Rotorcraft

Abstract

The utility model belongs to the technical field of aircrafts, and particularly provides a rotorcraft which comprises a rotorcraft body, a main rotor, a balance empennage and a plurality of balance rotors. The main rotor is connected with the rotor body; the main rotor is used for providing and keeping the rising and hovering lift force of the rotorcraft; the balance rotors are connected with the rotor body, and the multiple balance rotors are arranged around the main rotor; the balance rotor is used for keeping the flight balance of the rotorcraft and controlling the flight direction of the rotorcraft; and the balance empennage is arranged at the tail part of the rotor wing body and is used for offsetting reverse torque generated by rotation of the main rotor wing and the balance rotor wing. According to the rotorcraft, the main rotor and the balance rotors are arranged, the lift force and the balance system of the rotorcraft are separated, and the lift force stability and the flight balance can be kept all the time. And by arranging the balance empennage, the reverse torque generated by rotation of the main rotor and the balance rotor can be offset, so that the rotorcraft cannot rotate in the horizontal plane direction due to the reverse torque, and the flight balance of the rotorcraft is further improved.

Description

Technical Field

[0001] This application belongs to the field of aircraft technology, and more specifically, relates to a rotorcraft. Background Technology

[0002] Currently, the design and performance of gyroplanes in the field of aircraft technology are constantly being improved. However, existing gyroplanes still have some shortcomings in terms of flight stability and controllability. For example, some gyroplanes need to constantly adjust their rotation speed to balance and maintain lift, which can easily lead to control problems, causing the gyroplane to lose lift or balance and crash; helicopters need to constantly change their rotor tilt angle to maintain balance and flight, which is complex in structure and prone to failure. Utility Model Content

[0003] The purpose of this application is to provide a rotorcraft to solve the technical problems of insufficient flight stability and controllability in the prior art.

[0004] To achieve the above objectives, the technical solution adopted in this application is: to provide a rotorcraft, comprising:

[0005] Rotorcraft fuselage;

[0006] The main rotor is connected to the rotor fuselage; the main rotor is used to provide and maintain the lift for the rotorcraft to ascend and hover.

[0007] Multiple balancing rotors are connected to the rotor fuselage and arranged around the main rotor; the balancing rotors are used to maintain the flight balance of the rotorcraft and control the flight direction of the rotorcraft.

[0008] A counterbalance tail fin is disposed at the tail of the rotor fuselage and is used to counteract the opposing torque generated by the rotation of the main rotor and the counterbalance rotor.

[0009] Furthermore, the rotor fuselage includes a main fuselage body and multiple balancing connecting arms. One end of each balancing connecting arm is connected to the fuselage, and the other end of each balancing connecting arm is connected to the balancing rotor. The multiple balancing connecting arms are arranged in a circular array. The main rotor is mounted on the main fuselage body.

[0010] Furthermore, the rotor fuselage also includes a tail connecting arm, one end of which is connected to the fuselage body and the other end of which is connected to the stabilizer tail.

[0011] Furthermore, the main rotor includes a main blade and a main drive unit. The main drive unit is mounted on the fuselage body, and the main blade is connected to the main drive unit. The main drive unit is used to drive the main blade to rotate.

[0012] Furthermore, the balancing rotor includes balancing blades and a balancing drive component. The balancing drive component is mounted on the balancing connecting arm, and the balancing blades are connected to the balancing drive component. The balancing drive component is used to drive the balancing blades to rotate.

[0013] Furthermore, the balancing tail fin includes a tail blade and a tail drive component. The tail drive component is mounted on the tail connecting arm, and the tail blade is connected to the tail drive component. The tail drive component is used to drive the tail blade to rotate.

[0014] Furthermore, the rotation axis of the balancing blade is parallel to the rotation axis of the main blade.

[0015] Furthermore, the rotation axis of the tail blade is perpendicular to the rotation axis of the main blade.

[0016] Furthermore, the size of the main blade is larger than the size of the balance blade, and the size of the main blade is larger than the size of the tail blade.

