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...

aircraft regarding to the elevator deflection angle is designed. The way how the elevator angle affects pitching motion of the aircraft is pointed out, as well as, how a pitch controller can be applied for the aircraft to reach certain pitch angle. In this digital optimal system, the elevator deflection angle and pitching angle of the plane are considered to be input and output respectively. A ...

The first year of activity has been productive. • We list a total of 21 papers published or submitted by members of the research team and that have been partially supported by our sponsors. • We attended the annual SAAP-Industry meeting on March 5 – 7, 2002, in Hampton, VA. • Langley's FOSS laboratory has generated data on strain tests that is being used as test bed for some fault signature tec...

In the present paper intelligent controllers design methodology is presented to examine their overall performance primarily based on time response specification for controlling Pitch movement of aircraft. The aircraft pitch control system is designed for Linear and Non-linear models and the effect of various nonlinearities is studied based on the overall performance of various controllers in Fl...

Progress in aircraft designs heavily depend on automatic flight control system. Modern aircraft have a wide flight envelope (linear and nonlinear) region. This study considers the design of stability and control augmentation system (SCAS) in high angle of attack region for a modern type aircraft via back stepping method. Because of highly nonlinear phenomena in aerodynamic parameters, a locally...

The next generation (NextGen) transport aircraft configurations being investigated as part of the NASA Aeronautics Subsonic Fixed Wing Project have more control surfaces, or control effectors, than existing transport aircraft configurations. Conventional flight control is achieved through two symmetric elevators, two antisymmetric ailerons, and a rudder. The five control surfaces, reduced to th...

Research into previous flight accidents and investigations of the fault-tolerant flight control (FTFC) strategies used suggest that an aircraft, under many post-failure circumstances, can still achieve a certain level of flight performance using the remaining valid control effectors. However, the control authority or the safe flight envelope of the aircraft will inevitably shrink due to structu...

The emerging flight-by-wire and flight-by-light technologies increase the possibility of enabling and improving aircraft design with excellent handling qualities and performance across the flight envelope. As a result, it is desired to take into account the dynamic characteristics and automatic control capabilities at the early conceptual stage. In this paper, an integrated control-configured a...

In this paper, the use of continuous mathematical models of an aircraft in an aircraft simulator is described. The models are of lower degree and less time-consuming for calculation. Computer implementation of the models capable to work faster and more accurately and efficiently is also described. The suggested approach allows to achieve the required precision at accelerated simulation speed us...