Clarification of "Turn Performance of Aircraft"
نویسنده
چکیده
Arecent noteanalyzed theminimum turning radius ofanairplane intermsofitsai_peedandangleof bank. Unfortunately, somemisccyaceptions concerning theunderlying physics wereinlroduced. Thisnoteis intended to clarifythoseareas.
منابع مشابه
Study the effect of nano Al2O3 and nano graphene ceramic additives on the aircraft anti-icing/de-icing fluids
In the present study, the effect of nano Al2O3 and nano graphene ceramic additives in optimizing performance and improving thermophysical properties of aircraft anti-icing/de-icing fluids was investigated. Nanoparticles were characterized by TEM, SEM and XRD methods. The thermal conductivity, surface tension and dynamic viscosity of the hybrid nanofluids were experimentally assessed for tempera...
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 کاملRobust Adaptive Attitude Stabilization of a Fighter Aircraft in the Presence of Input Constraints
The problem of attitude stabilization of a fighter aircraft is investigated in this paper. The practical aspects of a real physical system like existence of external disturbance with unknown upper bound and actuator saturation are considered in the process of controller design of this aircraft. In order to design a robust autopilot in the presence of the actuator saturation, the Composite Nonli...
متن کاملOptimized Fuzzy Logic for Nonlinear Vibration Control of Aircraft Semi-active Shock Absorber with Input Constraint (TECHNICAL NOTE)
Landing impact and runway unevenness have proximate consequence on performance of landing gear system and conduce to discomfort of passengers and reduction of the pilot’s capability to control aircraft. Finally, vibrations caused by them result in structure fatigue. Fuzzy logic controller is used frequently in different applications because of simplicity in design and implementation. In the pre...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
عنوان ژورنال:
- SIAM Review
دوره 38 شماره
صفحات -
تاریخ انتشار 1996