Inclined rotary wing aircraft for water surface take-off and landing and take-off and landing method

Abstract

The invention discloses an inclined rotary wing aircraft for water surface take-off and landing and a take-off and landing method.The aircraft comprises an aircraft body, the aircraft body comprises wings, a power system and a control system, the aircraft further comprises inclined rotary wings, and the inclined rotary wings are rotationally connected with the wings located on the two sides of the aircraft body; and accurate rotation can be carried out along the axial direction of the wing. According to the invention, the advantage of large carrying capacity of the fixed wing during long endurance is combined, the shape and the motion trail of the rotor wing are optimized, the independent rotation resistance is reduced, and the overall aerodynamics is more efficient, so that the total resistance is reduced, and under the condition of the same carrying capacity, the water surface take-off and landing distance is shortened to 1 / 3 compared with that of the traditional fixed wing; and the endurance and the voyage are expanded by more than two times compared with helicopters.

Description

Technical Field

[0001] The present invention relates to the field of aircraft design, in particular to a tilt-rotor aircraft for taking off and landing on water surface and a take-off and landing method. Background Art

[0002] Surface take-off and landing aircraft (including seaplanes and amphibious aircraft) are a unique category of aircraft, referring to fixed-wing aircraft or rotorcraft that can take off and land on the water. They have irreplaceable advantages and value in areas such as maritime missions, commuting in remote areas, forest firefighting, and specific military applications. However, the existing surface take-off and landing fixed-wing aircraft do not have the ability to hover at a precise point and require a long taxiing distance to take off. Long taxiing increases the probability of the aircraft encountering wind and waves, affecting flight efficiency and safety. Therefore, adding a float design to the surface take-off and landing fixed-wing aircraft can achieve surface take-off and landing. Traditional helicopter-configured aircraft with added floats have the ability to land at a fixed point and hover, but are limited by the rotor lift and float design and are not capable of long-distance missions such as offshore operations.

[0003] Therefore, it is urgent to provide a solution for a tilt-rotor aircraft and a take-off and landing method for taking off and landing on water surface. Summary of the Invention

[0004] In order to solve the above problems, the technical solution of the present invention provides a tilt-rotor aircraft for taking off and landing on water surface and a take-off and landing method, which can realize short-distance take-off on the water surface and perform long-distance missions.

[0005] According to a first aspect embodiment of the technical solution of the present invention, a tilt-rotor aircraft for taking off and landing on water is provided, wherein the aircraft includes an aircraft body, the aircraft body includes wings, a power system and a control system, and the aircraft also includes tilt-rotors, which are rotatably connected to wings located on both sides of the aircraft body and can be precisely rotated along the axial direction of the wings.

[0006] In the above solution, the tilt rotor includes a rotor shaft and a plurality of rotors arranged around the rotor shaft;

[0007] The power system is connected to the tilt-rotor wing and is used to drive the rotor wing to rotate along the rotor shaft and the tilt-rotor wing to rotate along the axial direction of the wing.

[0008] In the above scheme, the control system is connected to the power system. The control system includes a controller and is integrated with an attitude sensor and a gyroscope. When the attitude sensor and the gyroscope detect an attitude change of the aircraft body, the attitude change information is transmitted to the controller. The controller receives the attitude change information and calculates the tilt angle of the tilt rotor that needs to be adjusted based on the attitude change information. The controller controls the power system to adjust the tilt angle of the tilt rotor.

[0009] In the above solution, the power system includes a turbine engine, a gearbox and a transmission shaft. The turbine engine serves as a power source to drive the tilt-rotor to rotate through the gearbox and the transmission shaft.

[0010] In the above solution, the connection between the wing and the tilt-rotor wing is a rotating shaft structure, and the tilt-rotor wing is rotationally engaged with the rotating shaft.

[0011] In the above solution, the angle between the rotor and the horizontal plane is 0 to 90 degrees.

[0012] In the above solution, the rotation speed of the tilt rotor is 300-500 r / min.

[0013] In the above solution, the side bottom of the aircraft body is streamlined.

