Investigation of Characteristics of an Electrohydraulic Servoactuator Incorporating Jet Pipe Amplifier (original) (raw)
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Motion control of an aircraft electro-hydraulic servo actuator
IOP Conf. Series: Materials Science and Engineering 610, 18th International Conference on Aerospace Sciences & Aviation Technology, 2019
The use of the Fly-by-Wire (FBW) systems for flight control of aeronautical vehicles has increased steadily in the recent years. Such systems use electro-hydraulic servo-actuators to position the manoeuvring surfaces of airplanes or movable thrust vector controls of space vehicles. The marriage between electronics and hydraulic power systems has led to many powerful and precise control systems, saving much energy and money. This paper deals with the motion control of aircraft integrated electro-hydraulic servo-actuator (ISA) via development of a detailed nonlinear mathematical model and a computer simulation program using MATLAB/SIMULINK package. The ISA mainly consists of two separate active hydraulic power systems, used to supply the ISA with the required power. The studied ISA incorporates two electro-hydraulic servo-valves, a twin-symmetrical-hydraulic actuating cylinder, and a smart design of built in directional control valves with a feedback system. The output linear motion of the actuating cylinder of the ISA is presented and controlled by obtaining the transient response of the ISA. A classical PID controller is designed and tuned by Zeigler-Nichols method according to the Integral Square Error (ISE) criteria to minimize the difference between the obtained system output feedback and the desired set input by adjusting the system control parameters. The system stability and precision requirements are insured by applying the tuned PID controller.
For a mechanohydraulic servomechanism used in the control chain of an airplane a mathematical model given by four strongly nonlinear ordinary differential equations is considered. It relates the state variables of the inertial load (position and speed) to the pressures in the two chambers of the hydrocylinder. The Jacobian matrix for the equilibria has a zero in its spectrum so we have a critical case for Lyapunov stability analysis. This case is handled using Lyapunov-Malkin approach, and as a result some stability charts are drawn in the space of parameters indexing equilibria. To ensure stability for all equilibria with respect to first state variable (position), is considered control synthesized for an electrohydraulic servo. A stabilizing control law is considered using the method of backstepping and Barbalat's lemma.
Electro-hydrostatic servo-actuators for aircraft
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Some great aeronautic catastrophes were produced by the hydraulic liquid lost and from this by the impossibility of aerodynamic surfaces command. For this reason it appears necessary to replace the centralized hydraulic system with some small local hydraulic systems. This paper presents some problems concerning these actuators, a mathematical model for a such actuator and some numerical simulations.
Feasibility Study of a PHM System for Electro-hydraulic Servo-actuators for Primary Flight Controls
Annual Conference of the PHM Society
Electro-Hydraulic Servo-Actuators (EHSA) are by far the mostly used type of actuators in aircraft primary flight control systems. Though electrical actuation is been considered since long as a possible replacement of hydraulic actuation for aircraft systems, EHSAs are still the technology of choice in the primary flight control systems of new commercial aircrafts. Considering that 10 or more EHSAs are typically used in an aircraft flight control system, the development of an effective PHM system for this equipment could provide large benefits and be of great interest for the OEMs and for the air fleet operators. This paper presents the results of a feasibility study making up the first part of an ongoing research activity focused on the development of a PHM system for EHSAs used in fly-by-wire primary flight control systems and takes as a use case the primary flight control actuator of a wide body commercial aircraft. One of the key features of the research is the implementation of ...
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B P International, 2023
The use of Fly-by-Wire (FBW) systems for aeronautical vehicle flight control has continuously increased in recent years. These systems employ electro-hydraulic servo-actuators to position the movable thrust vector controls on spacecraft or airplanes maneuvering surfaces. Electronics and hydraulic power systems have been combined to provide a variety of strong and accurate control systems that save a significant amount of energy and money. In this study, a comprehensive nonlinear mathematical model and a computer simulation program using the MATLAB/SIMULINK package are used to control the motion of an aircraft integrated electro-hydraulic servo-actuator (ISA). The ISA is primarily made up of two distinct active hydraulic power systems that provide it with the necessary power. The investigated ISA includes a twin-symmetrical hydraulic actuation cylinder, two electro-hydraulic servo-valves, and a cleverly constructed set of built-in directional control valves with a feedback system. By obtaining the transient response of the ISA, the output linear motion of the actuating cylinder of the ISA is provided and regulated. By altering the system control settings, a traditional PID controller is created and tuned using Zeigler-approach Nichol's in accordance with the Integral Square Error (ISE) criteria to minimize the difference between the required system output feedback and the desired set input. By using the tuned PID controller, the system's stability and precision needs are guaranteed.
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Frequency Response Of Critical Components Of A Hydraulic Servovalve
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Hydraulic servo systems are characterized by their ability to impart large forces at high speeds and are used in many industrial motion systems. The goal of this paper is to present a mathematical model of a complete hydraulic servo system (solenoid valve, hydraulic valve, actuator, and controller). The model is developed for the system and simulation is carried out with four types of controller namely Proportional (P) control, Proportional-Differential (PD) control, Proportional-Integral (PI) control and PID control. The results of simulation with different controller are discussed and compared.