A vertical take-off and landing multi-purpose ground effect vehicle

Abstract

The utility model relates to the field of aircraft technology, concretely relates to a vertical take-off and landing multipurpose ground effect aircraft, including fuselage, one pair of left and right symmetrical wings is fixedly connected to the both sides of fuselage, two cantilever mounting rods are fixed to each side wing, rotatable rotor arm is connected on cantilever mounting rod, and tilt duct type propeller is installed on rotor arm, rotor arm penetrates tilt duct type propeller, the inside of each cantilever mounting rod is provided with steering wheel, and steering wheel output shaft is coaxial with corresponding rotor arm, two underwater pump jet propellers are symmetrically arranged in the area below the waterline of fuselage lower part, and tail propeller is installed to the tail of fuselage, wherein, cantilever mounting rod is hollow structure, and the inside is equipped with the wiring channel that communicates steering wheel and flight control, and rotor arm rotates 0 under the drive of steering wheel °-180 relative to steering wheel shaft.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to a vertical take-off and landing multi-purpose ground effect vehicle. Background Technology

[0002] Ground effect vehicles (GEVs) are special flight vehicles that utilize the ground effect principle to alter the aerodynamic characteristics of their wings, thereby increasing lift and enabling them to fly stably close to the ground or water surface in the ground effect zone. The increased lift is due to the increased pressure on the lower surface of the wing caused by the deceleration of the air between the ground and the wing surface. This method significantly improves aerodynamic efficiency and represents a newly developed and excellent high-speed transportation tool.

[0003] However, existing traditional ground effect vehicles have significant limitations:

[0004] 1. Takeoff and landing environment is highly dependent on calm water: Most ground effect vehicles need to perform long-distance run-offs on water, like seaplanes, to gain sufficient takeoff speed and enter the ground effect zone. This greatly limits their application scenarios, making it impossible for them to be deployed and operated on land, in complex sea conditions, near shore, or in areas lacking open water.

[0005] 2. Lack of vertical takeoff and landing capability: Traditional ground effect vehicles do not have vertical takeoff and landing capabilities and must rely on runways (water or land), resulting in poor deployment flexibility and difficulty in use in confined spaces or emergency situations.

[0006] 3. Limited functionality and inability to operate underwater: Traditional designs focus on above-water ground effect flight and lack the ability to dive into the water for underwater propulsion or operations, limiting their application in fields such as ocean exploration and underwater rescue.

[0007] On the other hand, while vertical takeoff and landing aircraft (such as tiltrotor aircraft and multi-rotor drones) have solved the problem of takeoff and landing site limitations and have flexible deployment capabilities, their high-speed cruise efficiency is usually lower than that of fixed-wing or ground effect aircraft, and they lack a mechanism to improve efficiency by utilizing ground effect, and they do not have the ability to glide on water or propel underwater.

[0008] Therefore, for a takeoff weight of approximately 100 kg, how to combine the large payload capacity of a ground effect vehicle with the flexible deployment capability of a vertical takeoff and landing vehicle to meet the above requirements is a technical problem that needs to be solved. Utility Model Content

[0009] The purpose of this invention is to provide a vertical takeoff and landing multi-purpose ground effect vehicle to solve the problems mentioned in the background art.

[0010] To achieve the above objectives, this utility model provides the following technical solution: a vertical takeoff and landing multi-purpose ground effect vehicle, comprising a fuselage, a pair of symmetrical wings fixedly connected to both sides of the fuselage, two cantilever mounting rods fixed to each wing, a rotatable rotor arm connected to the cantilever mounting rod, a tilting ducted thruster mounted on the rotor arm, the rotor arm passing through the tilting ducted thruster, a servo motor installed inside each cantilever mounting rod, and the servo motor output shaft coaxially connected to the corresponding rotor arm, two underwater pump-jet thrusters symmetrically arranged below the waterline of the lower part of the fuselage, and a tail thruster installed at the tail of the fuselage, wherein the cantilever mounting rod is a hollow structure, and a wiring channel connecting the servo motor and the flight control is provided inside, and the rotor arm rotates from 0° to 180° relative to the servo motor shaft under the drive of the servo motor.

[0011] Preferably, the wingspan of the aircraft is 8 meters, the distance between the two cantilever mounting rods on the same wing is 1.8-2.2 meters, and the distance from the mounting position of the cantilever mounting rod to the root of the wing is 1.2-1.6 meters.

[0012] Preferably, the aspect ratio of the wing is 3-4.

[0013] Preferably, the length, width and height of the cantilever mounting rod are 0.28×0.125×0.08m.

[0014] Preferably, the rotor arm is 1.55 meters long, has a rectangular cross-section, and the vertical distance between the rotor arm's rotation axis and the fuselage's center of gravity is 15-20% of the total fuselage length.

