An external rotor motor aircraft

Abstract

The application relates to the technical field of aircrafts, and discloses an outer-rotor motor aircraft, which comprises a disc-shaped stealth outer shell, a disc-shaped sandwich shell and a double-layer outer-rotor motor propeller mechanism; the disc-shaped stealth outer shell comprises an upper outer shell and a lower outer shell, and the upper outer shell and the lower outer shell are fixedly buckled; the disc-shaped sandwich shell is located in the disc-shaped stealth outer shell, and the disc-shaped sandwich shell comprises an upper shell cover and a lower shell cover, and the upper shell cover and the lower shell cover are fixedly buckled; the double-layer outer-rotor motor propeller mechanism is located between the upper shell cover and the lower shell cover, and the double-layer outer-rotor motor propeller mechanism comprises a central fixed stator and two groups of independent rotating rotor assemblies; the top end and the bottom end of the central fixed stator are fixedly connected with the upper shell cover and the lower shell cover respectively. The application has the following advantages and effects: the overall structure of the aircraft is highly integrated, the aircraft is stable in flight, the aircraft does not spin, the aircraft can be omnidirectionally vectored and maneuvered, efficient and accurate attitude and heading control is realized, and the aircraft has natural radar and infrared stealth performance.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to an external rotor motor aircraft. Background Technology

[0002] Vertical takeoff and landing (VTOL) aircraft are mainly used to carry people and cargo and perform special missions. They take off and fly by relying on the static buoyancy of the air or the aerodynamic forces generated by the relative motion of the air. VTOL aircraft are mainly divided into three categories: conventional multi-rotor UAVs, coaxial helicopters, and ducted disc aircraft.

[0003] In existing technologies, traditional vertical takeoff and landing (VTOL) aircraft often adopt a multi-arm external independent external rotor motor layout, with each motor driving a propeller independently. The counter-rotation of diagonal rotors offsets the anti-torque. This structure makes the propeller and motor completely exposed, and the metal motor housing and blades become strong radar reflectors, lacking natural stealth capabilities. It cannot meet the needs of covert reconnaissance and low-altitude special operations. Furthermore, the dispersed arm layout occupies a large amount of external space, the internal payload bay is small, and the space utilization rate is low. The failure of a single motor can easily lead to the loss of control and crash of the entire aircraft. The flight control redundancy is extremely low, and attitude adjustment is achieved solely by rotor differential speed without aerodynamic vector assistance. In windy conditions, hovering at a fixed point results in significant shaking, and the control precision is insufficient.

[0004] Therefore, we propose an external rotor motor aircraft to solve the above problems. Summary of the Invention

[0005] The purpose of this application is to provide an external rotor motor aircraft that features a highly integrated overall structure, stable flight, no spin, omnidirectional vector maneuverability, efficient and precise attitude and heading control, and inherent radar and infrared stealth capabilities.

[0006] The above-mentioned technical objective of this application is achieved through the following technical solution: an external rotor motor aircraft, comprising a disc-shaped stealth shell, a disc-shaped sandwich shell, and a double-layer external rotor motor propeller mechanism; the disc-shaped stealth shell comprises an upper shell and a lower shell, which are fastened together; the disc-shaped sandwich shell is located inside the disc-shaped stealth shell, and the disc-shaped sandwich shell comprises an upper shell cover and a lower shell cover, which are fastened together; the double-layer external rotor motor propeller mechanism is located between the upper shell cover and the lower shell cover, and the double-layer external rotor motor propeller mechanism comprises a central fixed stator and two sets of independent rotating rotor assemblies, the top and bottom of the central fixed stator are respectively fixedly connected to the upper shell cover and the lower shell cover, and the two sets of independent rotating rotor assemblies are sleeved on the central fixed stator.

[0007] A further configuration of this application is as follows: the dual-group independent rotating rotor assembly includes an upper annular rotor, an upper propeller, a lower annular rotor, and a lower propeller; the upper annular rotor is rotatably mounted on the top of the central fixed stator; the upper propeller is mounted on the top of the upper annular rotor; the lower annular rotor is rotatably mounted on the bottom of the central fixed stator; the upper annular rotor and the lower annular rotor are each independently electromagnetically driven; the lower propeller is mounted on the bottom of the lower annular rotor; and the upper propeller and the lower propeller rotate in opposite directions.

[0008] A further configuration of this application is: the upper propeller is sleeved on the upper annular rotor via an upper shaft ring, and the lower propeller is sleeved on the lower annular rotor via a lower shaft ring.

