Large-windward-area high-energy-efficiency impeller continuous driving unmanned aerial vehicle

Abstract

The invention discloses a large-windward-area and high-energy-efficiency impeller continuous driving unmanned aerial vehicle which is characterized by comprising a fuselage frame, a wind shield, a rotary impeller, an empennage frame, a vertical tail rotor, a horizontal tail rotor and an unmanned aerial vehicle undercarriage, the wind shield and the rotary impeller form a rotary wing, and the rotary impeller rotates in the wind shield; the unmanned aerial vehicle can generate lifting force in the vertical direction and propelling force in the horizontal direction, the four rotary wings are arranged on the fuselage frame in an isosceles trapezoid shape and provide lifting force and propelling force for the unmanned aerial vehicle, the empennage frame is installed at the tail of the unmanned aerial vehicle, and the vertical tail rotor and the horizontal tail rotor are installed at the upper end and the lower end of the tail of the empennage frame of the unmanned aerial vehicle correspondingly. The method is used for controlling the flight direction of the UAV and maintaining flight balance of the UAV. The two unmanned aerial vehicle undercarriages are symmetrically installed at the bottom of the fuselage frame and used for supporting the unmanned aerial vehicle on the ground.

Description

Technical Field

[0001] This invention relates to the field of rotary-wing aircraft and flying robots, and in particular to a high-efficiency impeller-driven unmanned aerial vehicle with a large frontal area. Background Technology

[0002] There are three types of flight modes for aircraft: fixed-wing, rotor, and flapping-wing. Both rotor and flapping-wing are movable wings.

[0003] Flapping-wing flight is a mode of flight employed by flying organisms in nature. It primarily utilizes the up-and-down flapping of the wings to generate lift and thrust simultaneously. Its main characteristic is the integration of lift, hovering, and propulsion functions, resulting in strong maneuverability and flexibility, making it particularly suitable for maneuvering around obstacles. For small-sized aircraft flying at low speeds, operating at low Reynolds numbers, the unsteady lift generated by flapping wings is significantly greater than the steady lift of fixed-wing aircraft; in terms of thrust, flapping wings are more efficient than propellers. Current research on flapping-wing aircraft mainly focuses on designing various flapping-wing mechanisms to simulate the flight attitudes of flying organisms in nature. However, a common problem with these flapping-wing mechanisms is their relatively low overall aerodynamic efficiency, even lower than that of similarly sized fixed-wing micro-aircraft. The main reason for the low overall efficiency of flapping-wing aircraft is that most current research simply imitates the shape and flapping motion of bird or insect wings, but it is difficult to realize the use of changes in the attitude and structure of the wings themselves to reduce air resistance and generate unsteady aerodynamic forces during the flapping motion of flying organisms. The resulting low aerodynamic efficiency seriously restricts the widespread application of flapping-wing aircraft.

[0004] Rotorcraft flight utilizes the thrust of its rotor (including propellers) to provide lift. The forward thrust originates from the horizontal component generated by a small-angle deflection of the rotor vector. Currently, the attitude control and horizontal movement of rapidly developing multi-rotor small aircraft are achieved through the differential thrust of the multi-rotors. Rotorcraft are characterized by vertical takeoff and landing (VTOL) and hovering capabilities, and the ability to fly over relatively small areas. However, due to the relatively low aerodynamic efficiency of rotors, high-power, long-endurance flight is challenging. Summary of the Invention

[0005] The purpose of this invention is to provide a high-efficiency continuously driven UAV with a large windward area that significantly improves aerodynamic efficiency, facilitates vertical take-off and landing, enables rapid switching of flight direction, and has excellent flight flexibility and maneuverability, in order to solve the problem of low aerodynamic efficiency in the prior art.