[0015] Preferably, the radius of the tilting ducted thruster is 0.56 meters.

[0016] Preferably, the cantilever mounting rod, rotor arm, and tilting ducted thruster are all made of titanium alloy.

[0017] Compared with the prior art, this utility model provides a vertical takeoff and landing multi-purpose ground effect vehicle with the following advantages: This utility model achieves seamless switching between three modes—vertical takeoff and landing, high-speed flight, and water surface taxiing—through a servo-driven rotor arm rotation structure.

[0018] 1. Vertical Take-off and Landing Mode: The horizontal extension of the rotor arm enables the tilt-ducted propulsion system to provide vertical lift, completely eliminating runway dependence and supporting flexible take-off and landing on land and water.

[0019] 2. High-speed flight mode: The rotor arm rotates 90° upwards, causing the tilt-ducted thruster to move horizontally forward, working in conjunction with the tail thruster to increase speed and range;

[0020] 3. Water surface gliding mode: The rotor arm rotates down 90° to drive the tilting ducted thruster into the water, and the propeller blade tip is submerged in the water surface to form a dual power system with the underwater pump-jet thruster. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of the structure of this utility model;

[0022] Figure 2 This is a schematic diagram of the servo motor.

[0023] Figure 3 This is a top view of the present invention;

[0024] Figure 4 This is a schematic diagram of the vertical takeoff and landing mode;

[0025] Figure 5 This is a diagram illustrating high-speed flight mode.

[0026] Figure 6 This is a schematic diagram of the water gliding mode.

[0027] Explanation of reference numerals in the attached drawings: 1. Fuselage; 2. Wing; 3. Cantilever mounting rod; 4. Rotor arm; 5. Tilting ducted propulsion; 6. Servo; 7. Underwater pump-jet propulsion; 8. Tail propulsion. Detailed Implementation

[0028] The technical solutions of the present utility model will now be described with reference to the accompanying drawings in the embodiments of the present utility model:

[0029] like Figure 1-6 As shown, this utility model provides a vertical takeoff and landing multi-purpose ground effect vehicle, including a fuselage 1. The fuselage 1 adopts a streamlined boat-shaped bottom design to reduce water resistance. A pair of symmetrical wings 2 are fixedly connected to both sides of the fuselage 1. The aspect ratio of the wings 2 is 3-4 to optimize the lift distribution in the ground effect zone. The wingspan of the aircraft is M, which is 8 meters. Two cantilever mounting rods 3 are fixed to each wing 2. The two cantilever mounting rods 3 are symmetrically installed at the front and rear ends of the wings 2. The length, width and height of the cantilever mounting rods 3 are 0.28×0.125×0.08m. The distance between the two cantilever mounting rods 3 on the same wing 2 is H, which is 1.8-2.2 meters to balance the aerodynamic load. The distance from the installation position of the cantilever mounting rod 3 to the root of the wing is L, which is 1.2-1.6 meters to avoid the turbulence area of ​​the fuselage 1.

[0030] A rotatable rotor arm 4 is connected to the cantilever mounting rod 3. The length of the rotor arm 4 is D, which is 1.55 meters. The cross-section of the rotor arm 4 is rectangular and the dimensions are 0.05 × 0.08 meters. The vertical distance between the rotation axis of the rotor arm 4 and the center of gravity of the fuselage 1 is 15-20% of the total length of the fuselage, ensuring pitch stability.

[0031] A tilting ducted thruster 5 is mounted on rotor arm 4. The duct structure of the tilting ducted thruster 5 enhances thrust safety. The radius of the tilting ducted thruster 5 is R, which is 0.56 meters. The cantilever mounting rod 3, rotor arm 4, and tilting ducted thruster 5 are all made of titanium alloy. Rotor arm 4 passes through the tilting ducted thruster 5.

[0032] Each cantilever mounting rod 3 has a servo motor 6 installed inside. The servo motor 6 and the cantilever mounting rod 3 are in a relatively static and fixed state. The cantilever mounting rod 3 has a hollow structure, and its interior has a wiring channel connecting the servo motor 6 and the flight controller. The servo motor 6 is connected to the flight controller, onboard computer and other components through wiring. It can receive control commands from the remote controller, ground station and the flight controller itself through signal transmission to control the rotation of the arms.

[0033] Two underwater pump-jet propulsion units 7 are symmetrically arranged below the waterline on the lower part of fuselage 1 to provide the main thrust for surface navigation and reduce water resistance. A tail thruster 8 is installed at the tail of fuselage 1.

[0034] The output shaft of servo motor 6 is coaxially connected to the corresponding rotor arm 4. Under the drive of servo motor 6, rotor arm 4 rotates from 0° to 180° relative to the shaft of servo motor 6.