[0014] In the above solution, the bottom surface of the aircraft body is "V"-shaped, with an angle of 30 to 60 degrees.

[0015] According to a second aspect of the technical solution of the present invention, a method for taking off and landing a tilt-rotor aircraft for water surface takeoff and landing is provided. Utilizing the tilt-rotor aircraft for water surface takeoff and landing as described in the above solution, the tilt-rotor includes a rotor shaft and rotors. The method comprises the following steps:

[0016] S1, water takeoff mode, the rotor is at a 45° angle to the horizontal plane, so that the rotor generates upward lift and forward thrust, pushing the aircraft to accelerate and glide out of the water and enter a low-altitude flight state;

[0017] S2, horizontal forward flight mode, the rotor is perpendicular to the horizontal plane, providing propulsion;

[0018] S3, vertical landing mode, the rotor is parallel to the horizontal plane and rotates to provide lift, and the height of the aircraft gradually decreases until the bottom touches the water surface, completing the landing.

[0019] Beneficial effects of the present invention:

[0020] The present invention discloses a tiltrotor aircraft for waterborne takeoff and landing, combining the advantages of fixed-wing aircraft with their long flight time and high payload capacity. By adjusting the rotor angle, the tiltrotor aircraft optimizes the distribution of lift and thrust during different flight phases, enabling fixed-point hovering and precise delivery. During horizontal flight, the tiltrotor aircraft tilts the rotors at a certain angle, allowing each blade to generate more thrust during rotation. This adjustment optimizes the rotor shape and trajectory, reducing individual rotational resistance and making the overall aerodynamics more efficient, thereby reducing total drag. Consequently, with the same payload, the waterborne takeoff and landing distance is reduced to one-third that of traditional fixed-wing aircraft, while the flight time and range are more than doubled compared to helicopters. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying any creative work.

[0022] Figure 1 A schematic diagram of a vertical landing mode of a tilt-rotor aircraft for water takeoff and landing provided by the present invention;

[0023] Figure 2 A schematic diagram of a water surface takeoff mode of a tilt-rotor aircraft for water surface takeoff and landing provided by the present invention;

[0024] Figure 3 A schematic diagram of a horizontal forward flight mode of a tilt-rotor aircraft for water surface takeoff and landing provided by the present invention;

[0025] Figure 4 A bottom view of the tilt-rotor aircraft for taking off and landing on water provided by the present invention;

[0026] Figure 5 A front view of a tilt-rotor aircraft for taking off and landing on water provided by the present invention;

[0027] Figure 6 A side view of the tilt-rotor aircraft for taking off and landing on water provided by the present invention.

[0028] Among them, the aircraft body-1; the tilt rotor-2; the wing-3; the rotor shaft-21; and the rotor-22.

[0029] The purpose, features and advantages of the present invention will be further described with reference to the accompanying drawings and in conjunction with the embodiments. DETAILED DESCRIPTION

[0030] Exemplary embodiments will be described in detail herein, with examples illustrated in the accompanying drawings. In the following description, when referring to the drawings, identical numerals in different figures represent identical or similar elements, unless otherwise indicated. The embodiments described in the following exemplary embodiments are not intended to represent all possible embodiments consistent with the present disclosure. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the present disclosure, as detailed in the appended claims.

[0031] The terms "first," "second," and the like in the description and claims of the present disclosure are used to distinguish similar objects and are not necessarily used to describe a particular order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, such that the embodiments of the present disclosure described herein can, for example, be implemented in orders other than those illustrated or described herein.

[0032] In addition, the terms "comprises" and "having" and any variations thereof are intended to cover a non-exclusive inclusion. For example, a process, method, system, product or apparatus that includes a series of steps or elements is not necessarily limited to those steps or elements expressly listed but may include other steps or elements not expressly listed or inherent to such process, method, product or apparatus.

[0033] Multiple includes two or more.

[0034] It should be understood that the term "and / or" as used in this disclosure simply describes an association between related objects, indicating that three possible relationships exist. For example, "A and / or B" can represent three situations: A exists alone, A and B exist simultaneously, and B exists alone.

