Aircraft Automatic Control System Failure and Flight Safety
نویسندگان
چکیده
منابع مشابه
Evolution of Aircraft Flight Control System and Fly-By-Light Flight Control System
In past, the aircraft control systems were based on conventional methods of mechanical and hydro-mechanical system. The present generation aircraft are using fly-by-wire (FBW) and in future likely to migrate to fly-by-light (FBL) method for aircraft control system. Mechanical & Hydromechanical flight control systems have been replaced by FlyBy-Wire due to increasing speed of modern aircraft. Du...
متن کاملSystem Identification Methods for Aircraft Flight Control Development and Validation
System-identification methods compose a mathematical model, or series of models, from measurements of inputs and outputs of dynamic systems. The extracted models allow the characterization of the response of the overall aircraft or component subsystem behavior, such as actua-tors and on-board signal processing algorithms. This paper discusses the use of frequency-domain system-identification me...
متن کاملAutomatic Flight Control System Design of Level Change Mode for a Large Aircraft
The level change mode is an essential part of large civil aircraft automatic flight control systems. In cruise, with the decrease of the plane’s weight caused by fuel consumption and the influence of bad weather, such as thunderstorms, the level change mode is required to solve this problem. This work establishes a nonlinear model of large aircraft, takes level chan...
متن کاملVision-only Aircraft Flight Control
1 Graduate Research Assistant Email: [email protected] 2 Graduate Research Assistant Email: [email protected] 3 Lockheed Martin Assistant Professor of Avionics Integration Email: [email protected] Abstract Building aircraft with navigation and control systems that can complete flight tasks is complex, and often involves integrating information from multipl...
متن کاملFlight Test of Asac Aircraft Interior Noise Control System
A flight test is described in which an active structural/acoustic control system reduces turboprop induced interior noise on a Raytheon Aircraft Company 1900D airliner. Control inputs to 21 inertial force actuators were computed adaptively using a transform domain version of the multichannel filtered-X LMS algorithm to minimize the mean square response of 32 microphones. A combinatorial search ...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Transport and Aerospace Engineering
سال: 2016
ISSN: 2255-9876
DOI: 10.1515/tae-2016-0002