A saucer-shaped ducted aircraft driven by electromagnetic force

Abstract

The application relates to the field of aviation technology, in particular to a disc-shaped ducted aircraft driven by electromagnetic force, which comprises a static fuselage, an upper rotating fuselage and a lower rotating fuselage. The static fuselage comprises an inner static fuselage, the outer side of the inner static fuselage is sleeved with an outer static fuselage, and a plurality of connecting rods are connected between the inner static fuselage and the outer static fuselage. The upper rotating fuselage and the lower rotating fuselage are rotationally arranged between the inner static fuselage and the outer static fuselage. The upper rotating fuselage and the lower rotating fuselage each comprise an inner rotating fuselage and an outer rotating fuselage. The application has higher energy utilization efficiency, better aerodynamic efficiency, greater structural strength and simpler structure through the unique design of arranging an electromagnetic coil group outside the outer rotating fuselage and fixing the blade tip and the blade root, so that the aircraft has higher cruising speed and longer cruising time under the same structural weight.

Description

Technical Field

[0001] This invention relates to the field of aviation technology, and in particular to a disc-shaped ducted aircraft driven by electromagnetic force. Background Technology

[0002] Currently, my country's efforts to promote low-carbon emissions and protect the green environment have created an urgent demand for aviation equipment, primarily civil aircraft. However, the current technological development in this field faces the following limitations: existing new energy civil aircraft still mainly use traditional turbine engine or electric motor drive modes, and the main innovations are focused on replacing traditional fuel, resulting in problems such as low power, complex power transmission systems, and low flight speed; in terms of aircraft configuration, current aircraft configurations still mainly adopt the two modes of traditional fixed-wing aircraft design and rotary-wing helicopter design.

[0003] However, both modes, whether it is a long-span flat wing or a slender helicopter rotor, are cantilever thin-walled beam structures with one end fixed and the other free. The large deformation and concentrated high load in the connection area at the root of the structure, which are unique to this configuration, severely restrict the improvement of aerodynamic and structural design efficiency, as well as the inability to make good attitude control adjustments during flight. Summary of the Invention

[0004] In view of this, the purpose of this invention is to propose a disc-shaped ducted aircraft driven by electromagnetic force, in order to solve the problems of complex power systems, severe profit concentration at the blades or wing roots, and inability to change the blade installation angle, which leads to the inability to change the flight direction of the aircraft.

[0005] To achieve the above objectives, the present invention provides a disc-shaped ducted aircraft driven by electromagnetic force, comprising a stationary fuselage, an upper rotating fuselage, and a lower rotating fuselage;

[0006] The stationary fuselage includes an inner stationary fuselage, an outer stationary fuselage is fitted around the outer side of the inner stationary fuselage, and a number of connecting rods connect the inner stationary fuselage and the outer stationary fuselage.

[0007] The upper and lower rotating bodies are rotatably positioned between the inner and outer stationary bodies. Each of the upper and lower rotating bodies includes an inner rotating body and an outer rotating body. Several blades are installed between the inner and outer rotating bodies. Each blade has a pitch actuator installed at its root. Electromagnetic coil groups are installed inside both the upper and lower rotating bodies. With the cooperation of the two electromagnetic coil groups, the upper and lower rotating bodies can be driven to rotate around the inner stationary body, and the rotation directions of the upper and lower rotating bodies are opposite.

[0008] Preferably, the inner stationary fuselage is a cylindrical shell structure, with airflow shrouds fixedly installed at its top and bottom, and the outer stationary fuselage has a conical cross-section.

[0009] Preferably, the inner rotating body is rotatably connected to the inner stationary body via a rotating bearing, and the outer rotating body is rotatably connected to the outer stationary body via a ball bearing assembly and a roller assembly.

[0010] Preferably, the blades in the upper rotating body and the blades in the lower rotating body twist in opposite directions.

[0011] Preferably, the blade adopts the OA209 airfoil, the rotation radius at the blade root is 540mm, the rotation radius at the blade tip is 1250mm, the blade twist angle is 9°, and the blade chord length is 175mm.

[0012] Preferably, the electromagnetic coil assemblies in the upper and lower rotating bodies are installed inside the outer rotating body.