[0035] like Figures 1 to 6 As shown, an embodiment of the technical solution of the present invention provides a tilt-rotor aircraft for taking off and landing on water surface, the aircraft includes an aircraft body 1, the aircraft body 1 includes wings 3, a power system and a control system, the aircraft also includes tilt-rotor wings 2, the tilt-rotor wings 2 are rotatably connected to the wings 3 located on both sides of the aircraft body 1, and can be precisely rotated along the axial direction of the wings 3.

[0036] The tilt rotor 2 includes a rotor shaft 21 and a plurality of rotors 22 arranged around the rotor shaft 21 .

[0037] The power system is connected to the tilt-rotor 2 and is used to drive the rotor 22 to rotate along the rotor shaft 21 and the tilt-rotor 2 to rotate along the axial direction of the wing 3 .

[0038] The control system is connected to the power system. The control system is integrated with an attitude sensor and a gyroscope to monitor the attitude changes of the aircraft body 1 in real time and adjust the tilt angle of the tilt rotor 2 through the power system to ensure the stability and maneuverability of the aircraft body 1 in different flight modes.

[0039] Specifically, the control system includes a controller. When the attitude sensor and gyroscope detect changes in the attitude of the aircraft body 1, they transmit this information to the controller. The controller receives and analyzes this information, calculates the required tilt angle of the tilt-rotor 2 based on the attitude change information, and then controls the power system to adjust the tilt angle of the tilt-rotor 2. This achieves control of the aircraft's attitude. Throughout flight, the controller continuously receives attitude change information from the attitude sensor and gyroscope, and adjusts the tilt angle of the tilt-rotor 2 in real time to ensure the aircraft's stability and maneuverability in different flight modes.

[0040] The design of adding tilt-rotor wings 2 to wings 3 combines the advantages of fixed-wing aircraft with their long flight time and high payload capacity. Specifically, during vertical takeoff and landing (VTOL) or hovering, rotors 22 are parallel to the horizontal plane, similar to a helicopter, generating sufficient lift to maintain the aircraft's main body 1's stable position in the air. Furthermore, by fine-tuning the angle and rotation speed of rotors 22, the aircraft's main body 1 can be precisely adjusted in mid-air. This design allows the aircraft's main body 1 to flexibly control its speed and position, enabling precise tasks such as cargo delivery during hovering or low-altitude flight. Equipped with a control system, attitude sensors, and gyroscopes, the controller calculates the required tilt angle of the tilt-rotor wings 2 based on attitude change information, making angle adjustment more precise. Therefore, by adjusting the angle of rotors 22, the distribution of lift and thrust is optimized in different flight phases, enabling fixed-point hovering and precise cargo delivery capabilities. Furthermore, during horizontal flight, rotors 22 are perpendicular to the horizontal plane or tilted at a certain angle (usually several degrees) to increase the thrust generated by each blade during rotation. This adjustment optimizes the shape and movement trajectory of the rotor 22, reduces the individual rotational resistance, and makes the overall aerodynamics more efficient, thereby reducing the total resistance. Therefore, with the same load capacity, the water take-off and landing distance can be shortened to one-third compared to traditional fixed-wing aircraft, and the flight time and range can be extended by more than twice compared to helicopters.

[0041] The tilt rotor 2 is rotatably connected to the wing 3 via a rotating shaft. Specifically, there are multiple rotors 22 on each wing 3. The tilt rotor 2 is connected to the wing 3 via a high-strength rotating shaft to ensure stability during rotation.

[0042] Preferably, when the aircraft body 1 is on the water, the tilt rotor 2 is 1 to 2 meters away from the water surface. Such a position design helps to fully utilize the water surface space during takeoff and landing, and enables the rotor 22 to function effectively in both hovering and horizontal flight.

