A type of waterborne vertical takeoff and landing manned aircraft

Abstract

This utility model discloses a waterborne vertical takeoff and landing (VTOL) manned aircraft, comprising a fuselage, wings, a vertical tail, tail floats, outer wing floats, and several rotor propulsion units. This waterborne VTOL manned aircraft is a lightweight seaplane capable of vertical takeoff and landing on water at any time, providing convenience for applications such as water rescue and sightseeing. The multi-float design, combining wing floats and tail floats, ensures the aircraft's stability on water. The propellers are entirely enclosed within duct openings, increasing propeller efficiency while significantly enhancing safety and reducing the risk of injury to personnel on the ground. Furthermore, the multi-rotor and wing-based structure allows both the multi-rotor and wings to provide lift during forward flight, ensuring a certain level of safety while increasing cruising efficiency. The motors employ a dual-winding configuration (or coaxial dual propellers), ensuring a stable landing even if a single winding fails.

Description

Technical Field

[0001] This utility model relates to the field of aviation technology, specifically to a waterborne vertical take-off and landing manned aircraft. Background Technology

[0002] The low-altitude economy is developing steadily, and various application scenarios for aircraft have been fully explored. Among these, water-based applications account for a significant portion, including maritime rescue, island transportation, tourism, and water recreation. However, existing technologies have the following shortcomings for water-based applications:

[0003] Traditional seaplanes rely on long-distance taxiing for takeoff and landing, cannot take off and land vertically, and are limited by runway conditions.

[0004] Conventional aircraft (such as multi-rotor drones, tiltrotor aircraft, etc.): can take off and land on land or ships, but lack stable floating ability on water. Utility Model Content

[0005] The technical problem solved by this utility model is to provide...

[0006] The technical solution adopted by this utility model to solve its technical problem is:

[0007] A manned vertical takeoff and landing aircraft for waterborne applications, comprising a fuselage, wings, a vertical tail, tail floats, outer wing floats, and several rotor propulsion systems;

[0008] The wings are symmetrically arranged with the fuselage on the left and right sides, and are located at the front section of the fuselage to form left and right wings. The wing inlet openings are symmetrically arranged in the middle of the left and right wings, and the inlet rotor power is installed in the wing inlet openings through the inlet rotor power mounting rod. The inlet rotor power is respectively connected to the wing inlet openings of the left and right wings to form the left inlet rotor power and the right inlet rotor power.

[0009] The tail of the fuselage is regularly provided with a tail duct opening, and a tail rotor power unit is arranged and installed in the tail duct opening through a tail rotor power mounting rod.

[0010] The vertical tail includes an upper vertical tail and a lower vertical tail. The upper vertical tail and the lower vertical tail are symmetrically arranged on the left and right sides of the fuselage and are respectively fixed to the upper and lower ends of the left and right sides of the tail duct opening of the fuselage, forming left and right upper vertical tails and left and right lower vertical tails; the roots of the upper vertical tail and the lower vertical tail are connected.

[0011] The tail float is fixed to the tip of the left and right downward-pointing tails, and the outer float of the wing is fixed to the tip of the left and right wings.

[0012] Preferably, the fuselage adopts a streamlined fuselage shape, and the fuselage belly adopts a boat-shaped belly shape.

[0013] Preferably, the wing adopts a low-speed, high-lift airfoil, and its structural form is a gull wing structure.

[0014] Furthermore, the in-wing rotor power mounting rods are symmetrically fixed to both sides of the fuselage, with their tips located in the in-wing duct openings of the wing, for mounting the left in-wing rotor power and the right in-wing rotor power.

[0015] Furthermore, the tail rotor power mounting rod is fixed to the tail of the fuselage, and its tip is disposed in the tail duct opening of the fuselage.

[0016] Furthermore, the upper vertical tail is provided with an outward tilt angle of 32° to 38°.

[0017] Furthermore, the drooping tail is provided with an outward tilt angle of 8° to 12°.

[0018] Preferably, the power sources for the right wing inner rotor, the left wing inner rotor, and the tail rotor all include a motor, an electronic control unit, and a propeller. The motor and electronic control unit are designed as an integrated unit, and the rotor power adopts a coaxial dual-propeller power system.

[0019] The beneficial effects of this utility model are:

[0020] This utility model relates to a lightweight seaplane capable of vertical takeoff and landing (VTOL) on water, providing convenience for applications such as water rescue and sightseeing. The multi-buoy design, combining wing and tail floats, ensures the aircraft's stability on water; the propellers are entirely enclosed within the duct opening, increasing propeller efficiency while significantly enhancing safety and reducing the risk of injury to personnel on the ground.