[0013] Preferably, the current flowing through the electromagnetic coil group in the upper rotating body and the electromagnetic coil group in the lower rotating body flows in opposite directions.

[0014] The beneficial effects of this invention are as follows:

[0015] First, it possesses excellent structural strength performance. By fixing both ends of the blade, the blade stiffness can be greatly improved, thereby reducing the amplitude of vibration and fatigue damage; at the same time, it greatly reduces stress concentration at the blade root. This improves the reliability of the structure and allows for weight reduction while maintaining the same level of safety.

[0016] Second, it has excellent aerodynamic design efficiency. The blades fixed at both ends and the duct are seamless, which can greatly reduce the blade tip induced drag that is common and accounts for a large proportion in rotorcraft. In addition, the upper and lower fuselages rotate in opposite directions, which can cancel each other out the rotational torque, so the stationary fuselage will not rotate.

[0017] Third, it has excellent electromagnetic drive power and efficiency. The electromagnetic coil group that generates rotational torque is arranged on the outer ring of the rotating structure, which greatly increases the lever arm of the electromagnetic force and greatly increases the rotational drive torque that can be generated by the same electromagnetic force. At the same time, since the electromagnetic coil directly drives the rotating fuselage and blades to rotate, it greatly simplifies the gear set and complex transmission mechanism required by the traditional rotor structure, thereby reducing the weight of the aircraft. In summary, the aircraft can have better energy utilization.

[0018] Fourth, it has excellent attitude control and adjustment. The computer adjusts the installation angle of each blade through the pitch actuator, thereby realizing the attitude control of the aircraft. Its control principle is basically the same as that of the basic attitude control of a helicopter. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, 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 embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the external overall structure of an embodiment of the present invention;

[0021] Figure 2 This is a schematic diagram of the stationary fuselage section and some rotating bearings according to an embodiment of the present invention;

[0022] Figure 3 This is a schematic diagram of the rotating fuselage and electromagnetic coil assembly according to an embodiment of the present invention;

[0023] Figure 4 This is a schematic diagram of the rotating fuselage and the outer stationary fuselage according to an embodiment of the present invention;

[0024] Figure 5 This is a schematic diagram of the rotating fuselage, blades, and pitch actuator in an embodiment of the present invention.

[0025] In the diagram: 1. Stationary body; 2. Upper rotating body; 3. Lower rotating body; 4. Rotary bearing; 5. Ball bearing assembly; 6. Electromagnetic coil assembly; 7. Inner rotating body; 8. Outer rotating body; 9. Blade; 10. Pitch actuator; 11. Inner stationary body; 12. Connecting rod; 13. Outer stationary body; 14. Roller assembly. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to specific embodiments and accompanying drawings.

[0027] It should be noted that, unless otherwise defined, the technical or scientific terms used in the embodiments of this invention should have the ordinary meaning understood by those skilled in the art to which this invention pertains. The terms "first," "second," and similar terms used in this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as "comprising" or "including" mean that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, without excluding other elements or objects. Terms such as "connected" or "linked" are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0028] like Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 As shown, a disc-shaped ducted aircraft driven by electromagnetic force includes a stationary fuselage 1, an upper rotating fuselage 2, and a lower rotating fuselage 3.

[0029] The stationary fuselage 1 includes an inner stationary fuselage 11, an outer stationary fuselage 13 is sleeved on the outside of the inner stationary fuselage 11, and a plurality of connecting rods 12 are connected between the inner stationary fuselage 11 and the outer stationary fuselage 13.

[0030] The upper rotating fuselage 2 and the lower rotating fuselage 3 are rotatably positioned between the inner stationary fuselage 11 and the outer stationary fuselage 13. Both the upper rotating fuselage 2 and the lower rotating fuselage 3 include an inner rotating fuselage 7 and an outer rotating fuselage 8. Several blades 9 are installed between the inner rotating fuselage 7 and the outer rotating fuselage 8. Each blade 9 has a pitch actuator 10 installed at its root. The computer adjusts the installation angle of each blade 9 through the pitch actuator 10, thereby achieving attitude control of the aircraft. Its control principle is basically the same as the basic attitude control of a helicopter. Electromagnetic coil groups 6 are installed inside both the upper rotating fuselage 2 and the lower rotating fuselage 3. With the cooperation of the two electromagnetic coil groups 6, the upper rotating fuselage 2 and the lower rotating fuselage 3 can be driven to rotate around the inner stationary fuselage 11, and the rotation directions of the upper rotating fuselage 2 and the lower rotating fuselage 3 are opposite.