[0009] A further feature of this application is that: the outer annular wall surfaces of the upper and lower shell covers are provided with a plurality of equally spaced annularly distributed assembly holes, and a grid vector assembly is provided in each of the plurality of assembly holes. The grid vector assembly includes an annular frame and a plurality of grid blades. The annular frame is fixedly installed in the assembly hole, and the grid blades are rotatably installed in the annular frame. A micro servo motor is installed and fixed in the annular frame, and the micro servo motor is used to synchronously adjust the tilt angle of the plurality of grid blades.

[0010] A further feature of this application is that the upper shell, lower shell, and grille blades are all made of wave-absorbing and heat-insulating composite materials.

[0011] A further feature of this application is that both the upper and lower annular rotors are made of carbon fiber reinforced plastic, and neodymium iron boron magnets are attached to the inner walls of both the upper and lower annular rotors.

[0012] A further feature of this application is that both the upper propeller and the lower propeller are made of carbon fiber.

[0013] This application includes at least one of the following beneficial technical effects:

[0014] This application designs an upper and lower propeller with independently adjustable speed and direction. When the upper and lower propellers rotate at the same speed but in opposite directions, the counter-torque can cancel each other out, ensuring that the fuselage as a whole will not spin, resulting in stable flight and strong anti-interference capability. When the upper and lower propellers rotate at different speeds, they generate pitch or roll torque to assist in attitude control. By controlling the independent start and stop of the upper and lower propellers, special maneuvers and emergency attitude adjustments can be achieved.

[0015] This application designs the speed difference between the upper and lower propellers to generate attitude torque, enabling coarse attitude adjustment. It also designs a grid vector component to guide the airflow direction by adjusting the tilt angle of the grid blades, achieving fine attitude and heading control. With the combined effect of the two, efficient and flexible omnidirectional maneuvering is achieved, improving control precision and response speed.

[0016] The disc-shaped stealth shell, composed of an upper and lower outer shell, gives the aircraft an overall saucer-like appearance and a naturally low radar cross-section, effectively scattering radar waves. By completely enclosing the disc-shaped sandwich shell and the double-layered external rotor motor propeller mechanism inside the disc-shaped stealth shell, with no exposed rotating parts, the radar reflection source is significantly reduced. The disc-shaped stealth shell, made of radar-absorbing and heat-insulating composite materials, concentrates the heat generated by the double-layered external rotor motor propeller mechanism inside the disc-shaped stealth shell, reducing infrared signal characteristics. This ensures that the aircraft achieves a dual natural stealth effect of radar stealth and infrared stealth, further enhancing its radar stealth performance. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying 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.

[0018] Figure 1 This is a three-dimensional structural diagram of this embodiment.

[0019] Figure 2 This is a schematic diagram of the exploded three-dimensional structure of this embodiment.

[0020] Figure 3 This is a schematic diagram of the exploded three-dimensional structure of the disc-shaped sandwich shell.

[0021] Figure 4 This is a three-dimensional structural diagram of a double-layer external rotor motor propeller mechanism.

[0022] Figure 5 This is an exploded three-dimensional structural diagram of a double-layer external rotor motor propeller mechanism.

[0023] In the diagram, 1. Upper outer shell; 2. Lower outer shell; 3. Upper shell cover; 4. Lower shell cover; 5. Double-layer external rotor motor propeller mechanism; 51. Central fixed stator; 52. Upper annular rotor; 53. Upper propeller; 54. Lower annular rotor; 55. Lower propeller; 56. Upper shaft collar; 57. Lower shaft collar; 6. Annular frame; 7. Grid blades. Detailed Implementation

[0024] The technical solution of this application will be clearly and completely described below with reference to specific embodiments. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0025] See Figures 1-5 This application provides an external rotor motor aircraft, including a disc-shaped stealth shell, a disc-shaped sandwich shell, and a double-layer external rotor motor propeller mechanism 5; the disc-shaped stealth shell includes an upper shell 1 and a lower shell 2, which are fastened together; the disc-shaped sandwich shell is located inside the disc-shaped stealth shell, and includes an upper shell cover 3 and a lower shell cover 4, which are fastened together; the double-layer external rotor motor propeller mechanism 5 is located between the upper shell cover 3 and the lower shell cover 4, and includes a centrally fixed stator 5. The central fixed stator 51 has two sets of independent rotating rotor assemblies. The top and bottom of the central fixed stator 51 are fixedly connected to the upper shell cover 3 and the lower shell cover 4, respectively. Three-phase windings are evenly distributed on the outer periphery of the central fixed stator 51 to form an annular electromagnetic drive surface. The central fixed stator 51 has a hollow columnar structure and serves as the installation space for equipment bay, payload bay, flight control system and energy battery or fuel. The central fixed stator 51 does not rotate as a whole, providing rigid support and structural foundation for the entire aircraft. The two sets of independent rotating rotor assemblies are fitted on the central fixed stator 51.

