A ducted lifting body and ducted aircraft

Abstract

The present application relates to the field of unmanned aerial vehicle, specifically relates to a ducted lift body and ducted aircraft, the ducted lift body includes rotor and duct shell, rotor is positioned in the duct of duct shell through support frame, the central axis of rotor coincides with the center line of duct, motor is fixed on support frame, the rotor of motor is fixedly connected with the central axis of rotor, when the rotor blade of rotor rotates, the duct shell will rotate in the opposite direction, the rotor blade of the present application and the rapid rotation of the ducted lift body have gyroscopic effect, can effectively offset the vibration of the ducted aircraft, can provide stable torque when encountering gust, so as to improve the stability and environmental adaptability of the ducted lift body.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of unmanned aerial vehicles, in particular to a ducted lifting body and a ducted aircraft. BACKGROUND

[0002] The conventional single-duct rotor aircraft only has the motor and propeller rotating in the rotating plane, the duct body is not moving, the moment of inertia is small, and the stability is poor; the duct body has a large windward area, and in the environment with side wind, it is subjected to a large wind resistance, and a large electric power is required to generate a force to offset the wind resistance; when encountering side wind and gust, it cannot provide a large stable torque, and the aircraft vibrates greatly. SUMMARY

[0003] The present application aims to overcome the defects of the prior art, and provides a ducted lifting body, the ducted lifting body and the rotor rotate in opposite directions, the moment of inertia is large, and a large stable torque can be provided, thereby increasing the stability of the unmanned aerial vehicle and significantly reducing the vibration of the unmanned aerial vehicle when encountering side wind and gust.

[0004] The technical solution of the present application is: a ducted lifting body, comprising a rotor and a duct shell, the rotor is positioned in the duct of the duct shell through a support frame, the center axis of the rotor is coincident with the center line of the duct, the motor is fixed on the support frame, the rotor of the motor is fixedly connected with the center axis of the rotor, when the rotor blades of the rotor rotate, the duct shell rotates in the opposite direction.

[0005] Further, the cross section of the duct shell is airfoil-shaped.

[0006] Further, it further comprises a fixed wing, the fixed wing is fixed on the outer surface of the duct shell, and the fixed wing is symmetrically arranged around the center line of the duct shell.

[0007] Further, the fixed wing is a flexible wing.

[0008] Further, the outer surface skin of the fixed wing is a flexible material; a high-strength tensile rope is arranged in the fixed wing and fixed with the ducted lifting body.

[0009] Further, the outer surface skin of the fixed wing is one of rubber, polyvinyl acetate, polyvinyl chloride and silicone.

[0010] Further, the high-strength tensile rope is one of nylon rope, high-molecular polyethylene fiber rope and steel wire.

[0011] On the other hand, a ducted aircraft comprises the above-mentioned ducted lifting body.

[0012] Further, the ducted aircraft is a tethered aircraft.

[0013] The present application has the following beneficial effects: when the rotor blades rotate, an opposite torque is generated to act on the ducted lifting body of the ducted aircraft, the ducted lifting body of the ducted aircraft rotates under the action of the opposite torque, the ducted lifting body has a smaller windward area than other multi-rotor unmanned aerial vehicles under the same total weight and has a smaller cross-sectional resistance due to the similar airfoil, so that the energy consumption can be effectively reduced; the rapid rotation of the rotor blades of the ducted lifting body and the ducted lifting body has a gyro effect, which can effectively offset the vibration of the ducted lifting body and provide a stable torque when encountering a gust, thereby improving the stability and environmental adaptability of the ducted lifting body; the ducted lifting body is an airfoil disc, which can generate additional lift under the action of the crosswind, thereby reducing the energy consumption of the unmanned aerial vehicle; the fixed wing is a flexible wing, which will deform under the action of the crosswind, thereby reducing the interference of the crosswind on the unmanned aerial vehicle and increasing the stability of the unmanned aerial vehicle; when encountering a gust, the flexible wing can deform, reducing the interference of the gust on the unmanned aerial vehicle and further increasing the stability of the unmanned aerial vehicle. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 is a three-dimensional schematic view of the ducted aircraft of the present application.

[0015] Figure 2 is a partial sectional view of the ducted lifting body.

[0016] Figure 3 is a sectional view of the fixed wing of the present application.

[0017] Among them, the above drawings include the following reference signs: 1, rotor; 2, support frame; 3, duct shell; 4, fixed wing; 5, motor. DETAILED DESCRIPTION

[0018] The technical solutions of the present application will be described clearly and completely below in conjunction with the drawings, obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor belong to the scope of protection of the present application.

