In order to meet the requirements of long range obstacle measurement of tower crane safety warning system and accurately estimate time of flight (TOF), an ultrasonic long range measurement system is designed and a mathematical model of echo envelope is established in this paper. Experimental data of long range obstacle measurement were collected and analyzed by using traditional threshold metho...

This paper presents an investigation into the controllability for an aircraft of seamless aeroelastic wing. The research is aimed at the design of control laws for the aircraft rolling by actively operating a pair of an unconventional hingeless flexible leading and trailing control surfaces at different flight speed. The main challenge is how to achieve a specified rolling rate for the aircraft...

Two unsteady Reynolds-averaged Navier-Stokes solvers are used to compute the rotor airloads on the UH-60A rotorcraft at several flight conditions across the flight envelope. One code, OVERFLOW, solves the flow equations using either structured grids, or a combination of structured and Cartesian grids. The other solver, FUN3D, uses unstructured grids. Both flow solvers are coupled to the same ro...

Abstract High performance aircraft of the future will be designed lighter, more maneuverable, and operate over an ever expanding flight envelope. One of the largest differences from the flight control perspective between current and future advanced aircraft is elasticity. Over the last decade, dynamic inversion methodology has gained considerable popularity in application to highly maneuverable...

The atmospheric disturbances affect not only flying qualities of an airplane but also flight safety. According to flight records, most aircraft accidents occurred during final approach or landing. If the flight conditions are beyond the preset envelope, the automatic landing system (ALS) is disabled and the pilot takes over. An inexperienced pilot may not be able to guide the aircraft to a safe...

Wing morphing as a means to continuously modify wing geometry is employed in numerical simulation order act upon aerodynamic performance cruise flight. In this flight regime, the interaction of shock wave and boundary layer instabilities can lead transonic buffet, coordinated motion both detached layer. This flow instability induces unsteady forces on which may induce dip-flutter or cause stall...

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...