Drive mechanism for trailing edge flaps of variable-speed rigid rotor

Abstract

The invention discloses a drive mechanism for trailing edge flaps of a variable-speed rigid rotor comprising a fixing frame, a driver, trailing edge flaps and pressing blocks, a wedge block and a steel bar matched with the fixing frame, wherein the driver comprises driver base steel sheets and piezoelectric fiber sheets affixed to the driver base steel sheets; the rear ends of the driver base steel sheets are connected to the trailing edge flaps and the front ends of the driver base steel sheets are fixed to the body of the fixing frame by virtue of the pressing blocks; the upper surface of the portion, between each piezoelectric fiber sheet and each trailing edge flap, of each driver base steel sheet is in contact with the wedge block on the body of the fixing frame, and the lower surface of the portion, between each piezoelectric fiber sheet and each trailing edge flap, of each driver base steel sheet is in contact with the steel bar on the body of the fixing frame; and the steel bar and the wedge block clamp the drive base steel sheets to form revolute prismatic joints. The drive mechanism for the trailing edge flaps of the variable-speed rigid rotor is used for driving the deflection motion of the trailing edge flaps, and the additional aerodynamic load caused by the deflection motion of the trailing edge flaps is used to counteract a part of the vibration load of the variable-speed rigid rotor to achieve the purpose of vibration reduction.

Description

technical field [0001] The invention belongs to an intelligent driving mechanism in the field of helicopters, and in particular relates to an active deformation trailing edgelet light-weight driving mechanism suitable for variable-speed rigid rotors. Background technique [0002] Helicopters have been widely used in military and civilian fields because of their high-efficiency hovering, low-speed forward flight and other performances that fixed-wing aircraft do not have. However, compared with fixed-wing aircraft, conventional configuration helicopters have obvious gaps in maximum range and flight time. One of the main reasons leading to this problem is that the rotational speed of conventional helicopter rotors cannot be adjusted in good time according to changes in flight status. In the design stage of conventional helicopters, designers comprehensively consider parameters such as the maximum weight, maximum forward speed, and design critical height of the helicopter to d...

AI Technical Summary

Problems solved by technology

The operating speed of the variable speed helicopter rotor will vary in a large range with different working conditions, and the frequency of the rotor vibration load will also change greatly. Conventional rotor vibration reduction measures are difficult to meet the variable speed helicopter rotor vibration reduction requirements.

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