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Chapter 4

Chapter 4 Dynamical Equations for FlightVehiclesThese notes provide a systematic background of the derivation of the equations of motionfor a flight vehicle, and their linearization. The relationship between dimensional stabilityderivatives and dimensionless aerodynamic coefficients is presented, and the principalcontributions to all important stability derivatives for flight vehicles having left/rightsymmetry are Basic Equations of MotionThe equations of motion for a flight vehicle usually are written in a body -fixed coordinate is convenient to choose the vehicle center of mass as the origin for this system, and the orientationof the (right-handed) system of coordinate axes is chosen byconvention so that, as illustrated inFig.

Figure 4.2: The Euler angles Ψ, Θ, and Φ determine the orientation of the body axes of a flight vehicle. (a) Yaw rotation about z-axis, nose right; (b) Pitch rotation about y-axis, nose up; (c) Roll rotation about x-axis, right wing down. The orientation of the body axis system is specified by starting with the inertial system, then, in

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