A variant of a distributed ground effect vehicle

Abstract

A variant of the distributed ground effect vehicle (GEV) belongs to the field of aerodynamic layout design technology for GEVs. It solves the problems of limited application environments and low efficiency in existing GEV technologies. Key technical features include: wings mounted on both sides of the fuselage, and a tail fin at the rear; the wings consist of a front wing and a rear wing. The front wing is movably mounted on both sides of the front of the fuselage, rotating around its leading edge axis along the wingspan. An engine is mounted on the front wing, with a ducted fan at the engine's output end. A front aileron is located at the rear end of the front wing. The rear wing is mounted on both sides of the mid-rear section of the fuselage, with a rear outer wing connected to its tail end. Flaps are located at the rear end of the rear wing, and a rear aileron is located at the rear end of the rear outer wing. A float is located at the connection between the rear wing and the rear outer wing. This invention can provide greater payload and lift-to-drag ratio. The extended rear outer wing can act as an additional stabilizing surface and winglet, increasing the stability and maneuverability of the GEV.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic layout design technology for ground effect vehicles, specifically a variant of a distributed ground effect vehicle. Background Technology

[0002] Existing technologies for ground effect vehicles (GEVs) have certain drawbacks: they are limited by their application environment. Within a half-wingspan flight altitude, the closer to the ground, the higher the efficiency of the ground effect. Conversely, when leaving the ground effect area or encountering severe sea conditions, GEVs are difficult to take off and fly, significantly reducing the advantages of the ground effect. At low altitudes, they are easily affected by airflow, wake turbulence, and obstacles. At high speeds, their obstacle avoidance and maneuverability are poor, and they are prone to loss of control when turning or climbing too much. The aerodynamic characteristics within the ground effect area are highly nonlinear, changing abruptly with altitude, speed, and attitude. This requires a high-precision flight control system and experienced personnel to operate, resulting in high structural design difficulty, high R&D costs, and high human resource consumption.

[0003] Therefore, there is an urgent need to propose a variant of the distributed ground effect vehicle to solve the problems of large application environment limitations and low efficiency of existing ground effect vehicles. Summary of the Invention

[0004] In view of the above facts, in order to solve the problems of large application environment limitations and low efficiency of ground effect vehicles in the prior art, the present invention designs a variant distributed ground effect vehicle.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A variant of a distributed ground effect vehicle, comprising a fuselage, wings, and a tail.

[0007] The fuselage is equipped with wings on both sides and a tail fin at the rear.

[0008] The wing includes a front wing and a rear wing. The front wing is movably mounted on both sides of the front part of the fuselage. The front wing rotates around the leading edge axis along the wingspan direction. An engine is mounted on the front wing, and a ducted fan is mounted at the output end of the engine. A front aileron is mounted at the rear end of the front wing. The rear wing is mounted on both sides of the middle and rear part of the fuselage. A rear outer wing is connected to the tail end of the rear wing. A flap is mounted at the rear end of the rear wing, and a rear aileron is mounted at the rear end of the rear outer wing.

[0009] A float is provided at the connection between the rear wing and the rear outer wing;

[0010] The fuselage is connected to the frame of the rear wing via a configuration conversion assembly. The frame of the rear wing and the frame of the rear outer wing are connected by gears, which are connected by connectors.

[0011] The configuration conversion assembly includes two conversion mechanisms arranged opposite to each other. Each conversion mechanism includes a hydraulic cylinder, a support frame, a sleeve, a mounting frame, and an arc-shaped limiting bracket. The support frame and the mounting frame are both fixed to the fuselage. The sleeve is arranged opposite to each other on the inner side of the mounting frame. The gear rod of the rear wing is hinged to the sleeve. The hydraulic cylinder is arranged opposite to each other on the inner side of the support frame. The gear rod of the rear wing is hinged to the drive end of the hydraulic cylinder. The arc-shaped limiting bracket is fixed on the inner side of the mounting frame to limit the angle between the rear wing and the fuselage.

[0012] Furthermore: the tail fin includes a horizontal tail fin and a vertical tail fin;

[0013] The vertical tail is mounted vertically on the rear of the fuselage, and a rudder is provided at the rear end of the vertical tail. The horizontal tail is mounted on the vertical tail, and a tail endplate is vertically connected to the rear end of the horizontal tail. An elevator is provided at the rear end of the horizontal tail.

[0014] Furthermore, the wingspan of the front wing is shorter than that of the rear wing.

[0015] Furthermore: the engine is a distributed electric ducted motor.

[0016] The beneficial effects of this invention are as follows:

[0017] 1. This invention improves the lift of the front wing by using ducted fan jets, and changes the jet angle of the ducted fan by tilting the front wing around the leading edge axis to change the azimuth angle. This injects high-speed airflow into the lift-enhancing ground effect air cushion composed of the fuselage, rear wing, flaps, floats and water surface, and utilizes the ground effect to achieve effective lift enhancement and drag reduction, as well as rapid and stable short-distance takeoff and landing.

