Small multi-mode compound control ground effect aircraft and control method thereof

Abstract

The invention belongs to the field of ground effect aircrafts, and particularly provides a small multi-mode compound control ground effect aircraft which comprises a fuselage main body, a lifting main wing is arranged on the fuselage main body, two tiltable duct engines are arranged on the front portion of the lifting main wing, and two buoys are fixedly connected to the two sides of the lifting main wing respectively. The tail parts of the buoys are connected with vertical tails, and the parts, capable of deflecting leftwards and rightwards, of the rear parts of the vertical tails form rudders; the horizontal empennage is supported at the top of the vertical fin; the vertically deflectable part at the rear part of the horizontal empennage forms an elevator; a tail propeller is arranged at the joint of the vertical tail and the horizontal tail; and a sweepback lift winglet is arranged from the middle part to the tail part of the buoy. The invention further provides a control method for the small multi-mode compound control ground effect vehicle. The control method is used for controlling the ground effect vehicle in the water surface taxiing stage, the takeoff stage and the flight stage. The ground effect aircraft provided by the invention can take off and land quickly through compound control; and the overall structure is simple.

Description

Technical Field

[0001] The invention relates to a ground effect vehicle, in particular to a small multi-modal composite control ground effect vehicle and a control method thereof. Background Art

[0002] In the related technology, a ground effect vehicle is a kind of transportation tool that flies over the ground or sea and is developed by utilizing the principle of aerodynamic ground effect. When a vehicle with spread wings flies close to the ground or water, the air flow is constrained by the ground or water surface, resulting in an increase in the lift-to-drag ratio and a decrease in induced drag. The closer the effect is to the ground, the stronger the ground effect, the greater the lift obtained by the vehicle, and the greater the weight that can be carried.

[0003] At present, the relatively independent structure of the wing and fuselage of traditional ground effect vehicles leads to complex structural connections and low lift efficiency; moreover, the single propulsion mode cannot take into account both water resistance and aerodynamic requirements, resulting in low propulsion efficiency in the transition stage from water surface to air. Summary of the invention

[0004] The purpose of the embodiments of the present invention is to provide a small multi-modal composite control ground effect vehicle and a control method thereof, aiming to solve the technical problem that the lift efficiency of traditional ground effect vehicles is low, resulting in low propulsion efficiency in the transition stage from the water surface to the air.

[0005] To achieve the above object, the present invention provides the following technical solutions.

[0006] An embodiment of the present invention provides a small multi-mode composite control ground effect vehicle, the ground effect vehicle comprising: The fuselage body is provided with a main lift wing, and two tiltable ducted engines are arranged at the front of the main lift wing; The two buoys are fixedly connected to the two sides of the lift main wing, and the tail of each buoy is connected to a vertical tail, and the rear part of the vertical tail that can be deflected left and right forms a rudder; The horizontal tail is supported on the top of the vertical tail, and the rear part of the horizontal tail that can be deflected up and down forms the elevator; Among them, a tail propeller is provided at the connection between the vertical tail and the horizontal tail; The float has a swept lift winglet from the middle to the tail.

[0007] As a further limitation of the preferred embodiment of the present invention, the horizontal tail is entirely located above the tail of the lift main wing.

[0008] As a further limitation of the preferred embodiment of the present invention, the two tiltable ducted engines are symmetrically located on both sides of the head of the fuselage body.

[0009] As a further limitation of the preferred embodiment of the present invention, a detachable module is provided on the fuselage body.

[0010] As a further limitation of the preferred embodiment of the present invention, the lift winglet has a dihedral angle of 20 degrees to improve aerodynamic efficiency.

[0011] As a further limitation of the preferred embodiment of the present invention, the two tail propellers are respectively arranged at the connection between the two vertical tails and the horizontal tail.

[0012] Another embodiment of the present invention provides a control method, which includes the following steps: In the water planing state, the rudder deflection on the two vertical tails and the differential of the tail propeller jointly generate the yaw moment; During takeoff, the front tiltable ducted engine tilts upward, so that the airflow generated by the propeller of the tiltable ducted engine enters the space between the bottom of the lift main wing and the water surface, generating air cushion lift; the tail propeller works together to move forward, generating a nose-down moment, so that the buoy leaves the water surface as quickly as possible; the elevator on the horizontal tail controls the pitch balance of the aircraft; the flight direction of the aircraft is controlled by the differential between the rudder of the vertical tail and the tail propeller; During the flight phase, the front tiltable ducted engine resumes its forward position and is placed at a cruising angle according to the flight status; the tail propeller and the propeller of the tiltable ducted engine jointly generate flight power; the elevator on the horizontal tail controls the pitch, and the rudder on the vertical tail controls the direction; lift wings are installed on the outer sides of the pontoons on both sides, which can generate the lift-increasing effect of the wingtip winglets, and at the same time reduce the roll of the fuselage when the rudder is yawed.

