Distributed electric propulsion box type wing ground effect aircraft

Abstract

The invention discloses a distributed electric propulsion box type wing ground effect aircraft which comprises a main fuselage, the two sides of the main fuselage are connected with one ends of sweepback wing main wings, one ends of two empennages above the tail of the main fuselage are connected with the main fuselage through vertical tails, and the other ends of the two empennages are connected with the other ends of the two main wings through end plates respectively. The empennage is connected with a plurality of high ducted fans directly driven by a motor, an elevator and an aileron are arranged at the rear part of the empennage, a rudder is arranged at the rear part of the vertical fin, and the elevator, the aileron and the rudder are controlled by a flight control system and are mutually independent. The ground-effect aircraft provided by the invention adopts a box-type wing structure formed by combining the sweepback main wing and the sweepforward empennage, has better aerodynamic performance in a take-off and climbing low-speed flight state, and can provide larger lift force and better maneuvering characteristics.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft design, and in particular relates to a distributed electric propulsion box-type wing ground effect aircraft. Background Art

[0002] Ground effect vehicles are a product that combines the advantages of many transportation tools such as general land-based aircraft, seaplanes and high-performance ships. With the development of social economy and changes in military needs, it is becoming more and more valued by people and is considered to be one of the ideal high-speed surface transportation tools. Ground effect vehicles use the ground / water surface effect to significantly improve the lift-to-drag ratio of the aircraft. The flight speed is several to dozens times that of ordinary ships, and the effective load coefficient is 25%-50% higher than that of ordinary aircraft. Therefore, ground effect vehicles have broad application prospects.

[0003] In order to meet the transportation efficiency and highlight the advantages of efficient transportation, the body design of ground effect vehicles is usually bulky, resulting in reduced cruising maneuverability; ground effect vehicles are usually not equipped with special water rudders, and the efficiency of air rudders is low when sailing at low speed on the water surface, and there is a problem of large turning radius on the water surface. Existing ground effect vehicles generally have poor maneuverability and are difficult to avoid obstacles in time when cruising on water / air, which greatly restricts their use scenarios.

[0004] In order to highlight the advantages of ground effect vehicles in marine environmental monitoring, maritime rescue, resource exploration and other applications, they must have the ability to take off / land quickly and cruise efficiently in complex sea conditions. However, the impact of waves on aircraft is particularly significant, and the need for ground effect vehicles to resist waves restricts the further development of their equipment. In order to increase the height of the propeller above the water and avoid the problem of propeller touching the water, existing ground effect vehicles usually adopt an upper wing configuration or place the propeller above the fuselage, but the increase in the height of the propeller above the water is limited. Summary of the invention

[0005] Purpose of the Invention

[0006] Aiming at the shortcomings of poor maneuverability and wave resistance of existing ground effect vehicles, the present invention provides a distributed electric propulsion box-wing ground effect vehicle, which can improve the maneuverability and wave resistance of the ground effect vehicle.

[0007] Inventing technical solutions

[0008] A distributed electric propulsion box-type wing ground effect vehicle comprises a main body, one end of a swept wing main wing is connected to the two sides of the main body, one end of two tail wings above the tail of the main body is connected to the main body through a vertical tail, and the other end is respectively connected to the other end of the two main wings through end plates, a plurality of high-mounted ducted fans directly driven by a motor are connected to the tail wing, an elevator and an aileron are arranged at the rear of the tail wing, and a rudder is arranged at the rear of the vertical tail, the elevator, aileron and rudder are controlled by a flight control system, and the elevator, aileron and rudder are independent of each other.

[0009] Preferably, the main body includes an upper body and a lower body, and the lower body adopts a V-shaped hull.

[0010] Preferably, the main fuselage extends along the span direction of the main wing.

[0011] Preferably, the main fuselage and the main wing have a smooth transition.

[0012] Preferably, the junction between the front and rear parts of the lower hull has a straight step structure.

[0013] Preferably, buoys are provided below both ends of the main wing.

[0014] Preferably, the tail wing adopts a large aspect ratio forward-swept wing type.