[0018] 2. This invention can increase the effective wing surface area by changing the dihedral angles of the rear wing and the rear outer wing, thereby enabling long-distance rapid transport.

[0019] 3. This invention can provide greater payload and lift-to-drag ratio. The extended rear wing can serve as an additional stabilizing surface and winglet, increasing the stability and maneuverability of the ground effect vehicle.

[0020] 4. The modified ground effect vehicle's wings are fully extended, allowing it to detach from the ground effect and fly in the air. It can still maintain mission efficiency even when facing severe sea conditions, effectively expanding the mission envelope of the ground effect vehicle.

[0021] 5. The ducted fan power layout in this invention can effectively reduce the impact of wave splashing on the propulsion system and improve the flight safety of the ground effect vehicle. Attached Figure Description

[0022] Figure 1 This is an isometric view of the present invention;

[0023] Figure 2 This is the front view of the present invention;

[0024] Figure 3 This is a diagram showing the positional relationship between the ducted fan and the engine in this invention;

[0025] Figure 4 This is a diagram showing the positional relationship between the ducted fan and the front wing in this invention;

[0026] Figure 5 This is a diagram showing the positional relationship between the frame of the rear wing, the frame of the rear outer wing, and the configuration conversion assembly in this invention.

[0027] Figure 6 This is a schematic diagram of a variant of the present invention.

[0028] In the diagram: 1-fuselage, 2-ducted fan, 3-forward wing, 4-engine, 5-forward aileron, 6-rear wing, 7-rear outer wing, 8-rear aileron, 9-flaps, 10-float, 11-horizontal tail, 12-elevator, 13-tail endplate, 14-vertical tail, 15-rudder, 17-hydraulic cylinder, 18-support frame, 19-sleeve, 20-mounting bracket, 21-arc-shaped limit bracket, 24-gear. Detailed Implementation

[0029] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present application.

[0030] The terms "set up," "connect," and "fix" should be interpreted broadly. For example, "connection" can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection, a direct connection, or an indirect connection through an intermediate medium, or an internal connection between two devices, components, or parts. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0031] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.

[0032] Preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0033] Example 1: Reference Figure 1-5This embodiment describes a variant of a distributed ground effect vehicle, including a fuselage 1, wings, and a tail.

[0034] The fuselage 1 has wings installed on both sides and a tail fin installed at the rear of the fuselage 1.

[0035] The wing includes a front wing 3 and a rear wing 6. The front wing 3 is movably mounted on both sides of the front part of the fuselage 1. The motor is located inside the fuselage 1. The output shafts on both sides of the motor are connected to the front wing 3, driving the front wing 3 to rotate around the leading edge axis along the wingspan direction to change the azimuth angle. An engine 4 is mounted on the front wing 3. A ducted fan 2 is mounted at the output end of the engine 4. A front aileron 5 is mounted at the rear end of the front wing 3. The rear wing 6 is mounted on both sides of the middle and rear part of the fuselage 1. A rear outer wing 7 is connected to the tail end of the rear wing 6. A flap 9 is mounted at the rear end of the rear outer wing 6. A rear aileron 8 is mounted at the rear end of the rear outer wing 7.

[0036] A float 10 is provided at the connection between the rear wing 6 and the rear outer wing 7;

[0037] The fuselage 1 is connected to the frame of the rear wing 6 via a configuration conversion assembly. The frame of the rear wing 6 and the frame of the rear outer wing 7 are connected by gear 24. The gear 24 is connected by a connector.

[0038] The configuration conversion assembly includes two conversion mechanisms arranged opposite to each other. Each conversion mechanism includes a hydraulic cylinder 17, a support frame 18, a sleeve 19, a mounting frame 20, and an arc-shaped limiting bracket 21. The support frame 18 and the mounting frame 20 are both fixed to the fuselage 1. The sleeve 19 is arranged opposite to the inner side of the mounting frame 20. The gear rod of the rear wing 6 is hinged to the sleeve 19 and can rotate around the axis of the sleeve 19. The hydraulic cylinder 17 is arranged opposite to the inner side of the support frame 18. The gear rod of the rear wing 6 is hinged to the drive end of the hydraulic cylinder 17. The hydraulic cylinder 17 provides the power to rotate around the axis. The arc-shaped limiting bracket 21 is fixed inside the mounting frame 20 to limit the angle between the rear wing 6 and the fuselage 1 and control the termination position of the rotation.

[0039] More specifically: the tail fin includes a horizontal tail fin 11 and a vertical tail fin 14;

[0040] The vertical tail 14 is vertically mounted on the tail of the fuselage 1. A rudder 15 is provided at the rear end of the vertical tail 14. The horizontal tail 11 is mounted on the vertical tail 14. A tail end plate 13 is vertically connected to the tail end of the horizontal tail 11. An elevator 12 is provided at the rear end of the horizontal tail 11.