[0017] Furthermore, the main drive component is a fuel engine or an electric motor.

[0018] The beneficial effects of the gyroplane provided in this application are as follows: Compared with the prior art, this application separates the lift and balance systems of the gyroplane by setting a main rotor and multiple counter-rotors, thus maintaining stable lift and flight balance. By setting a counter-tail, the opposing torque generated by the rotation of the main rotor and the counter-rotors can be counteracted, preventing the gyroplane from rotating in the horizontal direction due to opposing torque, further improving the flight balance of the gyroplane. Compared with helicopters, the gyroplane of this application can maintain flight balance without changing the rotor tilt angle, resulting in a simpler mechanical structure and higher stability. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of this application, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a three-dimensional structural diagram of a rotorcraft provided in an embodiment of this application;

[0021] Figure 2 This is a three-dimensional structural diagram of the rotor fuselage of a rotorcraft provided in an embodiment of this application.

[0022] The following are the labeling elements in the figure:

[0023] 100 - Rotor fuselage; 101 - Main fuselage; 102 - Balance connecting arm; 103 - Tail connecting arm; 104 - Landing support;

[0024] 200 - Main rotor; 201 - Main blade; 202 - Main drive component;

[0025] 300 - Balanced rotor; 301 - Balanced blade; 302 - Balanced drive component;

[0026] 400 - Balanced tail fin; 401 - Tail rotor blade; 402 - Tail drive component;

[0027] 500-Controller. Detailed Implementation

[0028] To make the technical problems, technical solutions, and beneficial effects to be solved by this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and are not intended to limit the scope of this application.

[0029] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0030] It should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0031] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0032] Please refer to the following: Figure 1 and Figure 2The gyroplane provided in this application embodiment will now be described. The gyroplane includes a gyroplane fuselage 100, a main rotor 200, a counterweight 400, and multiple counterweight rotors 300. The main rotor 200 is connected to the gyroplane fuselage 100; the main rotor 200 provides and maintains lift for the gyroplane's ascent and hovering; the counterweight rotors 300 are connected to the gyroplane fuselage 100, and the multiple counterweight rotors 300 are arranged around the main rotor 200; the counterweight rotors 300 maintain the gyroplane's flight balance and control its flight direction; the counterweight 400 is located at the tail of the gyroplane fuselage 100 and counteracts the opposing torque generated by the rotation of the main rotor 200 and the counterweight rotors 300.

[0033] Compared with the prior art, the gyroplane provided in this application embodiment separates the lift and balance systems of the gyroplane by setting a main rotor 200 and multiple balancing rotors 300, thus maintaining stable lift and flight balance. By setting a balancing tail fin 400, the reverse torque generated by the rotation of the main rotor 200 and the balancing rotors 300 can be counteracted, preventing the gyroplane from rotating in the horizontal direction due to reverse torque, further improving the gyroplane's flight balance. Compared with helicopters, the gyroplane of this application can maintain flight balance without changing the rotor tilt angle, resulting in a simpler mechanical structure and higher stability.

[0034] In one embodiment of this application, please refer to Figure 2 The rotor fuselage 100 includes a fuselage body 101 and multiple balancing connecting arms 102. One end of the balancing connecting arm 102 is connected to the fuselage, and the other end of the balancing connecting arm 102 is connected to the balancing rotor 300. The multiple balancing connecting arms 102 are arranged in a ring array. The main rotor 200 is mounted on the fuselage body 101.

[0035] In this embodiment, the fuselage 101 is designed to be robust and able to withstand the powerful lift generated by the main rotor 200. The balancing connecting arm 102 is made of lightweight, high-strength material, ensuring a stable connection while reducing the overall weight of the gyroplane. This design makes the gyroplane more stable during flight and able to cope with various complex flight environments. In addition, the circular array distribution of the balancing connecting arm 102 allows the balancing rotor 300 to be evenly distributed, further enhancing the flight balance of the gyroplane.