[0006] The technical solution to achieve the purpose of this invention is: A high-efficiency, large-frontal-area, continuously driven unmanned aerial vehicle (UAV) with turbine propulsion is characterized by comprising a fuselage frame, a wind deflector, rotating impellers, a tail fin frame, a vertical tail rotor, a horizontal tail rotor, and UAV landing gear. Four horizontally rotating impellers are symmetrically arranged in two rows on both sides of the fuselage frame, forming an isosceles trapezoidal shape. Each impeller is equipped with a wind deflector coaxial with the impeller and mounted on the fuselage frame. The tail fin frame is mounted at the rear of the fuselage frame, and the vertical tail rotor is mounted at the upper end of the tail fin frame. The vertical tail rotor's rotation axis is parallel to the rotation axis of the rotating impellers and is used to control the UAV's flight direction. The horizontal tail rotor is mounted at the lower end of the tail fin frame. The horizontal tail rotor's rotation axis is perpendicular to the ground and also perpendicular to the vertical tail rotor's rotation axis, used to stabilize the UAV's flight attitude. The UAV landing gear is symmetrically mounted at the bottom of the fuselage frame. The fuselage frame is symmetrically equipped with a rear mounting arm and a front mounting arm for the rotor, with the length of the rear mounting arm being equal to the radial width of the wind deflector compared to the front mounting arm. A tail fin frame mounting slot is provided at the rear of the fuselage frame, near the end of the rear mounting arm, for mounting the tail fin frame. Four landing gear mounting holes are provided at the bottom of the fuselage frame for mounting two UAV landing gears. Wind deflector mounting holes and motor mounting slots are provided at the ends of the two rear mounting arms and the two front mounting arms, for mounting the wind deflector and the rotary motor on the rotor impeller, respectively. The power unit includes a windshield and a rotating impeller; the windshield includes a windshield plate, a windshield frame, bearings, a windshield surface, a windshield frame, and mounting holes; the rotating impeller includes a rotating motor, a rotating shaft, bearing holes, a blade frame, and blades; the windshield plate is a 180-degree arc-shaped plate fixed to the windshield frame, the inner ring of the bearing is fixed to the windshield surface, and the outer ring of the bearing is fixed in the bearing hole, providing support for the windshield. Windshield surfaces are symmetrically installed on both sides of the windshield plate, and the windshield frame is fixed to the windshield frame. The windshield frame is equipped with... Four mounting holes coincide with the windshield mounting holes. The rotary motor is installed in the motor mounting slot, and the rotating shaft is fixed to the rotary motor and coincides with the axis of the rotary motor. A bearing hole is provided at the end of the rotating shaft for fixing the bearing. Multiple sets of blades are fixed on the rotating shaft. Each set of blades includes two blades arranged axially. The blades within the set are parallel to each other. Multiple sets of blades are arranged circumferentially on the rotating shaft. The included angle between adjacent sets of blades is equal. For example, when the number of blades in multiple sets of blades is designed to be 6, the included angle between two sets of blades is 60 degrees. The vertical tail rotor includes a tail rotor frame, a propeller, and a tail rotor motor. The tail rotor motor is fixed to the upper end of the tail rotor frame, the propeller is mounted on the tail rotor motor, and the tail rotor frame is fixed to the housing of the tail rotor motor to provide protection for the tail rotor. The horizontal tail rotor includes horizontal blades and a propeller motor. The propeller motor is fixed to the lower end of the tail rotor frame, and the horizontal blades are fixed to the rotating shaft of the propeller motor.The wind deflector and its surrounding windproof surface form a semi-circular arc-shaped opening space. When the rotating impeller rotates, it pushes the airflow at the opening space to generate a reaction force, thereby providing lift and thrust for the drone. The angle between the normal vector of the opening space plane and the vertical plane containing the axis of the rotating impeller is 30 degrees. When the wind deflector is installed, the opening space of the wind deflector installed on the rear mounting arm faces the rear of the drone; the opening space of the wind deflector installed on the front mounting arm faces the front of the drone.

[0007] The working principle of this invention is as follows: A rotating motor on a rotating impeller drives a rotating shaft to rotate, simultaneously causing multiple blades mounted on the shaft to rotate within a windshield. As the impeller rotates within the windshield, the blade surface experiences a counter-thrust force from the air. This counter-thrust force is perpendicular to the blade surface and opposite to the direction of blade movement. When the rotating blades move within the windshield, the windshield's shielding surface, the side shields, and the blades together form a nearly closed area. Therefore, the blades within this area do not push air out of the windshield. When the blades move within the opening of the windshield, since there is no obstruction in front of them, they can experience a counter-thrust force from the air. When the blades rotate from a high position to a low position, due to the lack of vertical obstruction from the windshield, the blades as a whole experience upward lift and horizontal thrust. When the blades return from a low position to a high position, since all blade movement occurs inside the windshield, overall, the blades inside the windshield do not generate lift or thrust. When the aircraft is in flight, the impeller of the front mounting arm of the rotor rotates counterclockwise, while the impeller of the rear mounting arm rotates clockwise. Since the openings of the wind deflectors on the front and rear mounting arms are in opposite directions, the horizontal thrust generated by the front and rear mounting arms cancels each other out. The aircraft as a whole experiences an upward lift force perpendicular to the ground. Furthermore, because the front and rear impellers rotate in opposite directions, the torques they generate are equal in magnitude and opposite in direction, thus the overall torque of the aircraft is balanced, allowing the aircraft to hover in the air. When the front and rear impellers rotate at different speeds, the horizontal thrust on the front and rear impellers cannot cancel each other out, allowing the aircraft to move forward and backward in the horizontal direction. At the same time, the horizontal and vertical tail rotors of the aircraft rotate to maintain the overall attitude balance of the aircraft. When the vertical tail rotor of the aircraft rotates alone, the aircraft can turn.