[0043] The tilt-rotor 2 has an angle of 0 to 90 degrees with the horizontal plane. It is connected to the wing 3 via a high-strength shaft and equipped with precise electric or hydraulic devices, allowing it to tilt flexibly between hovering, vertical takeoff and landing, and fixed-wing flight propulsion. When the tilt-rotor 2 is tilted 45 degrees, the lift generated by the rotor 22 combines with the thrust vector to provide both upward lift to overcome gravity for water takeoff and forward pulling force to propel the aircraft body 1 to accelerate gliding.

[0044] The diameter of the tilt rotor 2 is 2 to 3 meters to provide sufficient lift and thrust.

[0045] The rotation speed of the tilt rotor 2 is 300 to 500 r / min and is adjusted according to different flight phases such as hovering, low-altitude flight or high-speed level flight.

[0046] The power system includes a turbine engine, a gearbox, and a transmission shaft. The turbine engine serves as a power source and drives the tilt-rotor 2 through the gearbox and transmission shaft to achieve efficient energy conversion.

[0047] In this embodiment, the bottom surface of the aircraft body 1 is preferably "V"-shaped, and the bottom of the side is streamlined. The angle of the "V"-shaped structure of the bottom surface of the aircraft body 1 is 30 to 60 degrees. Preferably, it is 45 degrees. The bottom of the aircraft body 1 adopts a V-shaped and streamlined design similar to the bottom structure of a ship, which can provide lateral stability. When it lands on the water, it can effectively offset the impact of lateral water flow, reduce the deviation caused by crosswind, and ensure that the aircraft lands smoothly on the water; the "V"-shaped structure contributes to the longitudinal stability of the aircraft. Even in the case of large waves, the V-shaped bottom can help the aircraft maintain balance and reduce back and forth shaking. When the aircraft body 1 contacts the water surface, it reduces splashing and potential damage to the aircraft body 1's structure. The V-shaped bottom also quickly cuts through the water surface, reducing the transmission of shock waves and making landing more stable. It also facilitates rapid water discharge, with a displacement of 0.3 to 0.8 tons, depending on the total weight of the aircraft and the design optimization of the bottom structure. This can reduce drag and shorten the time the aircraft spends on the water surface, making it easier for the aircraft to break away from the water. This design also makes the aircraft easier to control while gliding on the water, allowing for more accurate adjustment of the aircraft's attitude to ensure safe takeoff and landing. The streamlined design of the entire aircraft reduces air resistance and improves flight efficiency.

[0048] Furthermore, the base of the aircraft is made of lightweight composite materials, and the surface is specially treated to reduce water resistance.

[0049] According to a second embodiment of the technical solution of the present invention, a method for taking off and landing a tilt-rotor aircraft for water surface takeoff and landing is provided, using the tilt-rotor aircraft for water surface takeoff and landing as described above, comprising the following steps:

[0050] S1, water takeoff mode, the rotor is at a 45° angle to the horizontal plane, so that the rotor generates upward lift and forward thrust, pushing the aircraft to accelerate and glide out of the water and enter a low-altitude flight state;

[0051] S2, horizontal forward flight mode, the rotor is perpendicular to the horizontal plane, providing propulsion;

[0052] S3, vertical landing mode, the rotor is parallel to the horizontal plane and rotates to provide lift, and the height of the aircraft gradually decreases until the bottom touches the water surface, completing the landing.

[0053] The power system is connected to the tilt-rotor to drive the rotation of the rotor shaft of the tilt-rotor and the rotation of the tilt-rotor along the axial direction of the wing. A control system is connected to the power system and includes a controller integrated with an attitude sensor and a gyroscope. When the attitude sensor and gyroscope detect changes in the attitude of the aircraft body, they transmit the attitude change information to the controller. The controller receives the attitude change information and calculates the tilt angle of the tilt-rotor to be adjusted based on the attitude change information. The controller then controls the power system to adjust the tilt angle of the tilt-rotor.

[0054] It should be noted that, in this document, the terms "comprises," "includes," or any other variations thereof are intended to encompass non-exclusive inclusion, such that a process, method, article, or apparatus comprising a series of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of other identical elements in the process, method, article, or apparatus comprising the element.

