Paddle damping device of unmanned aerial vehicle

Abstract

The utility model discloses a blade damping device of an unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles and comprises a damping support, a shaft driving motor, a wing plate, a frame ring frame, blades and a support rod, the damping support is nested on the top of the shaft driving motor, and the blades are mounted in the frame ring frame. A worker assembles the damping support, the damping support and the wing plate are of an integrated structure through the base plate between the shaft driving motor and the blade, the frame ring frame and the supporting rod surround the blade to prevent deviation efficiently, and when the blade rotates and vibrates, the folding plate of the spring wire plate frame is sprung and extruded to form the upper damping operation effect in the support cylinder together with the spring wire. A balance weight ball groove is formed in a torsional spring pipe of the ball support mechanism to achieve the effect of stabilizing transmission shaft axis balance weight to align to lower-layer damping operation of a shaft driving motor, upper-layer damping and lower-layer damping are matched with protection of a whole paddle base, the air stratosphere amplitude of the whole unmanned aerial vehicle is reduced, the single-side wing deviation phenomenon is reduced, and the effect of more precise flight is achieved.

Description

Technical Field

[0001] The utility model relates to the technical field of unmanned aerial vehicles, in particular to a blade vibration reduction device for an unmanned aerial vehicle. Background Art

[0002] Aircraft refers to aircraft that can fly in the atmosphere. Any aircraft must generate a lift greater than its own weight in order to rise into the air. Based on the principle of generating lift, aircraft can be divided into two categories: lighter-than-air aircraft and heavier-than-air aircraft. The former relies on the static buoyancy of air to rise into the air; the latter relies on aerodynamic force to overcome its own gravity to rise into the air. Aircraft is a large category of aircraft, and refers to any machine that obtains aerodynamic force to rise into the air through the relative movement of the fuselage and the air, that is, not the reaction of air to the ground. Including balloons, airships, airplanes, gliders, gyroplanes, helicopters, flapping-wing aircraft, tilt-rotor aircraft, etc., and unmanned aerial vehicles are also a relatively special category of aircraft.

[0003] The propeller blades of unmanned aerial vehicles are often prone to a certain amount of working vibration due to bearing derailment or eccentricity. During routine testing, the propeller blade vibration will cause air stratosphere vibration, causing the flight of the unmanned aerial vehicle to be unstable and easily float up and down with the vibration amplitude, or cause the deviation of one side of the propeller blade to pull the aircraft off course. Utility Model Content

[0004] In view of the deficiencies in the prior art, the utility model provides a blade shock-absorbing device for an unmanned aerial vehicle to solve the problem that the blades of the unmanned aerial vehicle are often prone to a certain amount of working vibration due to bearing derailment or eccentricity. During routine testing, the blade vibration will cause air stratosphere vibration, resulting in unstable flight of the unmanned aerial vehicle, which is prone to floating up and down with the vibration amplitude, or causing unilateral blade deviation to pull the aircraft off course.

[0005] To achieve the above purpose, the utility model is implemented through the following technical solutions: a blade shock absorption device of an unmanned aerial vehicle, including a shock absorption support, an axial motor, a wing plate, a frame ring frame, a blade, and a support rod. The shock absorption support is nested on the top of the axial motor, the blade is installed inside the frame ring frame, three support rods are provided and are welded into one around the axis of the frame ring frame, the wing plate is fixed together with the support rod through the shock absorption support, the shock absorption support is provided with a spring wire plate frame, a support tube, a pad, and a ball support mechanism, the spring wire plate frame is installed inside the support tube, the support tube is tightly attached to the top surface of the pad, and the ball support mechanism is nested inside the axis of the pad.

[0006] Preferably, the spring wire plate frame is provided with a folding plate and a spring wire, two spring wires are provided and are respectively installed on the left and right sides of the folding plate, and the spring wire is mechanically connected to the folding plate.

[0007] Preferably, the ball support mechanism is provided with a torsion spring tube, a counterweight ball slot, a support pad block, and a transmission shaft. The torsion spring tube is vertically inserted into the counterweight ball slot, and the transmission shaft vertically passes through the torsion spring tube and the axis of the counterweight ball slot. Two support pad blocks are provided and are respectively tightly attached to the left and right lower corners of the counterweight ball slot.