[0008] The significant advantages of this invention compared to existing technologies are: 1. The large windward area high-efficiency impeller continuously driven UAV of the present invention maintains the advantage of continuous rotor rotation by setting the blades in the wheeled rotor to rotate continuously, and overcomes the weakness of flapping wings requiring reciprocating motion.

[0009] 2. The large windward area high-efficiency impeller continuously driven UAV described in this invention retains the upward lift and horizontal thrust of the rotating impeller through the design of the wind deflector structure, and suppresses the force on the external air when the impeller returns to a high position, thereby improving aerodynamic efficiency. Its aerodynamic efficiency is much higher than that of existing flapping-wing and rotary-wing aircraft, and can provide greater lift and thrust for the aircraft.

[0010] 3. The large frontal area, high-efficiency impeller continuously driven UAV described in this invention uses four rotating impellers to control the magnitude of lift. Adjusting the rotation speed of the front and rear rotating impellers enables the UAV to move forward and backward in the horizontal direction. The vertical and horizontal tail rotors stabilize the attitude of the aircraft, thereby enabling vertical take-off and landing, hovering in the air, and rapid switching to any direction of flight. Therefore, this type of UAV has excellent flexibility and maneuverability and can be widely used in various small aircraft and UAVs flying at low Reynolds numbers.

[0011] 4. The large windward area, high-efficiency impeller continuously driven UAV described in this invention has a simple structure, good processability, and low production cost. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the overall structure of the large windward area high-efficiency impeller continuously driven UAV of the present invention; Figure 2 This is a top view of the overall structure of the large windward area high-efficiency impeller continuously driven UAV of the present invention; Figure 3 This is a partial schematic diagram of the overall structure of the large windward area high-efficiency impeller continuously driven UAV of the present invention; Figure 4 This is a partial schematic diagram of the fuselage frame of the large windward area high-efficiency impeller continuously driven UAV of the present invention; Figure 5 This is a schematic diagram of the tail fin of the large windward area high-efficiency impeller continuously driven UAV of the present invention; Figure 6 This is a schematic diagram of the rotating impeller structure of the large windward area high-efficiency impeller continuously driven UAV of the present invention; Figure 7 This is a schematic diagram of the windshield structure of the large windward area high-efficiency impeller continuously driven UAV of the present invention. Detailed Implementation

