A rate demand controller, designed using RIDE (robust inverse dynamics estimation) for a thrust vectoring system, high performance fighter aircraft, has been successfully tested. Non-linear operation of the controller is shown between speeds of Mach 0.3 and 0.75 and at angles of attack between -10 deg of angle and 50 deg of angle. The thrust vectoring system has been demonstrated in flight conditions where insufficient aerodynamic motivator control power exists. The results from non-linear simulation studies involving post-stall manoeuvres have demonstrated that the RIDE control laws produce responses which closely match those achievable with ideal inverse dynamics control. The simplicity of the design method has facilitated the development of a control law capable of operating over a wide range of flight conditions, giving the aircraft a set of response characteristics easily specified by the designer. RIDE promises to produce dependable controllers given that only the control effectiveness matrix, for which accurate estimates should be available, is needed to calculate the gain matrices and the dynamic inverse input term. The closed loop system is tolerant to errors in the motivator effectiveness estimate as demonstrated in the examples shown. The system will be robust to aircraft non-linearities as the controller is independent of knowledge of the aircraft's aerodynamic derivates.
Control law design for a thrust vectoring fighter aircraft using robust inverse dynamics estimation (RIDE)
Auslegung einer Schubvektorsteuerung für Militärflugzeuge unter Anwendung eines stabil-inversen dynamischen Verfahrens
1996
11 Seiten, 7 Bilder, 3 Tabellen, 21 Quellen
Article (Journal)
English
Militärflugzeug , Flugeigenschaft , Antriebsanlage , Schubvektorsteuerung , Prozessmodell , dynamisches Verhalten , Anstellwinkel (Tragflügel) , Flugregelung , Aerodynamik , Manövrierfähigkeit , Abreißen der Strömung , Auslegung (Dimension) , Modellsimulation , Eigenfrequenz , Redundanz , fehlertolerantes System
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