[0015] Preferably, the two tail wings extend from the longitudinal section of the fuselage to both sides.

[0016] Preferably, the rudder extends vertically from below the tail wing.

[0017] Preferably, the ducted fans are suspended below the tail at equal intervals along the span direction of the tail.

[0018] The invention has the following advantages: the ground effect vehicle provided by the invention adopts a box-type wing configuration composed of a swept-back main wing and a swept-forward tail wing, has better aerodynamic performance in take-off and climbing low-speed flight states, can provide greater lift and better maneuverability; the box-type structure ensures the overall structural strength of the fuselage and the wing, and has a strong anti-stall capability. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 A schematic diagram of a distributed electric propulsion box-wing ground effect vehicle provided in an embodiment of the present invention.

[0020] Figure 2 A front view of a distributed electric propulsion box-wing ground effect vehicle provided in an embodiment of the present invention.

[0021] Figure 3 A top view of a distributed electric propulsion box-wing ground effect vehicle provided in an embodiment of the present invention.

[0022] Figure 4 A side view of a distributed electric propulsion box-wing ground effect vehicle provided in an embodiment of the present invention.

[0023] Figure 5 A three-dimensional diagram of a frame-mounted ducted fan configuration provided in an embodiment of the present invention.

[0024] In the figure: 1. main fuselage; 1-1. upper fuselage; 1-2. lower hull; 1-3. straight step; 2. main wing; 3. tail wing; 3-1. elevator; 3-2. aileron; 4. vertical tail; 4-1. rudder; 5. box structure; 5-1. end plate; 5-2. buoy; 6. distributed thruster; 6-1. ducted fan. DETAILED DESCRIPTION

[0025] The present invention is achieved through the following technical solutions.

[0026] like Figure 1 to Figure 5 A distributed electric propulsion box-type wing ground effect vehicle comprises a main body 1 consisting of an upper body 1-1 and a lower body 1-2, a box-type structure formed by connecting a forward-swept tail wing 3, a swept-back main wing 2 and an end plate 5-1, a distributed propulsion system consisting of a high-mounted ducted fan 6-1 directly driven by 8 groups of motors (not shown in the figure), an elevator 3-1, an aileron 3-2 and a rudder 4-1.

[0027] The main fuselage 1 and the main wing 2 have a smooth transition, and the overall structure is a streamlined design, which can improve the aerodynamic effect of the aircraft; the main fuselage 1 extends along the wingspan direction of the main wing 2, and the internal space of the fuselage is increased, which can improve the loading capacity of the aircraft; the aircraft configuration increases the surface area of ​​the fuselage and wings, which can effectively enhance the ground / water effect of the aircraft, thereby improving the load-bearing capacity.

[0028] The lower hull 1-2 has a straight step 1-3 structure, which plays a role in air-water separation and reducing water resistance during gliding and take-off stages on the water surface; the lower hull 1-2 adopts a V-shaped hull to improve the wave resistance of the aircraft and reduce the impact load during the water surface landing stage.

[0029] The buoys 5-2 are distributed below the two ends of the main wing 2 to provide a restoring moment for the aircraft in a heeling state.

[0030] The tail 3 adopts a large aspect ratio forward-swept wing type, and the left and right tail wings extend from the longitudinal section of the fuselage to both sides, making full use of the wingspan space, and are connected to the tail of the fuselage by the vertical tail 4 to play a supporting role; there is an integrated connection between the tail 3 and the main wing 2 by the vertical end plate 5-1, thereby forming a box-type structure to enhance the load-bearing capacity and strength of the rear wing.

[0031] The elevator 3-1 and the aileron 3-2 are located behind the tail 3; the rudder 4-1 is located behind the vertical tail 4; the rudder 4-1 extends vertically from the bottom of the tail 3, greatly increasing the effective control surface of the rudder and improving the maneuverability of the aircraft.

