Optimal Control Techniques in Aircraft Guidance and Control
نویسندگان
چکیده
منابع مشابه
Optimal Digital Pitch Aircraft Control
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 ...
متن کاملemittance control in high power linacs
چکیده این پایان نامه به بررسی اثر سیم پیچ مغناطیسی و کاوه یِ خوشه گر با بسامد رادیویی بر هاله و بیرونگراییِ باریکه هایِ پیوسته و خوشه ایِ ذرات باردار در شتابدهنده های خطیِ یونی، پروتونی با جریان بالا می پردازد و راه حل هایی برای بهینه نگهداشتن این کمیتها ارایه می دهد. بیرونگرایی یکی از کمیتهای اساسی باریکه هایِ ذرات باردار در شتابدهنده ها است که تاثیر قابل توجهی بر قیمت، هزینه و کاراییِ هر شتابدهند...
Model Problems of Aircraft Guidance in Education Program on Optimal Control and Differential Games
The authors of this talk work at the Institute of Mathematics and Mechanics in Ekaterinburg, Russia. The basic subject of their scientific investigations is differential game theory. Sergey Kumkov has a one-semester course on optimal control at the Physics Department of Urals University. Valerii Patsko reads a one-semester course on optimal control and differential games at the Mathematical Dep...
متن کاملMultidisciplinary Techniques and Novel Aircraft Control Systems
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 contribut...
متن کاملNonlinear Optimal Control Techniques Applied to a Launch Vehicle Autopilot
This paper presents an application of the nonlinear optimal control techniques to the design of launch vehicle autopilots. The optimal control is given by the solution to the Hamilton-Jacobi-Bellman (HJB) equation, which in this case cannot be solved explicity. A method based upon Successive Galerkin Approximation (SGA), is used to obtain an approximate optimal solution. Simulation results invo...
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: International Journal of Aerospace Engineering
سال: 2019
ISSN: 1687-5966,1687-5974
DOI: 10.1155/2019/3026083