Propeller aircraft slip flow pre-sensing rudder deflection control method and system

Abstract

The invention relates to a propeller aircraft slip flow pre-sensing rudder deflection control method. The method comprises the steps that an interpolation table of rudder deflection control angles of dynamic pressure, attack angles and axial overload under different flap skewness is constructed; obtaining a rudder deflection control angle according to the interpolation table, and generating a corresponding rudder deflection control signal; and connecting the rudder deflection control signal to a rudder control system to control the rudder to deflect. In addition, the invention relates to a propeller-driven aircraft slip flow pre-sensing rudder deflection control system, which comprises a rudder deflection balancing unit, which is internally provided with an interpolation table of rudder deflection control angles of dynamic pressure, attack angle and axial overload under different flap skewness, is connected with flap skewness signals, dynamic pressure signals, attack angle signals and axial overload signals, and is used for controlling the slip flow of a propeller-driven aircraft according to the interpolation table. And a rudder deflection control angle is obtained, a corresponding rudder deflection control signal is output, the rudder deflection control signal is input into a rudder control system, and the rudder is controlled to deflect.

Description

technical field [0001] The application belongs to the technical field of propeller aircraft slipstream change rudder deflection control, and in particular relates to a propeller aircraft slipstream pre-sensing rudder deflection control method and system thereof. Background technique [0002] The propeller of a propeller aircraft produces a spiral slipstream, which causes the aircraft to generate a yaw moment, which is mainly balanced by the deflection of the rudder. [0003] When the throttle of the aircraft is moved substantially, the helical slipstream generated by the propeller will change rapidly over a wide range. Although the rudder is designed to have an automatic trim function, it is a passive trim mechanism. When the state quantity deviates, the trim Before the full trim, there is a deviation in the state quantity, and it is automatically trimmed based on the integrator, which causes a phase lag in the control system, and is limited by the requirements of the stabil...

AI Technical Summary

Problems solved by technology

[0003] When the throttle of the aircraft is moved substantially, the helical slipstream generated by the propeller will change rapidly over a wide range. Although the rudder is designed to have an automatic trim function, it is a passive trim mechanism. When the state quantity deviates, the trim Before the full trim, there is a deviation in the state quantity, and it is automatically trimmed based on the integrator, which causes a phase lag in the control system, and is limited by the requirements of the stability margin of the control system, the gain of the integrator is usually not Large, the speed of automatic trim is relatively slow, and it is difficult to effectively suppress the yaw transient of the aircraft in the case of a large range of rapid changes in slip flow

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