Output feedback non-linear decoupled control synthesis and observer design for manoeuvring aircraft

摘要: This paper presents an application of decoupling theory for designing a controller with output feedback in rapid, non-linear aeroplane manoeuvres. For simplicity control law derivation, only momenta caused by aileron, rudder and elevator are considered, forces neglected. class systems, method observer is presented. Using this approach, angle attack sideslip constructed. An approximate obtained neglecting the derivatives roll rate aileron deflection. The synthesized using estimated from observer. Simulated responses closed-loop system, including forces, show that neglected have no significant effects large, simultaneous lateral longitudinal manoeuvres can be precisely performed. shows small effect wind gust.