Flap control method and system

Abstract

The invention relates to a flap control method and system. The control method comprises the following steps: acquiring the 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 values comprise a deflection amplitude and a deflection direction; controlling the trailing edge flap to deflect according to the control parameter value of the trailing edge flap; and controlling the leading edge flap to deflect according to the control parameter value of the leading edge flap. According to the invention, adverse results caused by vibration control only through the trailing edge flap can be relieved.

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 a helicopter, such as rotors, tail rotors, engines, and transmission systems. They will 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 passengers, as well as the fatigue life of the airframe structure and the normal operation of instrumentation equipment. Among the various rotating parts, the exciting force generated by the rotor is the largest. Therefore, how to reduce the vibration of the rotor is a very important part of the helicopter design. [0003] At present, the technologies used to reduce rotor vibration on helicopters are mainly divided in...

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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