[0031] By fixing both ends of the blade, the blade stiffness can be greatly improved, thereby reducing the amplitude of vibration and fatigue damage; at the same time, the stress concentration problem at the blade root is greatly reduced. This improves the reliability of the structure and allows for a reduction in the weight of the structure while maintaining the same level of safety.

[0032] The blades 9 are open at both ends and the side walls are sealed to form an airflow duct. The seamless connection between the blades 9 fixed at both ends and the duct can greatly reduce the blade tip induced drag, which is common and accounts for a large proportion of rotorcraft. Furthermore, the upper and lower fuselages rotate in opposite directions, which can cancel each other out the rotational torque, so the stationary fuselage will not rotate.

[0033] In a preferred embodiment of the present invention, the inner stationary fuselage 11 is a cylindrical shell structure with airflow shrouds fixedly installed at its top and bottom. The outer stationary fuselage 13 has a conical cross-section. While storing the effective payload (including control computer, mission payload, etc.), the airflow shroud can regulate the airflow, improve the intake efficiency, and reduce aerodynamic resistance. The outer stationary fuselage 13 can be used to store batteries and other working or mission payloads.

[0034] In another preferred embodiment of the present invention, the inner rotating body 7 is rotatably connected to the inner stationary body 11 via a rotating bearing 4, and the outer rotating body 8 is rotatably connected to the outer stationary body 13 via a ball assembly 5 and a roller assembly 14. The ball assembly 5 consists of a plurality of balls, and the roller assembly 14 consists of a plurality of rollers. The ball assembly 5 is used to transmit circumferential loads, while the roller assembly 14 is used to transmit radial loads.

[0035] In another preferred embodiment of the present invention, the blades 9 in the upper rotating body 2 and the blades 9 in the lower rotating body 3 have opposite twisting directions, so that although the upper rotating body 2 and the lower rotating body 3 rotate in opposite directions, the pulling force they generate is upward.

[0036] It should be noted that blade 9 adopts the OA209 airfoil. The rotation radius at the blade root of blade 9 is 540mm, the rotation radius at the blade tip is 1250mm, the blade twist angle is 9°, and the blade chord length is 175mm.

[0037] It should be noted that the electromagnetic coil group 6 inside the upper rotating body 2 and the lower rotating body 3 is installed inside the outer rotating body 8. A brush structure is designed between the rotating body and the stationary body, which allows the battery placed in the stationary body to continuously supply power to the electromagnetic coil.

[0038] The electromagnetic coil group 6 in the upper rotating fuselage 2 and the electromagnetic coil group 6 in the lower rotating fuselage 3 have opposite current flows. Because the current directions are different, the two sides of the coil are subjected to electromagnetic forces of the same magnitude but opposite directions. These two electromagnetic forces form an electromagnetic torque. Under the pull of the electromagnetic torque, the electromagnetic coil group 6 and the rotating fuselage will be driven to rotate. By changing the current flowing through the electromagnetic coil, the magnetic flux generated in the electromagnetic coil can be changed, thereby changing the electromagnetic torque generated by the coil group, ultimately increasing the rotor speed or overcoming greater aerodynamic drag.

