hydraulic system which drives a third electrical generator. plane requires control system reliability approaching that of the basic airframe. Ryder Boeing Commercial Airplane Company The constraint of requiring airplanes to have inhepent aerodynamic stability can be removed by using active control systems. Performances are evaluated through state-of-the-art metrics, showing promising results and providing the basis towards future applications on real in-flight data. The first electrical flight control system for a civil aircraft was designed by Aerospatiale. But back in the day even large jets had mechanical flight control systems that were later transitioned into Hydro-Mechanical flight controls that used hydraulic. REDUNDANCY OF HYDRAULIC FLIGHT CONTROL ACTUATORS C. The algorithm is at first theoretically discussed, and then tested against several degradation patterns. Results of both the simulation and the experimental work are used to select a suitable feature, then implemented within the prognostic framework based on particle filtering. The study is performed by means of a high-fidelity simulation model supported by experimental activities. The flight test program is described, and actuator performance is shown to be very close to that of the standard hydraulic actuator it replaced. This paper presents a case study on the design of a prognostic system for this degradation mode, in the context of a wider effort toward the definition of a prognostic framework suitable to work on in-flight data. The architecture of the EMA system is discussed, as well as its integration with the F/A-18 Flight Control System.
The primary flight controls consist of actuators that. The occurrence of excessive internal leakage within the EHSAs is one of the most common causes of return from the field of flight control actuators, making this failure mode a priority in the definition of any dedicated PHM routine. Todays flight controls of large commercial aircraft are controlled mainly by hydraulic actuators. Combining the expected service life of a commercial aircraft with the fact that electro-hydraulic technology is employed in the vast majority of currently in-service aircraft and is planned to be used on future platforms as well, the development of an effective Prognostic and Health Management (PHM) system could provide significant advantages to fleet operators and aircraft maintenance, such as the reduction of unplanned flight disruptions and increased availability of the aircraft. Electro-hydraulic servo-actuators (EHSAs) are currently considered the state-of-the art solution for the control of the primary flight control systems of civil and military aircraft.
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