[0013] Compared with the prior art, the small multi-mode composite control ground effect vehicle and the control method thereof of the present invention have the following beneficial effects: First, when in the water, the tail of the lift main wing slightly sinks into the water, and the lower part of the lift main wing and the buoy form a closed space, which is convenient for the generation of ground effect. At the same time, the rudder surface of the vertical tail sinks into the water to form a water rudder for steering, which is convenient for steering. Second, when gliding on the water, only the steps of the buoys are in contact with the water surface, and the main wing is completely out of the water. Third, in the ground effect flight state, the aircraft is completely separated from the water surface, and the flight altitude and direction are controlled by the elevator and rudder.

[0014] In summary, the ground effect vehicle provided by the present invention has two sets of power at the head and tail, and can take off and land quickly through compound control; the lift main wing, fuselage body and buoy of the present invention are an integral whole, with a simple structure and high efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present invention.

[0016] Figure 1 A three-dimensional structural diagram of a small multi-mode composite control ground effect vehicle of the present invention; Figure 2 A front view of the small multi-mode compound control ground effect vehicle provided by the present invention; Figure 3 A top view of the small multi-mode compound control ground effect vehicle provided by the present invention; Figure 4 A side view of the small multi-modal compound-controlled ground effect vehicle provided by the present invention.

[0017] The figure numbers are as follows: 1. Fuselage body; 2. Removable module; 3. Float; 4. Tilt ducted engine; 5. Horizontal tail; 6. Lift winglet; 7. Vertical tail; 8. Tail propeller; 9. Lift main wing. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0019] The specific implementation of the present invention is described in detail below in conjunction with specific embodiments.

[0020] Please refer to Figure 1-Figure 4 In one embodiment of the present invention, a small multi-mode compound control ground effect vehicle is provided, the ground effect vehicle comprises a fuselage body 1, the fuselage body 1 has a lift main wing 9, and the front part of the lift main wing 9 is provided with two tiltable ducted engines 4; Among them, two tiltable ducted engines 4 are symmetrically located on both sides of the head of the fuselage body 1; In addition, a detachable module 2 is provided on the fuselage body 1, and the detachable module 2 is a replaceable structure with a universal interface, and a manned manned module or an unmanned cargo module can be installed on the fuselage body 1 as needed. By replacing the detachable module, the application mode of the ground effect vehicle of the present invention can be changed, and its flexibility and adaptability can be effectively improved.

[0021] Further, in an embodiment of the present invention, the ground effect vehicle provided by the embodiment of the present disclosure further includes two buoys 3, and the two buoys 3 are respectively fixedly connected and arranged on both sides of the lift main wing 9; the tail of each buoy 3 is connected and arranged with a vertical tail 7, so that the ground effect vehicle provided by the embodiment of the present disclosure forms a double vertical tail structure; Among them, the part of the rear part of the vertical tail 7 that can be deflected left and right forms a rudder, which can be used to control the direction of the ground effect vehicle when it moves.

[0022] Preferably, the main lift wing 9, the fuselage body 1 and the pontoon 3 provided by the present invention are an integral structure formed in one piece, and the overall structure is compact, simple and highly efficient.

[0023] In one implementation of the present invention, the top support of the vertical tail 7 is provided with a horizontal tail 5, and the horizontal tail 5 is located above the tail of the lift main wing 9 as a whole; wherein the rear part of the horizontal tail 5 that can be deflected up and down forms an elevator.

[0024] Furthermore, the embodiment of the present disclosure provides a swept lift winglet 6 from the middle to the tail of the buoy 3, and the lift winglet 6 has a dihedral angle of 20 degrees to improve aerodynamic efficiency.

[0025] Furthermore, in the embodiment of the present invention, a tail propeller 8 is provided at the connection between the vertical tail 7 and the horizontal tail 5; Preferably, the two tail propellers 8 are respectively arranged at the connection between the two vertical tails 7 and the horizontal tail 5. In a specific implementation, the ground effect vehicle can be assisted to turn based on the differential principle of the two tail propellers 8. Therefore, the present invention is installed at the connection between the vertical tail 7 and the horizontal tail 5 through the tail propeller 8. This layout enables the tail propeller 8 to provide thrust and generate steering torque through the differential principle when the ground effect vehicle needs to turn. For example, when it is necessary to turn left or right, the control system of the aircraft will adjust the speed or thrust of the left and right tail propellers 8 so that the thrust of one propeller is greater than that of the other. The thrust difference will generate a steering torque, thereby driving the aircraft to turn.

[0026] In combination with the above structure, the ground effect vehicle provided by the present invention is divided into three flight states: When the ground effect vehicle is in the water, the tail of the lift main wing 9 slightly sinks into the water, and the lower part of the lift main wing 9 and the buoy 3 form a closed space, which is convenient for the generation of ground effect. At the same time, part of the rudder surface of the vertical tail 7 sinks into the water to form a water rudder for steering (i.e., a rudder for steering the ground effect vehicle); When the ground effect vehicle is in a gliding state on the water surface, only the step of the buoy 3 is in contact with the water surface, and the lift main wing 9 is completely out of the water surface; When a ground effect vehicle is in ground effect flight state, the vehicle is completely separated from the water surface, and the flight altitude and direction are controlled by the elevator and rudder.

