) for adjusting the height of the storage cover (9) is provided between the storage cover (9) and the left sub-body (2) and the right sub-body (3) of the aircraft; a storage baffle (11) is provided at the edge of the storage cover (9); a storage cavity (12) is formed inside the storage cover (9) and the storage baffle (11); the rotor mechanism (6) has rotor blades (13), and the rotor mechanism (6) and the rotor blades (13) can be stored in the storage cavity (12).

7. The three-body amphibious aircraft according to claim 1, characterized in that: The wing (4) comprises a main wing (14) and an aileron (15), one end of the main wing (14) is mounted on the outer wall of the aircraft body (1), the other end of the main wing (14) is provided with a clamping mechanism (16), a contraction groove (17) is provided inside the main wing (14), a driving mechanism (18) for adjusting the aileron (15) and the clamping mechanism (16) is provided in the contraction groove (17), one end of the aileron (15) is inserted into the contraction groove (17) and connected to the driving mechanism (18), and the other end of the aileron (15) is connected to the left aileron (2) and the right aileron (3) of the aircraft.

8. A method for switching the three-body three-amphibious aircraft to a three-amphibious configuration according to claim 1, characterized in that: When the aircraft switches to the air mode, the wings are first unfolded and the rotor mechanism is activated to make the aircraft take off; when the aircraft reaches a predetermined height, the sliding wheel assembly is retracted, the rotor mechanism is retracted, and the propeller is activated to make the aircraft cruise in the air; When the aircraft switches to land mode, the wings are retracted, the rotor mechanism is stored, the sliding wheel assembly is opened, and the propeller is turned on, so that the aircraft can move on land; When the aircraft switches to the underwater form, the sliding wheel assembly is stored, the rotor mechanism is stored, the wings are unfolded, and the propeller is turned on, so that the aircraft cruises in the water.

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