[0013] Combination Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7The large-frontal-area, high-efficiency impeller-driven UAV includes a fuselage frame 1, a windshield 2, a rotating impeller 3, a tail fin frame 4, a vertical tail rotor 5, a horizontal tail rotor 6, and a UAV landing gear 7. The fuselage frame 1 has four horizontally rotating impellers 3 arranged symmetrically in two rows on both sides. The four rotating impellers 3 are arranged in an isosceles trapezoidal shape on the fuselage frame 1. Each rotating impeller 3 is equipped with a wind shield 2. The wind shield 2 is coaxial with the rotating impeller 3 and is mounted on the fuselage frame 1. The fuselage frame 1 is symmetrically equipped with a rear mounting arm 101 and a front mounting arm 102 for rotating blades. The length of the rear mounting arm 101 is longer than that of the front mounting arm 102 by the radial width of the wind shield 2. The ends of the two rear mounting arms 101 and the two front mounting arms 102 are provided with wind shield mounting holes 105 and motor mounting slots 106, which are used to install the rotating motors 301 on the wind shield 2 and the rotating impellers 3, respectively. The power unit includes a windshield 2 and a rotating impeller 3. The windshield 2 includes a windshield plate 201, a windshield frame 202, a bearing 203, a windshield surface 204, a windshield frame 205, and mounting holes 206. The rotating impeller 3 includes a rotating motor 301, a rotating shaft 302, a bearing hole 303, a blade frame 304, and blades 305. The windshield plate 201 is a 180-degree arc-shaped plate fixed to the windshield frame 202. The inner ring of the bearing 203 is fixed to the windshield surface 204, and the outer ring of the bearing 203 is fixed in the bearing hole 303, providing support for the windshield 2. Windshield surfaces 204 are symmetrically installed on both sides of the windshield plate 201. The frame 205 is fixed to the windshield frame 202. The windshield frame 205 has four mounting holes 206 that coincide with the windshield mounting holes 105. The rotary motor 301 is installed in the motor mounting slot 106. The rotary shaft 302 is fixed on the rotary motor 301 and coincides with the axis of the rotary motor 301. The end of the rotary shaft is provided with a bearing hole 303 for fixing the bearing 203. Six sets of blades 305 are fixed on the rotary shaft. Each set of blades 305 includes two blades 305 arranged axially. The blades 305 in each set are parallel to each other. The six sets of blades are arranged circumferentially on the rotary shaft 302. The included angle between two adjacent sets of blades is 60 degrees. The wind deflector 201 and its surrounding wind-blocking surface 204 form a semi-circular arc-shaped opening space 208. When the rotating impeller 3 rotates, it pushes the airflow at the opening space 208 to generate a reaction force, thereby providing lift for the UAV. The angle between the plane normal vector of the opening space 208 and the vertical plane containing the axis of the rotating impeller 3 is 30 degrees. When the wind deflector 3 is installed, the opening space 208 of the wind deflector 2 installed on the rear mounting arm 101 is biased towards the rear of the UAV, while the opening space 208 of the wind deflector 2 installed on the front mounting arm 102 is oriented towards the front of the UAV. A tail wing frame mounting groove 103 is provided at the rear of the fuselage frame 1, near the rear mounting arm 102, for installing the tail wing frame 4. The vertical tail rotor 5 is installed at the upper end of the tail of the tail wing frame 4, and the rotation axis of the vertical tail rotor 5 is parallel to the rotation axis of the rotating impeller 3, used to control the flight direction of the UAV. The horizontal tail rotor 6 is installed at the lower end of the tail of the tail wing frame 4. The horizontal tail rotor 6 has its rotation axis perpendicular to the ground and also perpendicular to the rotation axis of the vertical tail rotor 5, which is used to stabilize the flight attitude of the UAV.The vertical tail rotor 5 includes a tail rotor frame 501, a propeller 502, and a tail rotor motor 503. The tail rotor motor 503 is fixed to the upper end of the tail fin frame 4, and the propeller 502 is mounted on the tail rotor motor 503. The tail rotor frame is fixed to the housing of the tail rotor motor 503, providing protection for the vertical tail rotor. The horizontal tail rotor 6 includes a horizontal blade 601 and a propeller motor 602. The propeller motor 602 is fixed to the lower end of the tail fin frame 4, and the horizontal blade 601 is fixed to the rotation shaft of the propeller motor 602. The fuselage frame 1 has four landing gear mounting holes 104 at its bottom for mounting two UAV landing gears 7. When the UAV is stationary on the ground, the landing gears 7 provide basic support.

Claims

1. A high-efficiency impeller-driven unmanned aerial vehicle with a large windward area, characterized in that: Includes fuselage frame[1], windshield[2], rotating impeller[3], tail frame[4], vertical tail rotor[5], horizontal tail rotor[6] and UAV landing gear[7]; The fuselage frame [1] has four horizontally arranged rotating impellers [3] in two rows on both sides. The four rotating impellers [3] are arranged in an isosceles trapezoidal shape on the fuselage frame [1]. Each rotating impeller [3] is equipped with a wind shield [2]. The wind shield [2] is coaxial with the rotating impeller [3] and is installed on the fuselage frame [1]. The tail fin frame [4] is installed at the tail of the fuselage frame [1]. The vertical tail rotor [5] is installed at the upper end of the tail of the tail fin frame [4]. The rotation axis of the vertical tail rotor [5] is parallel to the rotation axis of the rotating impeller [3] and is used to control the flight direction of the UAV. The horizontal tail rotor [6] is installed at the lower end of the tail of the tail fin frame [4]. The rotation axis of the horizontal tail rotor [6] is perpendicular to the ground and perpendicular to the rotation axis of the vertical tail rotor [5] and is used to stabilize the flight attitude of the UAV. The UAV landing gear [7] is symmetrically mounted at the bottom of the fuselage frame [1] to provide basic support for the UAV when it is on the ground.

