Multidisciplinary Techniques and Novel Aircraft Control Systems
نویسندگان
چکیده
The Aircraft Morphing Program at NASA Langley Research Center explores opportunities to improve airframe designs with smart technologies. Two elements of this basic research program are multidisciplinary design optimization (MDO) and advanced flow control. This paper describes examples where MDO techniques such as sensitivity analysis, automatic differentiation, and genetic algorithms contribute to the design of novel control systems. In the test case, the design and use of distributed shapechange devices to provide low-rate maneuvering capability for a tailless aircraft is considered. The ability of MDO to add value to control system development is illustrated using results from several years of research funded by the Aircraft Morphing Program.
منابع مشابه
Optimal nonlinear control of flight faults in manned aircrafts in the presence of fault and failure of control actuato
Control actuators' faults are among the major reasons to lose aircraft control while flights. The plane dynamics is severely dependent upon faults and errors in flight control systems and if the reformed control order is not issued by the fault tolerant controller there would be unpleasant outcomes such as inconsistency and the reduction of system performance and some dreadful aerial accide...
متن کاملFlying Qualities Constraints in the Multidisciplinary Design Optimization of a Supersonic Tailless Long Range Aircraft
The increased complexity of next generation aircraft has popularized Multidisciplinary Design Optimization (MDO) as an aircraft design tool. However, MDO efforts consistently neglect aircraft stability and control analyses beyond simple static assessments. Not only does this limit the potential of the MDO to identify an optimal design, but it also fails to assess the MIL-STD or FAR handling qua...
متن کاملOscillation Control of Aircraft Shock Absorber Subsystem Using Intelligent Active Performance and Optimized Classical Techniques Under Sine Wave Runway Excitation (TECHNICAL NOTE)
This paper describes third aircraft model with 2 degrees of freedom. The aim of this study is to develop a mathematical model for investigation of adoptable landing gear vibration behavior and to design Proportional Integration Derivative (PID) classical techniques for control of active hydraulic nonlinear actuator. The parameters of controller and suspension system are adjusted according to be...
متن کاملDesigning and Modeling a Control System for Aircraft in the Presence of Wind Disturbance (TECHNICAL NOTE)
This paper proposes a switching adaptive control for trajectory tracking of unmanned aircraft systems. The switching adaptive control method is designed to overcome the wind disturbance and achieve a proper tracking performance for control systems. In the suggested system, the wind disturbance is regarded as a finite set of uncertainties; a controller is designed for each uncertainty, and a per...
متن کاملAutomatic Landing Guidance Systems and Design of an Optimal Landing Control System
Guidance and control of aircraft in the landing phase imposes extra pilot work loads, hence application of automatic landing control systems is of great importance. In this study automatic landing control systems are introduced and an optimal landing control system is designed. The control system performance criteria are based on minimum control effort. The designed system is simulated for a tr...
متن کامل