[0008] Preferably, the folding plate is a folding circular plate frame structure in which three layers of gasket ring layers are stacked at the ends, so that the three plates can be folded to form the effect of alternating traction and shock absorption on the left and right sides of the spring wire.

[0009] Preferably, the torsion spring tube is a helical torsion spring body structure with a thick rubber shell covering the surface, so as to facilitate the thick torque damping to adapt to the stable and efficient rotational motion of the blades of the unmanned aerial vehicle.

[0010] Preferably, the counterweight ball slot is a composite ball slot structure with upper and lower semicircular counterweight blocks and a spherical cavity in the middle, which is convenient for the upper and lower axis configuration to prevent deviation efficiently, and the support pad is a pea-shaped pad structure, which is convenient for the left and right support pad counterweight ball slots to be clamped firmly.

[0011] The utility model provides a blade vibration reduction device for an unmanned aerial vehicle, which has the following beneficial effects:

[0012] The invention relates to a blade shock-absorbing device for an unmanned aerial vehicle. Workers assemble a shock-absorbing support between the shaft-driven motor and the blade through a pad and a wing plate to form an integrated structure, so that the frame ring frame and the support rod can effectively prevent the blade from deflecting. When the blade rotates and vibrates, the folding plate and the spring wire of the spring wire plate frame are elastically squeezed to form an upper shock-absorbing operation effect in the support tube. Then, a built-in counterweight ball groove of the torsion spring tube of the ball support mechanism forms a lower shock-absorbing operation effect of the shaft-driven motor with a stable counterweight to the axis of the transmission shaft. The upper and lower shock-absorbing layers cooperate with the protection of the entire blade base, so that the entire unmanned aerial vehicle can reduce the air stratospheric amplitude, and the deviation phenomenon of the wing on one side is reduced, so as to achieve a more precise flight effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] Figure 1 This is a schematic diagram of the three-dimensional structure of a blade shock absorbing device for an unmanned aerial vehicle according to the utility model;

[0014] Figure 2 This is a schematic diagram of the cross-sectional structure of the shock-absorbing support of the utility model;

[0015] Figure 3 This is a schematic diagram of the cross-sectional structure of the spring wire frame of the utility model;

[0016] Figure 4 It is a schematic diagram of the cross-sectional structure of the ball support mechanism of the utility model.

[0017] In the figure: shock-absorbing support 1, shaft-driven motor 2, wing plate 3, frame ring frame 4, blade 5, support rod 6, spring wire plate frame 11, support tube 12, pad 13, ball support mechanism 14, folding plate 111, spring wire 112, torsion spring tube 141, counterweight ball groove 142, support pad 143, transmission shaft 144. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0019] See also Figure 1-Figure 4 The utility model provides a blade shock absorbing device for an unmanned aerial vehicle, comprising a shock absorbing support 1, an axial motor 2, a wing plate 3, a frame ring frame 4, a blade 5, and a support rod 6. The shock absorbing support 1 is nested on the top of the axial motor 2, the blade 5 is installed inside the frame ring frame 4, three support rods 6 are provided and welded together around the axis of the frame ring frame 4, and the wing plate 3 is fixed together with the support rod 6 through the shock absorbing support 1.

[0020] Since the propeller blades of unmanned aerial vehicles are often prone to a certain amount of working vibration due to bearing derailment or eccentricity, the propeller blade vibration will cause air stratosphere vibration during routine testing, resulting in unstable flight of the unmanned aerial vehicle, which is easy to float up and down with the vibration amplitude, or cause the deviation of one side of the propeller blade to pull the aircraft off course.

[0021] The shock-absorbing support 1 is provided with a spring wire frame 11, a support tube 12, a pad 13, and a ball support mechanism 14. The spring wire frame 11 is installed inside the support tube 12, the support tube 12 is tightly attached to the top surface of the pad 13, and the ball support mechanism 14 is nested inside the axis of the pad 13.

[0022] The spring wire plate frame 11 is provided with a folding plate 111 and a spring wire 112. Two spring wires 112 are provided and are respectively installed on the left and right sides of the folding plate 111. The spring wire 112 is mechanically connected to the folding plate 111. The folding plate 111 is a folding circular plate frame structure with three layers of gasket ring layers stacked at the ends, which facilitates the folding of the three plates to form an alternating traction and shock absorption effect on the left and right sides of the spring wire 112.