2. The large windward area, high-efficiency impeller-driven UAV according to claim 1, characterized in that: The fuselage frame [1] is symmetrically provided with a rear mounting arm [101] and a front mounting arm [102], wherein the length of the rear mounting arm [101] is longer than the radial width of the windshield [2] by the length of the front mounting arm [102]; a tail wing frame mounting groove [103] is provided at the rear of the fuselage frame [1] near the end of the rear mounting arm [102] for mounting the tail wing frame [4]; four landing gear mounting holes [104] are provided at the bottom of the fuselage frame [1] for mounting two UAV landing gears [7]; The ends of the two rear mounting arms [101] and the two front mounting arms [102] are provided with windshield mounting holes [105] and motor mounting slots [106], which are used to install the windshield [2] and the rotary motor [301] on the rotary impeller [3], respectively.

3. A high-efficiency impeller-driven UAV with a large windward area as described in claim 1 or 2, characterized in that: The power unit includes a windshield[2] and a rotating impeller[3]; The windshield [2] includes a windshield plate [201], a windshield frame [202], a bearing [203], a windshield surface [204], a windshield frame [205], and mounting holes [206]. The rotating impeller [3] includes a rotating motor [301], a rotating shaft [302], a bearing hole [303], a blade frame [304], and blades [305]. The wind deflector [201] is a 180-degree arc plate fixed on the wind deflector frame [202]. The inner ring of the bearing [203] is fixed on the wind deflector [204], and the outer ring of the bearing [203] is fixed in the bearing hole [303] to provide support for the wind deflector [2]. The wind deflector [201] has wind deflectors [204] symmetrically installed on both sides. The wind deflector frame [205] is fixed to the wind deflector frame [202]. The wind deflector frame [205] has 4 mounting holes [206] arranged on it, which coincide with the wind deflector mounting holes [105]. The rotary motor [301] is installed in the motor mounting slot [106]. The rotating shaft [302] is fixed on the rotary motor [301] and coincides with the axis of the rotary motor [301]. A bearing hole [303] is provided at the end of the rotating shaft for fixing the bearing [203]. Six sets of blades [305] are fixed on the rotating shaft. Each set of blades [305] includes two blades arranged along the axial direction. The blades [305] in each set are parallel to each other. The six sets of blades are arranged circumferentially on the rotating shaft [302], and the included angle between two adjacent sets of blades is 60 degrees.

4. The large windward area, high-efficiency impeller-driven UAV according to claim 1, characterized in that: The vertical tail rotor [5] includes a tail rotor frame [501], a propeller [502], and a tail rotor motor [503]. The tail rotor motor [503] is fixed to the upper end of the tail rotor frame [4]. The propeller [502] is mounted on the tail rotor motor [503]. The tail rotor frame is fixed to the housing of the tail rotor motor [503], which can provide protection for the tail rotor. The horizontal tail rotor [6] includes a horizontal blade [601] and a propeller motor [602]. The propeller motor [602] is fixed to the lower end of the tail rotor frame [4]. The horizontal blade [601] is fixed to the rotating shaft of the propeller motor [602].

5. The large windward area, high-efficiency impeller-driven UAV according to any one of claims 1-4, characterized in that: The wind deflector [201] and the surrounding wind deflector surface [204] form a semi-circular arc-shaped opening space [208]. When the rotating impeller [3] rotates, the rotating impeller [3] at the opening space [208] pushes the airflow to generate a reaction force, thereby providing the UAV with vertical lift and horizontal thrust. The angle between the plane normal vector of the opening space [208] and the vertical plane containing the axis of the rotating impeller [3] is 30 degrees. When the wind shield [3] is installed, the direction of the opening space [208] of the wind shield [2] installed on the rear mounting arm [101] faces the rear of the drone; the direction of the opening space [208] of the wind shield [2] installed on the front mounting arm [102] faces the front of the drone.

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