[0026] In this embodiment, the dual-set independent rotating rotor assembly includes an upper annular rotor 52, an upper propeller 53, a lower annular rotor 54, and a lower propeller 55. The upper annular rotor 52 is rotatably mounted on the top of the central fixed stator 51. The upper propeller 53 is disposed on the top of the upper annular rotor 52. The lower annular rotor 54 is rotatably mounted on the bottom of the central fixed stator 51. The upper annular rotor 52 and the lower annular rotor 54 are each independently electromagnetically driven, and both the upper annular rotor 52 and the lower annular rotor 54 form an electromagnetic drive relationship around the central fixed stator 51, constituting a reverse motor structure. The lower propeller 55... Located at the bottom of the lower annular rotor 54, the upper propeller 53 and the lower propeller 55 rotate in opposite directions, and their speed and direction can be adjusted independently. When the upper propeller 53 and the lower propeller 55 rotate at the same speed but in opposite directions, the anti-torque forces can cancel each other out, ensuring that the fuselage as a whole will not spin, resulting in stable flight and strong anti-interference capabilities. When the upper propeller 53 and the lower propeller 55 rotate at different speeds, they generate pitch or roll torque to assist in attitude control. By controlling the independent start and stop of the upper propeller 53 and the lower propeller 55, special maneuvers and emergency attitude adjustments can be achieved.

[0027] In this embodiment, the upper propeller 53 is sleeved on the upper annular rotor 52 via the upper shaft ring 56, and the lower propeller 55 is sleeved on the lower annular rotor 54 via the lower shaft ring 57.

[0028] In this embodiment, both the upper shell cover 3 and the lower shell cover 4 have multiple equally spaced annularly distributed mounting holes on their outer peripheral annular walls. Each mounting hole contains a grid vector assembly, which includes an annular frame 6 and multiple grid blades 7. The annular frame 6 is fixedly installed within the mounting holes, and the grid blades 7 are rotatably installed within the annular frame 6. A micro servo motor is installed and fixed within the annular frame 6. The micro servo motor is used to synchronously adjust the tilt angle of the multiple grid blades 7. The tilt angle of the grid blades 7 is adjustable from 0° to 90°. By adjusting the tilt angle of the grid blades 7, [the following can be observed / represented]... It guides the airflow direction to achieve precise attitude and heading control; the grille blades 7 of each grille vector assembly can independently control the opening and closing angle and airflow direction. In the vertical direction, by adjusting the vertical airflow volume, it can assist in controlling the total lift. In the horizontal direction, by guiding the airflow to spray forward, backward, left and right, it can achieve pure airflow vector thrust and complete omnidirectional maneuvers such as pitch, roll, and yaw. By cooperating with the differential control of the upper propeller 53 and the lower propeller 55, it can form dual vector control, realize omnidirectional maneuvering and precise attitude control without rudder surfaces, tail rotor, and tilt mechanism, and improve control accuracy and response speed.

[0029] In this embodiment, the upper outer shell 1, lower outer shell 2, upper shell cover 3, lower shell cover 4, and grid blades 7 are all made of radar-absorbing and heat-insulating composite materials to improve stealth performance. By designing a disc-shaped stealth shell composed of the upper outer shell 1 and the lower outer shell 2, the overall appearance of the aircraft is saucer-shaped, with a naturally low radar cross-section, which can effectively scatter radar waves. Furthermore, the disc-shaped sandwich shell and the double-layer external rotor motor propeller mechanism 5 are completely enclosed inside the disc-shaped stealth shell, with no exposed rotating parts, which greatly reduces radar reflection sources. The disc-shaped stealth shell made of radar-absorbing and heat-insulating composite materials can concentrate the heat source generated by the double-layer external rotor motor propeller mechanism 5 inside the disc-shaped stealth shell, reducing infrared signal characteristics. This ensures that the aircraft as a whole forms a dual natural stealth effect of radar stealth and infrared stealth, which can further improve radar stealth performance.

