Synthesis of minimum time aircraft body attitude control at high angles of attack

• Autorzy: Chanov O. , Mirny D.
• Konferencja: Proceedings of the Third Seminar on Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education/seminar(III; 23-25.11.1998; Warszawa, Polska)
• Języki publikacji: EN

Abstrakty

EN

The problem of minimum time transition from given initial to given final values of angles of attack and bank angles is considered for simple model of movement, in which control variables are rates of variation of angle of attack and of bank angle. Control limitations dependent on angle of attack are imposed which is important at high angles of attack ( it is known that efficiency of aerodynamic controls at high angles of attack can be low). The problem is solved with maximum principle usage. It is shown, that in this problem there are the regular and special solutions resulting from necessary conditions of maximum principle, and also irregular solutions which cannot be formally derived from these conditions. Results of calculations are brought. Three types of the solutions generate in field of extremals the appropriate three areas, inside which extremals have various character. On the basis of the analysis of field of extremals the simple synthesis of optimum control is received.

Słowa kluczowe

EN

aircrafts; attitude control; attack

PL

samoloty; pozycja kontroli lotu; atak

• Wydawca: Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology
• Czasopismo: Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics
• Rocznik: 1998
• Tom: nr 8
• Strony: 97--102
• Opis fizyczny: Bibliogr. 3 poz., tab., wykr.

Twórcy

autor

Chanov O.

autor

Mirny D.

• Central Aerohydrodynamic Institute (TsAGI) named after N. E. Zhukovsky, Russia