By John G. Webster (Editor)
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The reader should note that these equations have been simplified by ignoring certain stability derivatives that are typically small. For complete equations see any of the aircraft stability and control texts in the bibliography. Longitudinal Equations. The n appearing in the summations represents the number of aerodynamic control effectors being employed. Also note that x˙ and z˙ are not perturbation quantities, as they represent velocity components of the aircraft’s center of mass, expressed in earth-fixed axes.
Bounded responses to bounded inputs) requires that the poles of the transfer function g11 (s) lie in the left half of the complex s plane. There is a fundamental, or natural, mode of motion associated with each real pole and each pair of complex conjugate poles of the g11 (s). The actual response to a control actuation is a superposition of these fundamental modes. The zeros of the transfer function determine the extent to which each mode enters into the response of each output variable. The elements of the matrices A and B of Eqs.
R. A. Hess Stability and turbulence, in R. C. ), The Engineering Handbook, Boca Raton, FL: CRC Press, 1996, Chap. 173. 5. D. T. McRuer I. Ashkenas D. Graham Aircraft Dynamics and Automatic Control, Princeton, NJ: Princeton University Press, 1973. 6. R. K. Heffley et al. A Compilation and Analysis of Helicopter Handling Qualities Data, Vol. 1: Data Compilation, NASA CR-3144, 1979. 7. M. B. ) Advances in Aircraft Flight Control, London: Taylor and Francis, 1996. 8. M. Waszak D. K. Schmidt Flight dynamics of aeroelastic vehicles, J.
23.Engineering Management by John G. Webster (Editor)