[0030] In this embodiment, both the upper annular rotor 52 and the lower annular rotor 54 are made of carbon fiber reinforced plastic to reduce rotational inertia and centrifugal force. Neodymium iron boron magnets are attached to the inner walls of both the upper annular rotor 52 and the lower annular rotor 54.

[0031] In this embodiment, both the upper propeller 53 and the lower propeller 55 are made of carbon fiber to ensure structural strength under high-speed rotation.

[0032] With the above structure, the external rotor motor aircraft provided in this application, when in use, utilizes the centrally fixed stator 51 as the stationary base of the entire aircraft, and arranges three-phase windings on the outer periphery to form an annular electromagnetic drive surface. The upper annular rotor 52 and lower annular rotor 54 are designed with neodymium iron boron magnets bonded to their inner walls, forming two independent external rotor motor structures. The flight control system is equipped with dual independent ESCs that supply alternating three-phase current to the stator windings. The alternating magnetic field drives the upper annular rotor 52 and lower annular rotor 54 to rotate independently around the centrally fixed stator 51, causing the upper propeller 53 and lower propeller 55 to rotate synchronously, cutting the air and generating a continuous downward airflow. The airflow passes through the annular channel inside the disc-shaped sandwich shell and is discharged outwards and downwards from the outer periphery grid vector assembly. The air reaction force forms a vertically upward total lift. The flight control system synchronously increases or decreases the speed of the upper annular rotor 52 and lower annular rotor 54, and the total lift increases or decreases synchronously, enabling the aircraft to take off vertically, hover, and descend. When the aircraft needs to hover and stabilize, the flight control system... The upper annular rotor 52 and lower annular rotor 54 are controlled to rotate at the same speed but in opposite directions. The opposing torques generated by the rotation of the upper propeller 53 and lower propeller 55 are equal in magnitude and opposite in direction, and the torques cancel each other out. The whole aircraft has no tendency to spin, and the hovering attitude is stable, without the need for tail rotor balancing torque. When the aircraft needs coarse attitude adjustment (pitch or roll), upon receiving forward / backward or left / right maneuver commands, the flight control system performs differential speed control on the upper annular rotor 52 and lower annular rotor 54, causing one of the upper annular rotors 52 and the lower annular rotor 54 to increase its speed and the other to decrease its speed. The difference in the opposing torque generated by the upper propeller 53 and the lower propeller 55 creates an unbalanced torque around the transverse and longitudinal axes of the fuselage, which drives the fuselage to complete pitch and roll movements, thus completing coarse attitude adjustment. When the aircraft needs to perform emergency special maneuvers, the flight control system can start or stop either the upper annular rotor 52 or the lower annular rotor 54 independently, relying on the lift and torque of a single rotor to achieve special attitude correction and emergency trim for faults.

[0033] By controlling the tilt angle of the grille blades 7 of each group of grille vector components from 0° to 90° via built-in micro servo motors, the airflow output downwards from the upper propeller 53 and lower propeller 55 passes through the gaps between the grille blades 7 in each annular frame 6 and is discharged outwards. By changing the tilt angle of the grille blades 7 via the servo motors, the direction of airflow can be changed, achieving precise aerodynamic vector control. When performing total lift auxiliary adjustment, all grille blades 7 are adjusted to retract synchronously, reducing the airflow area, increasing the static pressure of the airflow inside the disc-shaped sandwich shell, and thus increasing the vertical lift of the entire aircraft. A slight increase in lift is achieved by adjusting all the grid blades 7 to open simultaneously, increasing the airflow and decreasing the lift. This is combined with the dual adjustment of the speeds of the upper and lower annular rotors 52 and 54 for both lift and drop. When performing fine corrections for horizontal maneuvers, the front grid blade 7 is tilted forward by controlling it individually, causing the airflow to be ejected backward and generating forward horizontal thrust, propelling the aircraft forward. Similarly, by controlling the deflection of a single grid blade, the airflow is ejected to the opposite side, allowing the aircraft to roll and translate laterally. Adjusting the two diagonally opposite sets of grid blades 7 to deflect in opposite directions creates a couple, causing the aircraft to yaw and turn in place.

[0034] Furthermore, the upper annular rotor 52 and the lower annular rotor 54 are used for differential control to make large-scale coarse attitude adjustments to cope with strong winds and large-scale maneuvers. The partitioned grid airflow vector is used to make small attitude corrections and fixed-point hovering anti-shake. With the combined effect of the two, six-degree-of-freedom omnidirectional flight can be completed without control surfaces and tilting mechanisms.