[0041] More specifically: the wingspan of the forewing 3 is less than the wingspan of the rear wing 6.

[0042] More specifically: the engine 4 is a distributed electric ducted motor.

[0043] More specifically: Reference Figure 6 When encountering severe sea conditions, the ground effect is greatly reduced. At this time, the engine 4 drives the ground effect vehicle to begin configuration conversion. The dihedral angles of the rear wing 6 and the rear outer wing 7 turn to 0 degrees, the wing area increases, the aspect ratio increases, and the lift increases. At the same time, the ducted fan 2 rotates with the front wing 3 around the leading edge axis to the installation angle of 0 degrees. The jet of the ducted fan 2 blows towards the rear wing 6 to generate a power lift effect. The ground effect vehicle leaves the ground effect influence area and completes the conversion to cruise flight state.

[0044] More specifically: the lateral structural strength of the rear wing 6 is provided by the rear wing ribs and the front and rear walls of the rear wing, and the longitudinal structural spars of the rear wing 6 are the gear rods of the rear wing;

[0045] The lateral structural strength of the rear outer wing 7 is provided by the rear outer wing rib and the front and rear walls of the rear outer wing, and the longitudinal structural spar of the rear outer wing 7 is the gear rod of the rear outer wing.

[0046] More specifically: the flap 9 further enhances the lift-increasing and drag-reducing effect of the ground effect air cushion.

[0047] More specifically: The ground effect vehicle increases the lift of the front wing 3 by jetting air through the ducted fan 2, and changes the jetting angle of the ducted fan 2 by tilting the front wing 3 around the leading edge axis. This injects high-speed airflow into the lift-enhancing ground effect air cushion formed by the fuselage 1, rear wing 6, flaps 9, floats 10 and the water surface. By utilizing the ground effect, it achieves effective lift enhancement and drag reduction, as well as rapid and stable short-distance takeoff and landing.

[0048] Based on this, the ground effect vehicle can increase the effective wing area by changing the upward / downward dihedral angles of the rear wing 6 and the rear outer wing 7, thereby achieving the function of long-distance rapid transportation.

[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein; as long as there is no structural conflict, the various features in the specific embodiments disclosed in this application can be combined with each other in any way, and will not cause the substance of the corresponding technical solutions to deviate from the scope of the technical solutions of the present invention.

[0050] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A variant of a distributed ground effect vehicle, characterized in that, Includes fuselage (1), wings, and tail; The fuselage (1) has wings installed on both sides and a tail fin installed at the rear. The wing includes a front wing (3) and a rear wing (6). The front wing (3) is movably mounted on both sides of the front part of the fuselage (1). The front wing (3) rotates around the leading edge axis along the wingspan direction. An engine (4) is mounted on the front wing (3). A ducted fan (2) is mounted at the output end of the engine (4). A front aileron (5) is mounted at the rear end of the front wing (3). The rear wing (6) is mounted on both sides of the middle and rear part of the fuselage (1). A rear outer wing (7) is connected to the tail end of the rear wing (6). A flap (9) is mounted at the rear end of the rear outer wing (7). A rear aileron (8) is mounted at the rear end of the rear outer wing (7). A float (10) is provided at the connection between the rear wing (6) and the rear outer wing (7); The fuselage (1) is connected to the frame of the rear wing (6) through a configuration conversion assembly. The frame of the rear wing (6) and the frame of the rear outer wing (7) are meshed by a gear (24). The gear (24) is connected by a connector. The configuration conversion assembly includes two conversion mechanisms arranged opposite to each other. Each conversion mechanism includes a hydraulic cylinder (17), a support frame (18), a sleeve (19), a mounting frame (20), and an arc-shaped limiting bracket (21). The support frame (18) and the mounting frame (20) are both fixed on the fuselage (1). The sleeve (19) is arranged opposite to the inner side of the mounting frame (20). The gear rod of the rear wing (6) is hinged to the sleeve (19). The hydraulic cylinder (17) is arranged opposite to the inner side of the support frame (18). The gear rod of the rear wing (6) is hinged to the driving end of the hydraulic cylinder (17). The arc-shaped limiting bracket (21) is fixed inside the mounting frame (20) to limit the angle between the rear wing (6) and the fuselage (1).

2. A variant distributed ground effect vehicle according to claim 1, characterized in that, The tail fin includes a horizontal tail fin (11) and a vertical tail fin (14). The vertical tail (14) is vertically mounted on the tail of the fuselage (1). A rudder (15) is provided at the rear end of the vertical tail (14). The horizontal tail (11) is mounted on the vertical tail (14). A tail end plate (13) is vertically connected to the tail end of the horizontal tail (11). An elevator (12) is provided at the rear end of the horizontal tail (11).

3. A variant distributed ground effect vehicle according to claim 2, characterized in that, The wingspan of the front wing (3) is less than that of the rear wing (6).

4. A variant distributed ground effect vehicle according to claim 1, characterized in that, The engine (4) is a distributed electric ducted engine.

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