Integral flapping device for propeller
A propeller and integral technology, which is applied in the field of propeller integral waving devices, can solve the problems of increasing the moment of inertia of the hinge mechanism, reducing the lift force of the forward propeller, and the complex structure of the propeller.
Inactive Publication Date: 2021-03-19
江富余
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Problems solved by technology
[0002] At present, the known method for overcoming the unfavorable effect of the lift asymmetry caused by the acceleration of the propeller's forward blade and the deceleration of the backward blade on the forward flight of the helicopter is to adopt the flapping hinge of the blade, such as the tail propeller of a conventional single-rotor helicopter. Hinged waving device, which uses a horizontal hinge to make the blades of the propeller swing up and down, reducing the lift of the forward blades and reducing the lift asymmetry caused by the acceleration of the forward blades and the deceleration of the backward blades of the propeller, but because the horizontal hinge follows The rotation of the blades makes the structure of the propeller complex, the moment of inertia of the hinge mechanism increases, and the maintenance is difficult
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[0022] exist figure 1 In the shown embodiment, the blades of the propeller 1 are connected to the propeller hub 2 of the propeller, and the propeller hub 2 is connected to the propeller rotating main shaft 3, the propeller rotating main shaft 3 is perpendicular to the horizontal plane, and the engine 4 drives the propeller rotating main shaft 3 to drive the propeller 1 Rotate, the propeller 1 and the engine 4 are integrally installed on the bilateral tilting side frame 5, the sides of the bilateral tilting side frame 5 are parallel to the rotating surface of the propeller, and damping springs 9 are arranged at the lateral ends of the bilateral tilting side frame 5, and the damping spring 9 limits the bilateral tilting side frame 5 The damping spring 9 is installed on the bilateral mounting base 6, and the center of the bilateral tilting frame 5 is longitudinally provided with a rotating shaft 8, and the two ends of the rotating shaft 8 are installed on the bearing seat 7 in the...
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The invention relates to an integral flapping device for a propeller. The device is characterized in that a propeller and an engine are integrally mounted on a bilateral tilting frame or a unilateraltilting frame, and damping springs or damping rubber structures are arranged at two transverse ends of the bilateral tilting frame or one transverse end of the unilateral tilting frame. The damping springs or the damping rubber limit the tilting degree of the bilateral tilting frame or the unilateral tilting frame, the damping springs or the damping rubbers are installed on a double-side installation base or a single-side installation base, and a rotating shaft is arranged in the longitudinal direction of the center of the bilateral tilting frame or at the other end of the unilateral tilting frame. The two ends of the rotating shaft are installed on a bearing pedestal in the middle of the double-side installation base or a bearing pedestal at the other end of the single-side installation base, so that the bilateral tilting frame or the unilateral tilting frame can rotate around the rotating shaft, and screw holes are formed in the double-side installation base or the single-side installation base. The double-side installation base or the single-side installation base is mounted on a machine body through screws and is used for reducing the asymmetry degree of the lifting force of aforward blade and a backward blade of the propeller.
Description
technical field [0001] The invention relates to a propeller integral waving device for a multi-propeller helicopter, which can overcome the problem that due to the horizontal setting of the propeller rotating surface of the multi-propeller helicopter, when the multi-propeller helicopter is flying forward horizontally, the forward blades of the propellers are accelerated, and the lift force increases, while the backward blades The deceleration lift force is reduced, causing roll disturbance and reducing the alternating bending moment generated by the root of the blade of the propeller, prolonging the service life of the blade. Background technique [0002] At present, the known method for overcoming the unfavorable effect of the lift asymmetry caused by the acceleration of the propeller's forward blade and the deceleration of the backward blade on the forward flight of the helicopter is to adopt the flapping hinge of the blade, such as the tail propeller of a conventional sing...
Claims
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IPC IPC(8): B64C27/52
CPCB64C27/52
Inventor 江富余
Owner 江富余