[0036] Specifically, the balancing connecting arm 102 can be made of carbon nanotubes or other high-strength, lightweight materials to ensure sufficient strength and stability while reducing weight. Carbon nanotubes possess extremely high strength and stiffness, as well as good toughness, making them one of the ideal materials for manufacturing high-performance aircraft. Furthermore, carbon nanotubes exhibit excellent corrosion resistance, enabling them to maintain stable performance in harsh environments.

[0037] In one embodiment of this application, please refer to Figure 2 The rotor fuselage 100 also includes a tail connecting arm 103, one end of which is connected to the fuselage body 101, and the other end of which is connected to the stabilizer fin 400.

[0038] In this embodiment, the stabilizer fin 400 is securely connected to the rotor fuselage 100 by a tail connecting arm 103, ensuring the stability and reliability of the stabilizer fin 400 during flight. The tail connecting arm 103 is also made of lightweight, high-strength materials to ensure its stability and durability while reducing the overall weight of the rotorcraft. The design of the tail connecting arm 103 allows the stabilizer fin 400 to be stably fixed to the tail of the rotorcraft, providing necessary flight stability. The function of the stabilizer fin 400 is to adjust the rotorcraft's attitude during flight, helping it maintain a stable flight attitude. Through the synergistic effect of the tail connecting arm 103 and the stabilizer fin 400, the rotorcraft can better cope with various complex flight environments during flight, such as changes in wind direction and sudden changes in wind speed, ensuring flight safety and stability.

[0039] In one embodiment of this application, please refer to Figure 2 The rotorcraft fuselage 100 also includes a landing gear 104, which is connected to the bottom of the fuselage body 101 and provides support during landing. The landing gear 104 is designed to take into account the weight of the rotorcraft and the impact force during landing, ensuring a safe and stable landing. The landing gear 104 is also made of lightweight, high-strength materials to reduce the overall weight of the rotorcraft while maintaining sufficient strength and stability. During landing, the landing gear 104 absorbs and disperses the impact force, protecting the rotorcraft fuselage and internal structure from damage. Furthermore, the landing gear 104 can be equipped with shock absorbers to absorb the impact force during landing, protecting the rotorcraft structure from damage and further improving landing stability and safety.

[0040] In one embodiment of this application, please refer to Figure 1 The main rotor 200 includes a main blade 201 and a main drive unit 202. The main drive unit 202 is mounted on the fuselage body 101. The main blade 201 is connected to the main drive unit 202. The main drive unit 202 is used to drive the main blade 201 to rotate.

[0041] In this embodiment, the main lift source of the gyroplane is achieved by setting up the main rotor blade 201 and the main drive component 202. The main rotor blade 201 adopts an advanced aerodynamic design, which can generate sufficient lift when rotating, enabling the gyroplane to take off and land vertically and hover. The main drive component 202 is responsible for providing power to drive the main rotor blade 201 to rotate at high speed. Driven by the main drive component 202, the main rotor blade 201 can efficiently convert power into lift, enabling the gyroplane to maintain stable flight in various complex environments.

[0042] In one embodiment of this application, please refer to Figure 1 The balance rotor 300 includes a balance blade 301 and a balance drive 302. The balance drive 302 is mounted on the balance connecting arm 102. The balance blade 301 is connected to the balance drive 302. The balance drive 302 is used to drive the balance blade 301 to rotate.

[0043] In this embodiment, the balance and stability control of the rotorcraft is achieved by setting up a balance blade 301 and a balance drive component 302. The balance blade 301 also adopts an advanced aerodynamic design, which can generate a certain amount of lift and lateral force when rotating, helping the rotorcraft maintain balance during flight. The balance drive component 302 is responsible for providing power to drive the balance blade 301 to rotate.

[0044] In this embodiment, multiple balancing rotors 300 are provided, each with an identical structure, and the balancing drive component 302 of each balancing rotor 300 can be controlled independently to achieve balance adjustment of the gyroplane under different flight conditions. By precisely controlling the rotational speed and direction of each balancing drive component 302, the flight attitude of the gyroplane can be flexibly adjusted to ensure its stability and safety in complex flight environments. In addition, the synergistic effect of multiple balancing rotors 300 can also improve the gyroplane's resistance to crosswinds, enabling it to maintain stable flight even in severe weather conditions such as strong winds.

