Taken some fixed-wing UAV as the study object, the aircraft movement was broken down into the longitudinal movement and lateral movement according to the linearized small perturbation principle, the longitudinal control law design method was discussed using root locus which belonged to classical control theory. The six degrees of freedom nonlinear model simulation result shows that: the control parameters designed are reasonable, the simulation profile is fully consistent with the setting profile, the control effect of pitch angle loop and altitude loop meets with the indices requirements, the method is mature and reliable, easy to realize in engineering.
Longitudinal Control Law Design and Simulation of Fixed-Wing UAV
Applied Mechanics and Materials ; 241-244 ; 1128-1132
13.12.2012
5 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Landing Longitudinal Control System Design for a Fixed Wing UAV AIAA Paper
British Library Conference Proceedings | 2007
|