[0021] This utility model relates to a waterborne vertical takeoff and landing manned aircraft, which adopts a multi-rotor and wing structure. During forward flight, the multi-rotor and wing simultaneously provide lift, ensuring a certain level of safety while increasing cruise efficiency. The motor uses a dual-winding configuration (or coaxial dual propellers), ensuring a stable landing even if a single winding fails. Attached Figure Description

[0022] Figure 1 This is a three-dimensional structural diagram of the present invention;

[0023] Figure 2 for Figure 1 Front view;

[0024] Figure 3 for Figure 1 Top view;

[0025] Figure 4 This is a schematic diagram of the coaxial twin propellers of this utility model;

[0026] The diagram is marked as follows:

[0027] 1. Fuselage; 11. Cockpit canopy; 2. Wing; 201. Wing inlet duct; 21. Wing inlet rotor power mount; 301. Fuselage tail duct; 31. Tail rotor power mount; 4. Upper vertical tail; 5. Lower vertical tail; 6. Tail float; 7. Wing outer float.

[0028] A. Powered by the inner rotor of the right wing; B. Powered by the inner rotor of the left wing; C. Powered by the tail rotor. Detailed Implementation

[0029] To make the above-mentioned contents, objectives, and beneficial effects of this utility model more apparent and understandable, the specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a full understanding of this utility model. However, this utility model can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this utility model. Therefore, this utility model is not limited to the specific embodiments disclosed below.

[0030] It should be noted that, unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0031] like Figure 1-4 As shown, this utility model provides a waterborne vertical take-off and landing manned aircraft, including a fuselage 1, wings 2, a vertical tail, tail floats 6, outer wing floats 7, and several rotor engines.

[0032] The fuselage 1 adopts a streamlined shape, but is not limited to a streamlined shape. Its belly can be boat-shaped, so that the fuselage can provide most of the buoyancy when the aircraft is hovering on water. The cockpit and cockpit canopy 11 are arranged on the upper front of the fuselage 1. When the cockpit canopy 11 is opened, it is convenient for the occupants to enter the internal cockpit of the fuselage 1.

[0033] Furthermore, wings 2 are symmetrically arranged on the left and right sides of fuselage 1, located at the front section of fuselage 1, forming left and right wings. The airfoil of wings 2 is a low-speed, high-lift airfoil, and its structural form is a gull wing.

[0034] Furthermore, wing inlet ducts 201 are symmetrically arranged at the midpoint of the left and right wings, and in-wing rotor power units are installed in the wing inlet ducts 201 via in-wing rotor power mounting rods 21. The in-wing rotor power units are located in the wing inlet ducts 201 of the left and right wings, respectively, forming the left in-wing rotor power unit B and the right in-wing rotor power unit A. The in-wing rotor power mounting rods 21 are symmetrically fixed to both sides of the fuselage 1, and their tips are located in the wing inlet ducts 201 to form power mounting components for installing the left in-wing rotor power unit B and the right in-wing rotor power unit A.

[0035] Furthermore, a tail duct opening 301 is provided at the tail of the fuselage 1, and a tail rotor power unit C is installed in the tail duct opening 301 via a tail rotor power mounting rod 31. The tail rotor power mounting rod 31 is fixed to the tail of the fuselage 1, and its tip is located in the tail duct opening 301 to form a power mounting component for installing the tail rotor power unit C.

[0036] The rotor propulsion system of the aircraft consists of the right wing internal rotor A, the left wing internal rotor B, and the tail rotor C, providing power for vertical takeoff and landing and loitering flight. The propellers of the rotor propulsion system are all located inside the duct openings.

[0037] The rotor propulsion system of the aircraft comprises the right wing inner rotor power unit A, the left wing inner rotor power unit B, and the tail rotor power unit C. By simultaneously increasing or decreasing the rotational speeds of the right wing inner rotor power unit A, the left wing inner rotor power unit B, and the tail rotor power unit C, the aircraft achieves ascent or descent during the vertical takeoff and landing (VTOL) and cruise phases. By increasing the rotational speeds of the right wing inner rotor power unit A and the left wing inner rotor power unit B while decreasing the rotational speed of the tail rotor power unit C, the aircraft's pitch angle during VTOL and cruise phases is increased. By decreasing the rotational speed of the right wing inner rotor power unit A while increasing the rotational speed of the left wing inner rotor power unit B, the aircraft's roll angle during VTOL and cruise phases is increased. By increasing the rotational speed of the counter-clockwise rotating rotors while decreasing the rotational speeds of all clockwise rotating rotors in the rotor system, the aircraft rotates clockwise during VTOL and cruise phases.

[0038] Furthermore, such as Figure 1 and Figure 2 As shown, the aircraft's vertical tail includes an upper vertical tail 4 and a lower vertical tail 5. The upper vertical tail 4 is symmetrically arranged on the left and right sides of the fuselage 1 and is fixed to the upper ends of the left and right sides of the tail duct opening 301 of the fuselage. The upper vertical tail 4 is provided with a large outward cant angle α, which is preferably 32-38°. In one example, the outward cant angle is 35°.

