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As civil aircrafts require high requirement of reliability, the flight control system should make airplane safe at least when failure occurs. This paper proposed an active fault-tolerant control (AFTC) strategy for civil aircraft with ailerons stuck at different degrees. The baseline control law was designed based on linear quadratic regulator (LQR) to guarantee lateral control stability and performance...
In order to realize condition-based maintenance of aircraft and therefore ensure flight safety, it is significant to timely and accurately determine of remaining useful life (RUL) of the aviation hydraulic piston pump. Failure resulting from hydraulic oil contamination is the main failure mode of piston pump, thus a life prediction model based on contaminant sensitivity is established for the aviation...
This paper designs an active fault-tolerant controller based on Model Reference Adaptive Control (MRAC) and Linear Quadratic Regulator (LQR) for horizontal stabilizer asymmetric damaged large aircraft. Defining the parameters of damaged horizontal stabilizer, MRAC detects healthy result of the aircraft and switch HA to EHA. LQR regulator accepts the damage ratio of horizontal stabilizer and regulate...
To ensure the reliability and safety, hydraulic/electro-hydrostatic dissimilar dual redundant actuation system is widely used in advanced civil aircraft. Considering the change of dynamic performance of hydraulic actuator (HA) and electro-hydrostatic actuator (EHA), this paper establishes performance reliability model based on parameter drift model, and presents the calculation methods of performance...
The change of center of gravity (CG) of aircraft is influenced by fuel system greatly. In this paper, according to all of failure mode of fuel system 6 fuel transfer mode were discussed. Based on 6 fuel transfer mode, the models of CG of aircraft were established. The fuel system of military aircraft was token an example. The law of change of (CG) during fuel consumption was obtained. The influence...
Built-in-Test (BIT) is widely used in aircraft to improve the system's reliability and safety. However, the false alarm of BIT makes it difficult to practical. After investigating the mechanism of false alarm of BIT from sensor failure, signal coupling, unreasonable threshold and uncertainty of fault decision method, an improved fault diagnosis method integrated with sensor redundancy configuration,...
Axial piston pump is an important component in hydraulic system, which is widely applied in aeronautic hydraulic energy system. The performance of piston pump directly influences the operation of hydraulic system. This study puts emphasis up on the common failure mechanism analysis of pump. Then the model of piston pump was established in AMESim. Considering the characteristic of the fault condition,...
This paper proposes adaptive robust controller for electrical load simulator with estimation of parameters uncertainties and updating the model parameters to minimize model error Fuzzy logic is used to estimate the total disturbance which is function of extra torque and mechanical parameters variation. Estimation algorithm for parameters variation is derived from voltage and torque balance equations...
Aiming at the problems of vibration on hydraulic pipe in aircraft, using math modeling and simulation is a quite efficient and effective method in theory. In this paper, the 14-equation Fluid-Structure Interaction (FSI) with influence of viscous friction is established for modeling the pipe and fluid. By using the Transfer Matrix Method (TMM), the components and pipelines are connected to get the...
Electro-Hydrostatic Actuator (EHA) is an integrated system whose performance is related to many disciplines, such as electrics, mechanics, hydraulics and control. In order to achieve the performance optimization, the best way is to balance the multidisciplinary and realize the integrated optimization. This paper focuses on the collaborative design and simulation based on commercial software AMESim...
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