[0035] By employing a disc-shaped stealth shell formed by the interlocking of the upper shell 1 and the lower shell 2, the smooth disc shape and curved surface of the disc can scatter radar electromagnetic waves, significantly reducing the radar cross-section. The disc-shaped sandwich shell and the double-layer external rotor motor propeller mechanism 5 are completely enclosed inside the disc-shaped sandwich shell, with no exposed metal rotating parts, thus eliminating strong radar reflection sources. The upper shell 1, lower shell 2, and grid blades 7 are all made of wave-absorbing and heat-insulating composite materials, which can absorb incident radar waves and further reduce echo signals. The heat sources generated by motor operation and battery operation are all concentrated inside the hollow central fixed stator 51. The disc-shaped sandwich shell and the disc-shaped stealth shell are insulated from the internal heat by heat-insulating composite materials, preventing high-temperature heat sources from directly radiating infrared signals to the outside, ensuring that the entire aircraft has no exposed high-temperature components, significantly compressing infrared detection features, and improving radar stealth performance.

[0036] The foregoing has provided a detailed description of an external rotor motor aircraft provided in this application. Specific embodiments have been used to illustrate the principles and implementation methods of this application. The descriptions of these embodiments are merely for the purpose of helping to understand the method and core ideas of this application. It should be noted that those skilled in the art can make various improvements and modifications to this application without departing from its principles, and these improvements and modifications also fall within the protection scope of the claims of this application.

Claims

1. An external rotor motor aircraft, characterized in that, include: A disc-shaped stealth shell, comprising an upper shell (1) and a lower shell (2), wherein the upper shell (1) and the lower shell (2) are fastened together and fixed. A disc-shaped sandwich shell is located inside the disc-shaped stealth shell. The disc-shaped sandwich shell includes an upper shell cover (3) and a lower shell cover (4), which are fastened together. The double-layer external rotor motor propeller mechanism (5) is located between the upper shell cover (3) and the lower shell cover (4). The double-layer external rotor motor propeller mechanism (5) includes a central fixed stator (51) and two sets of independent rotating rotor assemblies. The top and bottom of the central fixed stator (51) are fixedly connected to the upper shell cover (3) and the lower shell cover (4) respectively. The two sets of independent rotating rotor assemblies are sleeved on the central fixed stator (51).

2. The external rotor motor aircraft according to claim 1, characterized in that, The dual-set independent rotating rotor assembly includes: The upper annular rotor (52) is rotatably mounted on top of the central fixed stator (51); An upper propeller (53) is disposed on top of the upper annular rotor (52); The lower annular rotor (54) is rotatably sleeved at the bottom of the central fixed stator (51), and the upper annular rotor (52) and the lower annular rotor (54) are each independently electromagnetically driven; The lower propeller (55) is disposed at the bottom of the lower annular rotor (54), and the upper propeller (53) and the lower propeller (55) rotate in opposite directions.

3. The external rotor motor aircraft according to claim 2, characterized in that, The upper propeller (53) is sleeved on the upper annular rotor (52) through the upper shaft ring (56), and the lower propeller (55) is sleeved on the lower annular rotor (54) through the lower shaft ring (57).

4. The external rotor motor aircraft according to claim 1, characterized in that, The outer annular wall of the upper shell cover (3) and the lower shell cover (4) are provided with a plurality of equally spaced annularly distributed assembly holes. Each of the plurality of assembly holes is provided with a grid vector assembly. The grid vector assembly includes an annular frame (6) and a plurality of grid blades (7). The annular frame (6) is fixedly installed in the assembly hole. The grid blades (7) are rotatably installed in the annular frame (6). A micro servo motor is installed and fixed in the annular frame (6). The micro servo motor is used to synchronously adjust the tilt angle of the plurality of grid blades (7).

5. An external rotor motor aircraft according to claim 4, characterized in that, The upper shell (1), the lower shell (2), and the grille blades (7) are all made of wave-absorbing and heat-insulating composite materials.

6. An external rotor motor aircraft according to claim 2, characterized in that, Both the upper annular rotor (52) and the lower annular rotor (54) are made of carbon fiber reinforced plastic material, and neodymium iron boron magnets are attached to the inner walls of both the upper annular rotor (52) and the lower annular rotor (54).

7. An external rotor motor aircraft according to claim 2, characterized in that, Both the upper propeller (53) and the lower propeller (55) are made of carbon fiber.

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