[0045] In one embodiment of this application, please refer to Figure 1 The tail fin 400 includes a tail blade 401 and a tail drive 402. The tail drive 402 is mounted on the tail connecting arm 103. The tail blade 401 is connected to the tail drive 402, and the tail drive 402 is used to drive the tail blade 401 to rotate.

[0046] In this embodiment, the flight stability and maneuverability of the rotorcraft are further enhanced by the addition of a tail rotor blade 401 and a tail drive component 402. The tail rotor blade 401 also employs an optimized aerodynamic design, capable of generating the necessary thrust during rotation to counteract the opposing torques generated by the rotation of the main rotor 200 and the counter-rotating rotor 300. The tail drive component 402 is responsible for providing power to the tail rotor blade 401, ensuring its stable and efficient rotation.

[0047] In one embodiment of this application, the rotation axis of the balance blade 301 is parallel to the rotation axis of the main blade 201.

[0048] In this embodiment, the design of the balance blade 301 coordinates the airflow generated by its rotation with that generated by the main blade 201, reducing airflow interference and improving the overall flight efficiency of the gyroplane. Simultaneously, the parallel rotation of the balance blade 301 and the main blade 201 makes the gyroplane's structure more compact, reduces air resistance, and further enhances flight performance. Furthermore, this design helps maintain the gyroplane's balance, resulting in more stable flight.

[0049] In one embodiment of this application, the rotation axis of the tail blade 401 is perpendicular to the rotation axis of the main blade 201.

[0050] In this embodiment, the vertically rotating tail rotor blade 401 design enables the gyroplane to achieve more agile handling performance during flight. When the tail rotor blade 401 rotates vertically, it can more effectively generate thrust to balance the torque generated by the rotation of the main rotor blade 201, thereby enhancing the gyroplane's flight stability. Furthermore, this design helps to reduce the overall size of the gyroplane, making it more compact and easier to store and transport. At the same time, the vertical rotation characteristic of the tail rotor blade 401 also gives it greater adaptability and flexibility in dealing with complex flight environments.

[0051] In one embodiment of this application, the size of the main blade 201 is larger than the size of the balance blade 301, and the size of the main blade 201 is larger than the size of the tail blade 401.

[0052] This design allows the main rotor blade 201 to generate greater lift. Concentrating the lift-generating power on the main rotor blade 201 improves work efficiency, thereby increasing the rotorcraft's flight altitude and load-bearing capacity. Simultaneously, the larger main rotor blade 201 also helps reduce rotorcraft vibration and noise, improving flight comfort and stability. Although the balance blade 301 and tail blade 401 are smaller in size, they each play an indispensable role in flight, jointly ensuring the rotorcraft's flight performance and handling stability.

[0053] In one embodiment of this application, the main drive unit 202 is a fuel engine or an electric motor.

[0054] In this embodiment, when the fuel engine is used as the main drive component 202, its powerful output ensures stable flight of the rotorcraft in various complex environments, allowing it to maintain high-power operation for extended periods and providing strong endurance, making it suitable for long-distance missions. When an electric motor is selected as the main drive component 202, power can be concentrated for work, achieving higher lift efficiency to improve endurance. Furthermore, electric motors operate with lower noise, making them more environmentally friendly and suitable for applications with high noise requirements. In addition, electric motors are easy to maintain and repair, reducing the operating costs of the rotorcraft. Users can flexibly choose the type of main drive component 202 according to specific application scenarios and needs to meet different flight requirements.

[0055] In one embodiment of this application, the main drive unit 202 further includes a transmission. The transmission is used to adjust the rotational speed of the main drive unit 202, thereby achieving precise control over the rotational speed of the main rotor blade 201. By setting the transmission, the rotational speed of the main rotor blade 201 can be adjusted according to flight requirements, optimizing the rotorcraft's flight performance. For example, during takeoff and hovering phases, the rotational speed of the main rotor blade 201 can be appropriately reduced to decrease energy consumption and noise; during high-speed flight, the rotational speed of the main rotor blade 201 can be increased to increase lift and flight speed. The transmission design enables the rotorcraft to adapt to different flight environments and mission requirements, improving its flexibility and applicability.

