Autonomous electro-hydraulic flight control actuator

The issues of the layout of flight control actuators on a mainline aircraft are considered. The authors give classification of flight control actuators by power sources, technical solutions, types of executive hydraulic motor, methods of organizing control and regulation, types of power sources. Three types of flight control actuators are considered in detail according to the type of power source: with centralized power supply, with self-contained power supply and electric power supply. The main advantages and disadvantages of development and operation of autonomous flight control actuators are formulated. The basic circuit solutions of promising autonomous flight control actuators are considered. The authors present a universal scheme for the implementation of an autonomous flight control actuator with account for possible regulating and regulated variables of the automatic control system. Based on the analysis of the revealed disadvantages of an autonomous flight control actuator, the priorities for improving are determined. The controlled parameters have been identified and possible types of regulators for an autonomous flight control actuator that compensate for external influence have been proposed. A possible interpretation of an autonomous flight control actuator as an object of regulation is presented. As information signals, the authors propose to use hydro-mechanical compensatory devices, namely pressure and flow sensors in the cavities of the hydraulic motor working in conjunction with regulators of the following types: pressure (dynamic pressure), speed, power and load sensitivity (LS) ones. A mathematical model of a flight control actuator with a power regulator and simulation results are presented

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