A kind of flap control method and system

Abstract

The invention relates to a flap control method and system. The control method includes: acquiring a flight speed of a helicopter; determining a control parameter value of a trailing edge flap and a control parameter value of a leading edge flap according to the flight speed, wherein the control parameter value includes a deflection amplitude and a deflection direction; The deflection of the trailing edge flap is controlled according to the control parameter value of the trailing edge flap; the deflection of the leading edge flap is controlled according to the control parameter value of the leading edge flap. The present invention mitigates the adverse consequences of vibration control by means of trailing edge flaps alone.

Description

technical field [0001] The invention relates to the field of flap control, in particular to a flap control method and system. Background technique [0002] There are many rotating parts on helicopters, such as rotors, tail rotors, engines and transmission systems, which generate alternating loads during operation, and these alternating loads will become the vibration source of the helicopter. The exciting force of these vibration sources acts on the body structure to cause the body to vibrate. Airframe vibration will affect the comfort of the driver and occupants, as well as the fatigue life of the airframe structure and the normal operation of instrumentation equipment. Among all rotating parts, the exciting force generated by the rotor is the largest. Therefore, how to reduce the vibration of the rotor is an important part of the helicopter design. [0003] At present, the technologies used to reduce rotor vibration on helicopters are mainly divided into passive control ...

AI Technical Summary

Problems solved by technology

[0004] Vibration control through the trailing edge flap requires the deflection of the trailing edge flap relative to the blades. In order to achieve the specified vibration level in the helicopter’s partial flight state, the deflection range of the trailing edge flap is relatively large, which leads to a relatively high power consumption of the helicopter rotor. Large; the blade is an elastic body, and at the same time it is in a state of high-speed motion. After the deflection of the trailing edge flap, it will inevitably cause the torsion and bending deformation of the blade itself. The trailing edge flap only indirectly affects the aerodynamic environment of the leading edge. The vibration problem caused by the dynamic stall caused by the trailing edge is difficult to slow down by trailing edge flaps alone

[0005] To sum up, the vibration control only through the trailing edge flap will cause the helicopter rotor to consume more power, cause the torsion and bending deformation of the blade itself, and cause rotor vibration.

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