An unmanned autogyro rotor control mechanism
A control mechanism and rotorcraft technology, applied in the field of unmanned autogyro rotor control mechanism, can solve the problems of slow development and inability to hover, and achieve the effects of reasonable mechanism layout, reduced resistance, and improved flight performance
Active Publication Date: 2020-12-18
CAIHONG DRONE TECH CO LTD
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- Application Information
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Problems solved by technology
[0003] The autogyro appeared earlier than the helicopter, but because it could not hover, the subsequent development slowed down
Method used
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Embodiment Construction
[0030] Such as figure 1 , 3 As shown, the present invention proposes a rotor control mechanism for an unmanned autogyro, including: a rotor support 1, an upper link 2, an ear piece 3, a lower link 4, a pitch assembly, a roll assembly, and a transmission assembly;
[0031] The rotor of the UAV is installed on the rotor support 1, the upper link 2 is connected with the lower link 4 through the lug 3, the upper link 2 is connected with the rotor support 1, the pitch component and the roll component are both passed through the transmission component It is connected with the lower link 4 to drive the rotor support 1 to pitch and roll, thereby realizing the pitch and roll control of the UAV rotor. Rotor pitch control and roll control are separated, and can be controlled at the same time, and pitch control or roll control can be performed independently without affecting the other party.
[0032] Between the upper connecting rod 2 and the ear piece 3, between the ear piece 3 and the...
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A rotor operating mechanism for an unmanned autogiro is used for achieving pitch operation and roll operation of a disc of the unmanned autogyro. Two upper control levers are respectively connected toear pieces on both ends of a rotor support, and are connected to lower connecting rods through the ear pieces mounted on a fuselage framework; the lower connecting rods are connected to an adapter piece mounted on upper and lower crossbars; the lower crossbar is mounted on the fuselage framework and can rotate around about a mounting axis; the upper crossbar is connected with the lower connectingrods through the ear pieces and the adapter piece; a disc pitch control steering gear is mounted on the lower crossbar; a pitch control arm is mounted on the upper and lower crossbars by bolts; a steering gear rocker arm is connected to the pitch control arm through the connecting rods; a disc transverse control steering gear is mounted on a fuselage bracket; a transverse control arm is mounted on the lower crossbar by the bolts; and the steering gear rocker arm is connected to the l transverse control arm through the connecting rods. Pitch and roll of a rotor disc can be controlled respectively through a longitudinal control steering gear and a transverse control steering gear, thereby changing a flight attitude of the unmanned autogyro.
Description
technical field [0001] The invention relates to the technical field of aircraft design, in particular to an unmanned autogyro rotor control mechanism. Background technique [0002] Autogyro is a rotorcraft that utilizes incoming flow to drive the rotor to rotate itself to generate lift, and the propeller pushes (pulls) to overcome the forward flight resistance. The difference between an autogyro and a helicopter is that the rotor of the autogyro relies on the incoming flow to drive the rotation, while the rotor of the helicopter relies on the engine to drive; the forward flight of the autogyro uses the push (pull) force of the propeller to overcome the forward flight resistance, while the helicopter generally It is to use the rotor pull force component to overcome the forward flight resistance; the autogyro generally uses the tilting rotor disc to change the flight state, while the helicopter generally uses the periodic pitch change to change the flight state. [0003] The ...
Claims
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IPC IPC(8): B64C27/12
CPCB64C27/12
Inventor 吴伟伟马存旺李明新李志国苏浩秦
Owner CAIHONG DRONE TECH CO LTD