Equations of Motion: rigid body dynamics, coordinate transformation, Euler angle & quaternion formulation – Dynamics of Generic Fixed Wing Aircraft: 6-DoF equations of motion, linearized equations of motion, linearised longitudinal & lateral equations, aerodynamic derivatives – LTI sys- tem basics – Stability of Uncontrolled Motion: linearized longitudinal & lateral dynamics, modes of motion – Response to Control Inputs: transfer function, step response & frequency response charac- teristics – Feedback Control: stability augmentation, PID control, root-locus technique for controller design – Introduction to modern control theory.
Same as Reference
Etkin, B. and Reid, L. D., Dynamics of Flight: Stability and Control, 3rd ed., Wiley (1996).
Phillips, W. F., Mechanics of Flight, 2nd ed., John Wiley (2009).
Nelson, R. C., Flight Stability and Automatic Control, 2nd ed., Tata McGraw-Hill (1997).
Cook, M., Flight Dynamics Principles: A Linear Systems Approach to Aircraft Stability and Control, 3rd ed., Elsevier (2012).
Stevens, B. L. and Lewis, F. L., Aircraft Control and Simulation, 2nd ed., Wiley (2003).
Stengel, R. F., Flight Dynamics, Princeton Univ. Press (2004).
Course Outcomes (COs):
CO1: Formulate the 6 DOF nonlinear and linearized equations of a conventional aircraft in flight about the equilibrium states.
CO2: Develop the competency to infer the stability and control derivatives of any given aircraft.
CO3: Deduce and analyze the longitudinal and lateral-directional modes.
CO4: Assess the handling qualities of a conventional aircraft.
CO5: Derive the transfer functions for aircraft motion for different control inputs.
CO6: Implement stability augmentation system and Autopilot for a conventional aircraft the using classical and modern control techniques.