4. 2. Stability and control theory 07/09/09 States vector Aerodynamic force given by changes in states Stability derivatives Forces, moments, speeds, angular speeds A1 =lateral cyclic pitch, B1 =longitudinal cyclic pitch, θc =collective pitch θT =tail rotor collective. Control vector Change in aerodynamic force given by changes in control Control derivatives Linear differential system
5. 3. Simulation model 07/09/09 Controls vector or States vector States and controls vector Classic linear system Improved linear system for MMLE method
![1. Equations of motions for a rotorcraft ,[object Object],07/09/09 Forces Moments](data:image/gif;base64,R0lGODlhAQABAIAAAAAAAP///yH5BAEAAAAALAAAAAABAAEAAAIBRAA7)