[0039] Furthermore, the drooping tail 5 is also symmetrically arranged on the left and right sides of the fuselage 1, and is fixed to the lower ends of the left and right sides of the duct opening 301 at the rear of the fuselage. The drooping tail 5 is provided with a certain outward angle β, which is preferably 8 to 12°. In one example, the outward angle is 10°. The upper drooping tail 4 and the drooping tail 5 are connected at their roots.

[0040] Furthermore, the tail float 6 is fixed to the tip of the drooping tail 5 (the lower end of the drooping tail 5). The tail float 6 is used to increase the longitudinal stability of the aircraft when floating on water, and can prevent the tail from sinking or touching the water. When the aircraft's takeoff / landing attitude changes significantly, it can prevent the tail rotor power C from contacting the water surface.

[0041] Furthermore, the outer wing floats 7 are fixed to the tips of the left and right wings. The outer wing floats 7 are used to increase the lateral stability of the aircraft when floating on water, preventing the wings from touching the water when the aircraft tilts and avoiding rollover. Simultaneously, the outer wing floats 7 and the tail floats 6 provide some buoyancy to the aircraft, which can provide a restoring torque when the aircraft tilts, keeping the fuselage level.

[0042] Furthermore, the power units for the right wing's inner rotor (A), the left wing's inner rotor (B), and the tail rotor (C) all include motors, electronic controls, and propellers, with the motors and electronic controls integrated into a single design. The motors can employ a dual-winding configuration to ensure a certain degree of redundancy in the power system, allowing the aircraft to land smoothly even if a single winding fails. Figure 4 As shown, the rotor is powered by a coaxial twin-propeller configuration, which ensures a smooth landing even if one power source fails.

[0043] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of this utility model. It should be understood that the above descriptions are merely specific embodiments of this utility model and are not intended to limit this utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A water-based vertical take-off and landing manned aircraft, characterized by: It includes the fuselage (1), wings (2), vertical tail, tail floats (6), outer wing floats (7), and several rotor engines; The wings (2) are arranged symmetrically with the fuselage (1) and are located at the front section of the fuselage (1) to form left and right wings; wing inlet openings (201) are symmetrically provided at the middle position of the left and right wings, and wing inlet rotor power is installed in the wing inlet openings (201) through the wing inlet power mounting rod (21); the wing inlet rotor power forms the left wing inlet rotor power (B) and the right wing inlet rotor power (A) respectively with the wing inlet openings (201) of the left and right wings; The tail of the fuselage (1) is regularly provided with a tail duct opening (301), and a tail rotor power unit C is arranged and installed in the tail duct opening (301) via a tail rotor power mounting rod (31). The vertical tail includes an upper vertical tail (4) and a lower vertical tail (5). The upper vertical tail (4) and the lower vertical tail (5) are symmetrically arranged on the left and right sides of the fuselage (1) and are respectively fixed to the upper and lower ends of the left and right sides of the tail duct opening (301) of the fuselage to form left and right upper vertical tails and left and right lower vertical tails; the roots of the upper vertical tail (4) and the lower vertical tail (5) are connected. The tail float (6) is fixed to the tip of the left and right drooping tails, and the outer wing float (7) is fixed to the tip of the left and right wings.

2. The water-based vertical take-off and landing passenger aircraft according to claim 1, characterized in that: The fuselage (1) adopts a streamlined fuselage, and the belly of the fuselage adopts a boat-shaped belly.

3. The waterborne vertical takeoff and landing manned aircraft according to claim 1, characterized in that: The wing (2) adopts a low-speed, high-lift airfoil, and its structural form is a gull wing structure.

4. The waterborne vertical takeoff and landing manned aircraft according to claim 1, characterized in that: The in-wing rotor power mounting rod (21) is symmetrically fixed to both sides of the fuselage (1), and its tip is set in the in-wing duct (201) of the wing for installing the left in-wing rotor power (B) and the right in-wing rotor power (A).

5. The waterborne vertical takeoff and landing manned aircraft according to claim 1, characterized in that: The tail rotor power mounting rod (31) is fixed to the tail of the fuselage (1), and its tip is located in the tail duct opening (301) of the fuselage.

6. The waterborne vertical takeoff and landing manned aircraft according to claim 1, characterized in that: The upper vertical tail (4) is provided with an outward tilt angle of 32° to 38°.

7. The waterborne vertical takeoff and landing manned aircraft according to claim 1, characterized in that: The drooping tail (5) is provided with an outward tilt angle of 8° to 12°.

8. The waterborne vertical takeoff and landing manned aircraft according to any one of claims 1-7, characterized in that: The right wing inner rotor power (A), the left wing inner rotor power (B), and the tail rotor power (C) all include a motor, electronic control, and propeller. The motor and electronic control are integrated into a single design, and the rotor power adopts a coaxial twin-propeller power system.

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