[0032] The elevator 3-1, aileron 3-2 and rudder 4-1 are controlled by the flight control system and move independently of each other; the yaw moment is provided by deflecting the rudder 4-1 to realize the bow turning movement of the aircraft in the air; the pitch moment is provided by deflecting the elevator 3-1 to realize the bow lifting control of the aircraft during take-off and climbing stages, and the pitching movement during cruising; the rolling movement of the aircraft is realized by providing a rolling moment by reversely deflecting the two ailerons 3-2.

[0033] The distributed electric propulsion system comprises 8 groups of ducted fans 6-1 and motors (not shown in the figure), with four groups on each side of the fuselage, and suspended below the tail 3 at equal intervals along the wingspan direction of the tail 3. The motors (not shown in the figure) are independent and directly drive the ducted fans 6-1 to work; each group of ducted fans 6-1 and the motor (not shown in the figure) move independently without interfering with each other, which is convenient for maintenance, repair and replacement of the propulsion system.

[0034] The flight control system distributes power to the motors (not shown) according to different working scenarios. The propulsion system has redundant power, which improves the safety performance of the aircraft. The flight control system implements differential control of the distributed motors to increase the aircraft's bow torque, reduce the turning radius on the water and in the air, and improve the aircraft's maneuverability.

[0035] In order to avoid corrosion or damage to the blades caused by the blades touching or hitting the water, the propellers of conventional ground effect vehicles are usually located above the fuselage, and the height of the blades above the water is limited by the fuselage. The distributed propeller 6 described in the ground effect vehicle of the present invention is placed high below the tail 3, which greatly increases the height of the propeller above the water, which is beneficial to improving the wave resistance of the ground effect vehicle; the ducted fan 6-1 and the ducted structure have a certain protective effect on the blades, further improving the reliability of the propeller.

[0036] The working principle of the ground effect vehicle of the present invention is as follows (taking off from the water surface as an example):

[0037] Floating on the water surface: Figure 4 As shown, when the local effect aircraft is floating on the water surface, the lower hull 1-2 is in contact with the water surface, and the buoyancy is provided by the wetted volume of the lower hull 1-2; when the aircraft is tilted, the float 5-2 is in contact with the water surface to provide a restoring torque.

[0038] Surface navigation: The distributed thrusters 6 provide longitudinal thrust for the aircraft, and the flight control system controls the motor on / off and the rotation speed, thereby achieving speed control; at low speeds, the rudder 4-1 is less efficient, and by controlling the thrust difference between the thrusters on the left and right sides of the fuselage, a bow turning moment is provided for the aircraft to achieve heading control and enhance the maneuverability of the ground effect vehicle; when gliding at high speed, the large wingspan tail 3 can provide partial lift for the aircraft, and under the combined effect of the hydrodynamic lift of the lower hull 1-2, the fuselage wetted area is reduced, thereby reducing the hydrodynamic resistance.

[0039] Surface takeoff process: on the basis of surface navigation, the longitudinal thrust generated by the distributed propeller 6 is increased by increasing the motor speed to increase the navigation speed; as the speed increases, the forward-swept tail wing 3 and the lower hull 1-2 hydrodynamic lift mainly provide lift for the aircraft, and gradually fly away from the water surface; the elevator 3-1 provides a pitch moment to achieve the control of the take-off heading angle; in the above process, the proportion of lift provided by the swept-wing main wing 2 gradually increases; under the joint lifting action of the tail wing 3, the lower hull 1-2 hydrodynamic lift, and the main wing 2, the aircraft realizes the take-off process.

[0040] Cruising process: When the aircraft is cruising in the ground effect area, there is power redundancy, and the motor speed can be reduced or some motors can be turned off; pitch movement is achieved by deflecting the elevator 3-1, rolling movement is achieved by reverse deflection of the two ailerons 3-2, and bow turning movement is achieved by the rudder 4-1, the thrust difference of the propeller or a combination of methods to perform obstacle avoidance maneuvers.

[0041] Landing process: shut down some motors or reduce motor speed to reduce aircraft speed, control water attitude by deflecting elevator 3-1, make lower hull 1-2 gradually contact with water surface, and then glide to land on water surface; redundant motors can be used to reverse ducted fans and achieve short-distance emergency stop of aircraft.