[0019] In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, therefore it cannot be understood as a limitation on the present application. In addition, the terms "first", "second", "third" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance.

[0020] In the description of the present application, it should be noted that unless otherwise expressly specified and limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or integrally connected; it can be mechanical connection, or electrical connection; it can be directly connected, or indirectly connected through intermediate medium, or the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0021] As shown in Figure 1 A ducted lift body, comprising a rotor 1 and a duct shell 3, the rotor 1 is positioned in the duct of the duct shell 3 through a support frame 2, the central axis of the rotor 1 coincides with the center line of the duct, when the rotor blades of the rotor 1 rotate, the duct shell 3 will rotate in the opposite direction; a motor 5 is fixed on the support frame 2, the rotor of the motor 5 is fixedly connected with the central axis of the rotor 1.

[0022] The rotor is arranged in the duct shell 3, which can suppress the wing tip disturbance and reduce the rotor rotation resistance; when the rotor blades of the rotor 1 rotate, an opposite torque will act on the duct shell 3, the duct shell 3 will rotate under the action of the opposite torque, when there is crosswind, the duct shell 3 has smaller windward area and smaller cross-sectional resistance due to similar wing type than other multi-rotor unmanned aerial vehicles under the same total weight, which can effectively reduce energy consumption; the rapid rotation of the rotor blades and the duct shell 3 has gyroscopic effect, which can effectively offset the vibration of the ducted aircraft, and can provide stable torque when encountering gust, thereby improving the stability and environmental adaptability of the ducted aircraft.

[0023] The cross section of the duct shell 3 is wing type, the leading edge radius is between 10%-20% of the chord length, the duct inlet is a continuous smooth curved surface, which can generate additional lift under the action of crosswind, thereby reducing the energy consumption of the unmanned aerial vehicle.

[0024] The ducted lift body further comprises a fixed wing 4, which is fixed on the outer surface of the duct shell 3, the fixed wing is arranged symmetrically around the center line of the duct shell, and the fixed wing 4 rotates with the duct shell 3, thereby providing additional lift.

[0025] The fixed wing 4 is a flexible wing, and when there is crosswind, the up-and-down waving of the rigid wing will cause the whole machine vibration of the ducted aircraft; when encountering gust, the sudden increase of lift on the rigid wing will immediately act on the unmanned aerial vehicle body, which will cause the unmanned aerial vehicle to vibrate or even lose stability. The fixed wing 4 is a flexible wing, which will deform under the action of crosswind, thereby reducing the interference of crosswind on the unmanned aerial vehicle and increasing the stability of the unmanned aerial vehicle; when encountering gust, the flexible wing can deform, thereby reducing the interference of gust on the unmanned aerial vehicle and further increasing the stability of the unmanned aerial vehicle.

[0026] The outer surface skin of the fixed wing 4 is made of flexible materials such as rubber, polyurethane, polyvinyl chloride or silicone.

[0027] The high-strength tensile rope arranged in the fixed wing 4 is fixed with the duct shell 3 and is used for bearing the centrifugal force of the paddle of the fixed wing 4, and the material can be nylon, high-molecular polyethylene fiber rope, steel wire and the like.

[0028] The above embodiment is the preferred embodiment of the present application, but the embodiment of the present application is not limited by the above embodiment, and any change, modification, replacement, combination, simplification made without departing from the spirit and principle of the present application should be an equivalent replacement mode, which is included in the protection scope of the present application.

Claims

1. A ducted lifting body, comprising a rotor and a duct shell, wherein the rotor is positioned within the duct of the duct shell by a support frame, the central axis of the rotor coincides with the center line of the duct, a motor is fixed on the support frame, and the rotor of the motor is fixedly connected to the central axis of the rotor, characterized in that: When the rotor blades rotate, the duct shell rotates in the opposite direction; the cross-section of the duct shell is airfoil; it also includes a fixed wing, which is fixed to the outer surface of the duct shell and is symmetrically arranged around the center line of the duct shell; the fixed wing is a flexible wing; the outer surface skin of the fixed wing is made of flexible material; high-strength tensile ropes are arranged inside the fixed wing and fixed together with the duct shell.

2. The ducted lifting body according to claim 1, characterized in that: The outer skin of the fixed wing is made of one of the following materials: rubber, polyurethane, polyvinyl chloride, or silicone.

3. The ducted lifting body according to claim 1, characterized in that: The high-strength tensile rope is a type of nylon rope, high molecular weight polyethylene fiber rope, or steel wire.

4. A ducted jet aircraft, characterized in that, Includes the ducted lifting body as described in any one of claims 1-3.

5. A ducted jet aircraft according to claim 4, characterized in that: The ducted aircraft is a tethered aircraft.

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