Read e-book online Modern Aircraft Flight Control PDF

By Miomir Vukobratovic, Radoslav Stojic

ISBN-10: 3540191194

ISBN-13: 9783540191193

ISBN-10: 3540391223

ISBN-13: 9783540391227

A whole dynamic version of flight dynamics is gifted. in keeping with this version, the inverse challenge and that of the synthesis of programmed movement are solved. a brand new method of decoupled regulate of large-scale nonlinear structures is utilized to dynamic flight regulate. keep an eye on synthesis is played in steps. First the nominal programmed keep an eye on is synthesized utilizing the total version of flight dynamics. This nominal keep an eye on may still detect nominal trajectory below excellent stipulations with out perturbations. on the moment step the monitoring of nominal trajectory is learned. The approach is considered as a collection of decoupled subsystems and for every subsystem neighborhood regulate is synthesized. Then the soundness of the general approach is analyzed and worldwide regulate is brought to compensate coupling between a few of the subsystems. within the booklet a selected number of subsystems is proposed in a case of flight keep an eye on, and the neighborhood and international keep watch over synthesis is gifted. large simulations of flight keep an eye on with diversified keep an eye on legislation also are presented.

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Sample text

A) V e r t i c a l translation: (~ varies). Attitude b) Pitch pointing: v a r i e d at c o n s t a n t cl Direet of vertical v e l o c i t y is held constant of a t t i t u d e at constant during velocity vector rotation. at a constant vector does not rotate. flight path angle The angle of attack of flight path at constant is This mode produces angle of attack a normal a c c e l e r a t i o n out c h a n g i n g angle-of-attack. Vertical Translation-Vertical velocity control at constant pitch attitude 0 V V ~ V~ Fuselage Pointing-Pitch attitude control at constant f l i g h t path angle y ct (~ ct Direct L i f t Control-Vertical f l i g h t path control at constant angle of attack V V v Fig.

105) are i n v e r t i b l e with r e s p e c t to the a s s o c i a t e d u n k n o w n v a r i a b l e in W-map, a time h i s t o r y of the p o s i t i o n vector X ° can be p u s h e d back t h r o u g h the model trol and i n t e r m e d i a t e states. to four, three-axes to o b t a i n r e q u i r e d con- T h a t is, the m o d e l can be m a d e e q u i v a l e n t i n t e g r a t o r string, w i t h the states d e f i n e d by the three-axes position, velocity, a c c e l e r a t i o n and a c c e l e r a t i o n rate v e c - tors.

Namely such problem formulation is correct in the presence of model or parameter uncertainties (for instance aerodynamic forces may not be exactly known). But when applied to a well defined, non-linear (due to inertial forces, kinematic nonlinearities etc) model which is sufficiently exact to represen~ plant behaviour, these techniques lead to unnecessary complex control algorithms and generally to poor performance characteristics. Applicability of linear techniques is limited due to ignoring the effects caused by nonlinearities.

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Modern Aircraft Flight Control by Miomir Vukobratovic, Radoslav Stojic


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