[0056] In one embodiment of this application, the balance drive 302 and the tail drive 402 can also be either a fuel engine or an electric motor to achieve flexible power configuration. Similar to the main drive 202, when a fuel engine is selected, the balance drive 302 and the tail drive 402 can provide stable and powerful power output, ensuring the balance and stability of the gyroplane during flight. When an electric motor is selected as the balance drive 302 and the tail drive 402, more efficient power conversion can be achieved, reducing energy consumption and noise, while improving the environmental performance and maneuverability of the gyroplane. Users can flexibly choose the type of balance drive 302 and tail drive 402 according to specific application scenarios and needs to optimize the overall performance of the gyroplane.

[0057] In one embodiment of this application, please refer to Figure 1The gyroplane also includes a controller 500, which is mounted on the fuselage body 101. The controller 500 controls the operation of the main drive unit 202, the balance drive unit 302, and the tail drive unit 402. By integrating advanced flight control algorithms, the controller 500 can monitor the gyroplane's flight status in real time and adjust the speed and direction of each drive unit as needed to ensure the gyroplane remains stable under various flight conditions. Furthermore, the controller 500 has fault diagnosis and self-protection functions, enabling it to take timely measures to protect the gyroplane's safety when abnormalities are detected. This intelligent design makes the gyroplane's operation simpler while also improving its flight safety and reliability.

[0058] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A rotorcraft, characterized in that, include: Rotorcraft fuselage; The main rotor is connected to the rotor fuselage; the main rotor is used to provide and maintain the lift for the rotorcraft to ascend and hover. Multiple balancing rotors are connected to the rotor fuselage and arranged around the main rotor; the balancing rotors are used to maintain the flight balance of the rotorcraft and control the flight direction of the rotorcraft. A counterbalance tail fin is disposed at the tail of the rotor fuselage and is used to counteract the opposing torque generated by the rotation of the main rotor and the counterbalance rotor.

2. The rotorcraft as described in claim 1, characterized in that, The rotor fuselage includes a main fuselage body and multiple balancing connecting arms. One end of each balancing connecting arm is connected to the fuselage, and the other end of each balancing connecting arm is connected to the balancing rotor. The multiple balancing connecting arms are arranged in a circular array. The main rotor is mounted on the fuselage body.

3. The rotorcraft as described in claim 2, characterized in that, The rotor fuselage also includes a tail connecting arm, one end of which is connected to the fuselage body and the other end of which is connected to the stabilizer tail.

4. The rotorcraft as described in claim 3, characterized in that, The main rotor includes a main blade and a main drive unit. The main drive unit is mounted on the fuselage body, and the main blade is connected to the main drive unit. The main drive unit is used to drive the main blade to rotate.

5. The rotorcraft as described in claim 4, characterized in that, The balancing rotor includes balancing blades and a balancing drive component. The balancing drive component is mounted on the balancing connecting arm, and the balancing blades are connected to the balancing drive component. The balancing drive component is used to drive the balancing blades to rotate.

6. The rotorcraft as described in claim 5, characterized in that, The tail fin includes a tail blade and a tail drive component. The tail drive component is mounted on the tail connecting arm. The tail blade is connected to the tail drive component. The tail drive component is used to drive the tail blade to rotate.

7. The rotorcraft as described in claim 5, characterized in that, The rotation axis of the balance blade is parallel to the rotation axis of the main blade.

8. The rotorcraft as described in claim 6, characterized in that, The rotation axis of the tail blade is perpendicular to the rotation axis of the main blade.

9. The rotorcraft as described in claim 6, characterized in that, The size of the main blade is larger than the size of the balance blade, and the size of the main blade is larger than the size of the tail blade.

10. The rotorcraft as described in any one of claims 4-9, characterized in that, The main driving component is either a fuel engine or an electric motor.

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