[0055] The serial numbers of the above embodiments of the present invention are for description only and do not represent the advantages or disadvantages of the embodiments.

[0056] Through the description of the above embodiments, those skilled in the art can clearly understand that the above implementation method can be implemented by means of software plus the necessary general hardware platform, or of course by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, can be embodied in the form of a software product. The computer software product is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk), and includes a number of instructions for enabling a terminal (which can be a mobile phone, computer, server, air conditioner, or network device, etc.) to execute the methods described in each embodiment of the present invention.

[0057] The embodiments of the present invention are described above in conjunction with the accompanying drawings, but the present invention is not limited to the above-mentioned specific implementation methods. The above-mentioned specific implementation methods are merely illustrative and not restrictive. Under the guidance of the present invention, ordinary technicians in this field can also make many forms without departing from the scope of protection of the present invention and the claims, all of which are protected by the present invention.

Claims

1. A tilt-rotor aircraft for taking off and landing on water, the aircraft comprising an aircraft body, characterized in that: The aircraft body includes wings, a power system and a control system. The aircraft also includes tilt-rotating wings, which are rotatably connected to the wings located on both sides of the aircraft body and can rotate precisely along the axial direction of the wings.

2. The tilt-rotor aircraft for water take-off and landing according to claim 1, characterized in that: The tilt rotor includes a rotor shaft and a plurality of rotors arranged around the rotor shaft; The power system is connected to the tilt-rotor wing and is used to drive the rotor wing to rotate along the rotor shaft and the tilt-rotor wing to rotate along the axial direction of the wing.

3. The tilt-rotor aircraft for water take-off and landing according to claim 2, characterized in that: The control system is connected to the power system. The control system includes a controller and is integrated with an attitude sensor and a gyroscope. When the attitude sensor and the gyroscope detect an attitude change of the aircraft body, the attitude change information is transmitted to the controller. The controller receives the attitude change information and calculates the tilt angle of the tilt rotor that needs to be adjusted based on the attitude change information. The controller controls the power system to adjust the tilt angle of the tilt rotor.

4. The tilt-rotor aircraft for water take-off and landing according to claim 2, characterized in that: The power system includes a turbine engine, a gear box and a transmission shaft. The turbine engine serves as a power source and drives the tilt-rotor to rotate through the gear box and the transmission shaft.

5. The tilt-rotor aircraft for water take-off and landing according to claim 1, characterized in that: The connection between the wing and the tilt-rotor wing is a rotating shaft structure, and the tilt-rotor wing is rotationally engaged with the rotating shaft.

6. The tilt-rotor aircraft for water take-off and landing according to claim 2, characterized in that: The included angle between the rotor and the horizontal plane is 0-90°.

7. The tilt-rotor aircraft for water take-off and landing according to claim 1, characterized in that: The rotation speed of the tilt rotor is 300-500 r / min.

8. The tilt-rotor aircraft for water take-off and landing according to claim 1, characterized in that: The side bottom of the aircraft body is streamlined.

9. The tilt-rotor aircraft for water take-off and landing according to claim 1, characterized in that: The bottom surface of the aircraft body is "V"-shaped, with an angle of 30 to 60 degrees.

10. A method for taking off and landing a tilt-rotor aircraft for taking off and landing on water, characterized in that: Utilizing the tilt-rotor aircraft for water surface takeoff and landing according to any one of claims 1 to 9, wherein the tilt-rotor comprises a rotor shaft and a rotor, the takeoff and landing method comprises the following steps: S1, water takeoff mode, the rotor is at a 45° angle to the horizontal plane, so that the rotor generates upward lift and forward thrust, pushing the aircraft to accelerate and glide out of the water and enter a low-altitude flight state; S2, horizontal forward flight mode, the rotor is perpendicular to the horizontal plane, providing propulsion; S3, vertical landing mode, the rotor is parallel to the horizontal plane and rotates to provide lift, and the height of the aircraft gradually decreases until the bottom touches the water surface, completing the landing.

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