[0023] The ball support mechanism 14 is provided with a torsion spring tube 141, a counterweight ball slot 142, a support pad 143, and a transmission shaft 144. The torsion spring tube 141 is vertically inserted into the interior of the counterweight ball slot 142, and the transmission shaft 144 vertically penetrates the interior of the torsion spring tube 141 and the axis of the counterweight ball slot 142. Two support pads 143 are provided and are respectively tightly attached to the left and right lower corners of the counterweight ball slot 142. The torsion spring tube 141 is a spiral torsion spring body structure with a thick rubber shell wrapped on the surface, which is convenient for thick torque shock absorption to adapt to the stable and efficient rotational movement of the blades 5 of the unmanned aerial vehicle. The counterweight ball slot 142 is a composite ball slot structure with upper and lower semicircular counterweight blocks and a spherical cavity in the middle, which is convenient for the upper and lower axis configuration to prevent deviation and be efficient. The support pad 143 is a pea-shaped pad structure, which is convenient for the left and right support pads and counterweight ball slots 142 to be clamped firmly.

[0024] The staff assembles the shock-absorbing support 1 between the axial motor 2 and the blade 5 through the pad 13 and the wing plate 3 to form an integrated structure, so that the frame ring frame 4 and the support rod 6 can effectively protect the blade 5 from deviation, and when the blade 5 rotates and vibrates, the folding plate 111 and the spring wire 112 of the spring wire plate frame 11 are elastically squeezed to form an upper shock-absorbing operation effect in the support tube 12, and then the built-in counterweight ball groove 142 of the torsion spring tube 141 of the ball support mechanism 14 forms a stabilizing drive shaft 144 axial counterweight to align the axial motor 2 lower shock-absorbing operation effect, so that the upper and lower shock absorption cooperate with the entire blade 5 base protection, so that the entire unmanned aerial vehicle can reduce the air stratospheric amplitude, and the unilateral wing deviation phenomenon is reduced, so as to achieve the effect of more precise flight.

[0025] The above description is only a specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application.

Claims

1. A blade vibration reduction device for an unmanned aerial vehicle, characterized in that: The invention comprises a shock absorbing support (1), an axial motor (2), a wing plate (3), a frame ring frame (4), a blade (5), and a support rod (6); the shock absorbing support (1) is nested on the top of the axial motor (2); the blade (5) is installed inside the frame ring frame (4); three support rods (6) are provided and are welded together around the axis of the frame ring frame (4); and the wing plate (3) is fixed together with the support rod (6) through the shock absorbing support (1); The shock-absorbing support (1) is provided with a spring wire plate frame (11), a support tube (12), a pad (13), and a ball support mechanism (14); the spring wire plate frame (11) is installed inside the support tube (12); the support tube (12) is closely attached to the top surface of the pad (13); and the ball support mechanism (14) is nested inside the axis of the pad (13).

2. The blade vibration reduction device of an unmanned aerial vehicle according to claim 1, characterized in that: The spring wire plate frame (11) is provided with a folding plate (111) and a spring wire (112). Two spring wires (112) are provided and are respectively installed on the left and right sides of the folding plate (111). The spring wire (112) is mechanically connected to the folding plate (111).

3. The blade vibration reduction device of an unmanned aerial vehicle according to claim 1, characterized in that: The ball support mechanism (14) is provided with a torsion spring tube (141), a counterweight ball slot (142), a support pad (143), and a transmission shaft (144); the torsion spring tube (141) is vertically inserted into the counterweight ball slot (142); the transmission shaft (144) vertically penetrates the interior of the torsion spring tube (141) and the axis of the counterweight ball slot (142); and two support pads (143) are provided and are respectively closely attached to the left and right lower corners of the counterweight ball slot (142).

4. The blade vibration reduction device of an unmanned aerial vehicle according to claim 2, characterized in that: The folding plate (111) is a folding circular plate frame structure in which three layers of gasket ring layers are stacked at the ends.

5. The blade vibration reduction device of an unmanned aerial vehicle according to claim 3, characterized in that: The torsion spring tube (141) is a helical torsion spring body structure with a thick rubber shell covering the surface.

6. The blade vibration reduction device of an unmanned aerial vehicle according to claim 3, characterized in that: The counterweight ball groove (142) is a composite ball groove structure with upper and lower semicircular counterweight blocks and a spherical cavity in the middle, and the support pad (143) is a pea-shaped pad structure.

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