[0035] When the engine is stopped, the four tilting ducted thrusters 5 are positioned with their axes perpendicular to the ground, and the bottom of the hull is in contact with the water surface.

[0036] During vertical takeoff from the ground, the four tilt-ducted thrusters 5 are positioned with their axes perpendicular to the ground, operating simultaneously to provide vertical upward thrust to the aircraft. After fully taking off, the tail thrusters 8 on the fuselage begin to work, providing forward thrust to the fuselage. At this time, the fuselage has a forward velocity, the airflow passes through the wings 2, and lift is generated due to the ground effect. When the lift balances the weight of the aircraft, the tilt-ducted thrusters 5 stop rotating, and the two tilt-ducted thrusters 5 located at the nose rotate 90 degrees and then start working again to provide additional power for flight.

[0037] When taking off vertically over water, the operation process is exactly the same as when taking off vertically from the ground.

[0038] During takeoff from the water surface, the underwater pump-jet propulsion unit 7 continuously provides power to the aircraft, while the tail thruster 8 continues to operate. The tilt-ducted thruster 5 rotates underwater to provide power for underwater navigation. Airflow passes over the wing 2, and lift is generated due to the ground effect. When the lift balances the aircraft's weight, the tilt-ducted thruster 5 stops rotating. The two rear tilt-ducted thrusters 5 retract to a horizontal position to reduce drag, while the two front tilt-ducted thrusters 5 rotate upwards 180 degrees and propel backwards to increase the aircraft's forward thrust.

[0039] Vertical takeoff and landing (VTOL) multi-purpose ground effect vehicles can land on and over water, take off vertically from both surfaces, and utilize an energy-saving water taxi takeoff mode. They can also navigate on water. They can carry various equipment to perform multiple functions, including passenger and cargo transport, water patrol, and rescue.

[0040] The above embodiments detail the workflow and structural coordination mechanism of this invention in vertical takeoff and landing, high-speed flight, and water surface taxiing modes. Through precise angle control of the rotor arm 4, optimized power distribution between the tail thruster 8, the front tilting ducted thruster 5, and the underwater pump-jet thruster 7, and underwater coordination between the underwater pump-jet thruster 7 and the tilting ducted thruster 5, this design not only expands the operating environment of traditional ground effect vehicles but also achieves adaptive operation in all scenarios, including land, water, and underwater.

[0041] The above embodiments are merely some, not all, of the embodiments of this utility model. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without inventive effort are within the scope of protection of this utility model.

Claims

1. A vertical take-off and landing multi-purpose ground effect vehicle characterised in that: The fuselage includes a fuselage (1), on which a pair of symmetrical wings (2) are fixedly connected. Each wing (2) has two cantilever mounting rods (3) fixed to it. A rotatable rotor arm (4) is connected to the cantilever mounting rod (3). A tilting ducted thruster (5) is mounted on the rotor arm (4). The rotor arm (4) passes through the tilting ducted thruster (5). A servo motor (6) is installed inside each cantilever mounting rod (3). The output shaft is coaxially connected to the corresponding rotor arm (4). Two underwater pump-jet propulsion units (7) are symmetrically arranged in the area below the waterline of the lower part of the fuselage (1). A tail propulsion unit (8) is installed at the tail of the fuselage (1). The cantilever mounting rod (3) is a hollow structure with a wiring channel connecting the servo motor (6) and the flight control inside. The rotor arm (4) rotates 0°-180° relative to the servo motor (6) axis under the drive of the servo motor (6).

2. The vertical takeoff and landing multi-purpose ground effect vehicle according to claim 1, characterized in that: The aircraft has a wingspan of 8 meters, and the distance between the two cantilever mounting rods (3) on the same wing (2) is 1.8-2.2 meters. The distance between the installation position of the cantilever mounting rod (3) and the root of the wing is 1.2-1.6 meters.

3. The vertical takeoff and landing multi-purpose ground effect vehicle of claim 1, wherein: The aspect ratio of the wing (2) is 3-4.

4. The vertical takeoff and landing multi-purpose ground effect vehicle of claim 1, wherein: The length, width and height of the cantilever mounting rod (3) are 0.28×0.125×0.08m.

5. The vertical takeoff and landing multi-purpose ground effect vehicle of claim 1, wherein: The rotor arm (4) is 1.55 meters long, and the cross-section of the rotor arm (4) is rectangular. The vertical distance between the rotation axis of the rotor arm (4) and the center of gravity of the fuselage (1) is 15-20% of the total length of the fuselage.

6. The vertical takeoff and landing multi-purpose ground effect vehicle of claim 1, wherein: The radius of the tilting ducted thruster (5) is 0.56 meters.

7. The vertical takeoff and landing multi-purpose hovercraft of claim 1, wherein: The cantilever mounting rod (3), rotor arm (4) and tilting ducted thruster (5) are all made of titanium alloy.

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