[0027] In one implementation, the step of the pontoon 3 provided in the embodiment of the present invention is arranged in the middle or front middle of the pontoon 3 to reduce the contact area with the water surface during takeoff, thereby reducing resistance.

[0028] Further, in another embodiment of the present invention, a control method for the small multi-mode compound control ground effect vehicle of the above-mentioned embodiment is provided, and the control method comprises the following steps: When the vehicle is gliding on the water, the rudder deflection on the two vertical tails 7 and the differential motion of the tail propeller 8 jointly generate a yaw moment; During the take-off phase, the front tiltable ducted engine 4 tilts upward, so that the airflow generated by the propeller of the tiltable ducted engine 4 enters the space between the bottom of the lift main wing 9 and the water surface, generating air cushion lift; the tail propeller 8 moves forward together to generate a nose-down moment, so that the buoy 3 leaves the water surface as quickly as possible; the elevator on the horizontal tail 5 controls the pitch balance of the aircraft; the flight direction of the aircraft is controlled by the differential between the rudder of the vertical tail 7 and the tail propeller 8; During the flight phase, the front tiltable ducted engine 4 resumes forward movement and is placed at a cruising angle according to the flight state; the tail propeller 8 and the propeller of the tiltable ducted engine 4 jointly generate flight power; the elevator on the horizontal tail 5 controls the pitch, and the rudder of the vertical tail 7 controls the direction; the outer sides of the buoys 3 are equipped with lift winglets 6, which can generate the lift-increasing effect of the wingtip winglets and at the same time reduce the roll of the fuselage when the rudder is yawed.

[0029] It can be seen that the ground effect vehicle provided by the present invention has two sets of power at the head and tail, and can take off and land quickly through compound control; In addition, the lift main wing, fuselage body and buoy of the present invention are integrated into one body, and the structure is simple and efficient.

[0030] The above solutions are only an illustration of a preferred example, but are not limited thereto. When implementing the present invention, appropriate replacement and / or modification can be performed according to user needs.

[0031] The number of devices and processing scales described here are used to simplify the description of the present invention. Applications, modifications and variations of the present invention will be obvious to those skilled in the art.

[0032] Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the specification and the embodiments. It can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional modifications can be easily realized. Therefore, without departing from the general concept defined by the claims and equivalent scope, the present invention is not limited to the specific details and the illustrations shown and described here.

Claims

1. A small multi-mode composite control ground effect vehicle, characterized in that: include: A fuselage body (1), the fuselage body (1) having a main lift wing (9), and two tiltable ducted engines (4) are arranged at the front of the main lift wing (9); A buoy (3), wherein the middle to the tail of the buoy (3) is provided with a swept lift winglet (6); two buoys (3) are respectively fixedly connected to the two sides of the lift main wing (9), and the tail of each buoy (3) is connected to a vertical tail (7), and the rear part of the vertical tail (7) that can be deflected left and right forms a rudder; A horizontal tail (5) is supported and arranged on the top of a vertical tail (7), and a portion of the rear of the horizontal tail (5) that can be deflected up and down forms an elevator; a tail propeller (8) is arranged at the connection between the vertical tail (7) and the horizontal tail (5).

2. A small multi-mode compound controlled ground effect vehicle according to claim 1, characterized in that: The horizontal tail wing (5) is located as a whole above the tail of the lift main wing (9).

3. A small multi-mode compound controlled ground effect vehicle according to claim 2, characterized in that: Two tiltable ducted engines (4) are symmetrically located on both sides of the head of the fuselage body (1).

4. A small multi-mode compound controlled ground effect vehicle according to claim 3, characterized in that: A detachable module (2) is provided on the fuselage body (1).

5. A small multi-mode compound controlled ground effect vehicle according to claim 4, characterized in that: The lift winglet (6) has an anhedral angle of 20 degrees.

6. A small multi-mode compound controlled ground effect vehicle according to claim 5, characterized in that: The two tail propellers (8) are respectively arranged at the connection between the two vertical tails (7) and the horizontal tail (5).

7. A control method for a small multi-mode compound controlled ground effect vehicle as claimed in any one of claims 1 to 6, characterized in that: The control method comprises the following steps: In the gliding state on the water surface, the yaw moment is generated by the deflection of the rudders on the two vertical tails (7) and the differential of the tail propeller (8); During the take-off phase, the front tiltable ducted engine (4) tilts upward, and the airflow generated by the propeller of the tiltable ducted engine (4) enters the space between the bottom of the lift main wing (9) and the water surface, generating air cushion lift; the tail propeller (8) moves forward together to generate a nose-down moment, which is used to make the buoy (3) leave the water surface; the elevator on the horizontal tail (5) controls the pitch balance of the aircraft; and the flight direction of the aircraft is controlled by the differential between the rudder of the vertical tail (7) and the tail propeller (8); During the flight phase, the front tiltable ducted engine (4) is restored to the forward direction and is placed at a cruising angle according to the flight state; the tail propeller (8) and the propeller of the tiltable ducted engine (4) jointly generate flight power; the elevator on the horizontal tail (5) controls the pitch, and the rudder on the vertical tail (7) controls the direction; the lift winglet (6) is used to generate the lift increase of the wingtip winglet.

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