[0039] Working principle: During flight, the battery located in the outer stationary fuselage 13 supplies power to the electromagnetic coil group 6 located in the outer rotating fuselage 8 through brushes. The electromagnetic torque generated by the coils continuously drives the upper rotating fuselage 2 and the lower rotating fuselage 3 to rotate in opposite directions. Since the blades 9 in the upper rotating fuselage 2 and the blades 9 in the lower rotating fuselage 3 twist in opposite directions, the rotating blades 9 all generate upward lift, overcoming the aircraft's gravity, thus achieving flight. Through the variable pitch actuator 10, the computer can adjust the installation angle of each blade 9. When all blades 9 are uniformly adjusted to the same installation angle, the same lift is generated on each blade 9, thereby enabling the aircraft to maneuver in the vertical direction. When the computer controls the blades 9 to change the blade installation angle when they rotate to a fixed angle, the blades 9 at the fixed angle will generate greater or less lift. The lateral torque generated on the rotating surface will cause the aircraft to tilt, thus changing the direction of the aircraft's lift. The lift will generate a lateral component parallel to the ground, and under the impetus of this component, the aircraft can achieve horizontal maneuvering.

[0040] Those skilled in the art should understand that the discussion of any of the above embodiments is merely exemplary and is not intended to imply that the scope of the invention is limited to these examples; within the framework of the invention, the technical features of the above embodiments or different embodiments can also be combined, the steps can be implemented in any order, and there are many other variations of the different aspects of the invention as described above, which are not provided in detail for the sake of brevity.

[0041] The embodiments of this invention are intended to cover all such substitutions, modifications, and variations falling within the broad scope of the appended claims. Therefore, any omissions, modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A disc-shaped ducted aircraft driven by electromagnetic force, characterized in that, It includes a stationary fuselage (1), an upper rotating fuselage (2), and a lower rotating fuselage (3); The stationary fuselage (1) includes an inner stationary fuselage (11), an outer stationary fuselage (13) is sleeved on the outside of the inner stationary fuselage (11), and a plurality of connecting rods (12) are connected between the inner stationary fuselage (11) and the outer stationary fuselage (13). The upper rotating body (2) and the lower rotating body (3) are rotatably disposed between the inner stationary body (11) and the outer stationary body (13). Both the upper rotating body (2) and the lower rotating body (3) include an inner rotating body (7) and an outer rotating body (8). The inner rotating body (7) is rotatably connected to the inner stationary body (11) through a rotating bearing (4). The outer rotating body (8) is rotatably connected to the outer stationary body (13) through a ball bearing assembly (5) and a roller assembly (14). Several blades (9) are installed between the inner rotating body (7) and the outer rotating body (8). Each blade (9) has a blade root with A variable pitch actuator (10) is installed, which is controlled by a computer. It is used to change the installation angle of the blade (9) when the blade (9) rotates to a fixed angle, so as to generate a tilting torque on the rotating surface to push the aircraft to tilt, so as to realize the horizontal maneuver of the aircraft. Electromagnetic coil groups (6) are installed in both the upper rotating fuselage (2) and the lower rotating fuselage (3). With the cooperation of the two electromagnetic coil groups (6), the upper rotating fuselage (2) and the lower rotating fuselage (3) can be driven to rotate around the inner stationary fuselage (11), and the rotation directions of the upper rotating fuselage (2) and the lower rotating fuselage (3) are opposite.

2. The disc-shaped ducted aircraft driven by electromagnetic force according to claim 1, characterized in that, The inner stationary fuselage (11) is a cylindrical shell structure, with airflow shrouds fixedly installed at its top and bottom, and the outer stationary fuselage (13) has a conical cross-section.

3. A disc-shaped ducted aircraft driven by electromagnetic force according to claim 1, characterized in that, The blades (9) in the upper rotating body (2) and the blades (9) in the lower rotating body (3) have opposite twisting directions.

4. A disc-shaped ducted aircraft driven by electromagnetic force according to claim 1, characterized in that, The blade (9) adopts the OA209 airfoil, the rotation radius at the blade root is 540mm, the rotation radius at the blade tip is 1250mm, the blade twist angle is 9°, and the blade chord length is 175mm.

5. A disc-shaped ducted aircraft driven by electromagnetic force according to claim 1, characterized in that, The electromagnetic coil assembly (6) in the upper rotating body (2) and the lower rotating body (3) is installed in the outer rotating body (8).

6. A disc-shaped ducted aircraft driven by electromagnetic force according to claim 5, characterized in that, The current flowing through the electromagnetic coil group (6) in the upper rotating body (2) and the electromagnetic coil group (6) in the lower rotating body (3) are in opposite directions.

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