mu Xuu+ Xww-mg cos 000+ m(wi-qUo) Zuu+ Zww Ziw+ Zgq-mg sin+ Iyyq Muu+ Mww+ Mww+ Mq+ There is no roll/yaw motion, so=0. Control commands△x,△z,and△ MC have not yet been specified
Goal: analyze aircraft longitudinal dynamics to determine if the be- havior is acceptable, and if not, then modify it using feed back control Note that we could (and will)work with the full dynamics model but for now, let's focus on the short period approximate model from
Complementary Filter(CF) Often, there are cases where you have two different measurement sources for estimating one variable and the noise properties of the two measurements are such that one source gives good information only in low frequency region while the other is good only in high frequency region
INERTIAL SENSoRS MoST, IF NoT ALL, INETIAL SEN SORS MEASURE RATES LINE4R R ANGULAR) 6R ACCELERATIONS WHILE THE RATE INFORMATION IS TYPLCALLY VALIO VER LONG PERIODS of TIME) IT MUST BE INTEGRATED To CET
Bachelor of Engineering The State University of Buffalo, 2002 Submitted to the Department of Aeronautics and Astronautics in partial fulfillment of the requirements for the degree of Master of Science in Aeronautics and Astronautics