[0042] The ground effect vehicle provided by the present invention adopts a distributed electric propulsion system, in which four motors on the left and right sides of the fuselage directly drive the ducted fans to work. Compared with the oil engine, the lightweight of the motor helps to realize the high placement of the propeller under the rear wing; the dispersion of power improves the flow field around the aircraft, improves the aerodynamic performance, and the electric propulsion system effectively reduces the noise level; compared with the traditional ground effect vehicle propulsion system, the distributed system increases the capacity of the system and improves the safety performance of the aircraft through redundant power; the distributed ducted fans are coordinated with the rudder for operation, which effectively improves the performance of the aircraft such as surface maneuvering and air cruising, and the electric propulsion system helps to achieve more precise power control and improve flight stability.

[0043] The main fuselage structure has a smooth transition with the main wing along the wingspan direction, and has good aerodynamic performance, which is beneficial to reducing energy consumption during the cruise phase; the aircraft has a compact structure, which can effectively utilize space, increase payload, and improve transportation efficiency.

[0044] The box-type structure greatly increases the height of the propeller above the water, effectively avoiding water contact and water hitting, which is beneficial to improving the wave resistance performance of the ground effect vehicle.

[0045] The protection scope of the present invention is not limited to the above-mentioned embodiments. Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the scope of the present invention. If these changes and modifications fall within the scope of the claims of the present invention and their equivalents, the present invention is intended to include these changes and modifications.

Claims

1. A distributed electric propulsion box-wing ground effect vehicle, characterized in that: The invention comprises a main body (1), wherein both sides of the main body (1) are connected to one end of a swept wing main wing (2), one end of two tail wings (3) above the tail of the main body (1) is connected to the main body (1) through a vertical tail (4), and the other end is connected to the other end of the two main wings (2) through an end plate (5-1), the tail wing (3) is connected to a plurality of high-mounted ducted fans (6-1) directly driven by a motor, an elevator (3-1) and an aileron (3-2) are arranged at the rear of the tail wing (3), and a rudder (4-1) is arranged at the rear of the vertical tail (4), wherein the elevator (3-1), aileron (3-2) and rudder (4-1) are controlled by a flight control system, and the elevator (3-1), aileron (3-2) and rudder (4-1) are independent of each other.

2. A distributed electric propulsion box-wing ground effect vehicle as claimed in claim 1, characterized in that: The main body (1) comprises an upper body (1-1) and a lower body (1-2), and the lower body (1-2) adopts a V-shaped hull.

3. A distributed electric propulsion box-wing ground effect vehicle as claimed in claim 1, characterized in that: The main fuselage (1) extends along the wingspan direction of the main wing (2).

4. A distributed electric propulsion box-wing ground effect vehicle as claimed in claim 3, characterized in that: The main body (1) and the main wing (2) are smoothly transitioned.

5. A distributed electric propulsion box-wing ground effect vehicle as claimed in claim 2, characterized in that: The junction between the front and rear parts of the lower hull (1-2) has a straight step (1-3) structure.

6. A distributed electric propulsion box-wing ground effect vehicle as claimed in claim 1, characterized in that: Floats (5-2) are arranged below both ends of the main wing (2).

7. A distributed electric propulsion box-wing ground effect vehicle as claimed in claim 1, characterized in that: The tail wing (3) adopts a large aspect ratio forward swept wing type.

8. A distributed electric propulsion box-wing ground effect vehicle as claimed in claim 1, characterized in that: Two tail wings extend from the longitudinal section of the fuselage to both sides.

9. A distributed electric propulsion box-wing ground effect vehicle as claimed in claim 1, characterized in that: The rudder (4-1) extends vertically from below the tail wing (3).

10. A distributed electric propulsion box-wing ground effect vehicle as claimed in claim 1, characterized in that: The ducted fans (6-1) are suspended below the tail wing (3) at equal intervals along the wingspan direction of the tail wing (3).

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