23.Engineering Management by John G. Webster (Editor)

By John G. Webster (Editor)

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1, wherein vehicle stability is dependent upon active feedback control, damage or subsystem failures can easily cause the vehicle to become uncontrollable by the pilot in a matter of seconds or less. As an example, Bodson and Groszkiewicz (22) offer a treatment of this problem using model-reference approaches. The attractiveness of adaptive control is its promise of providing control laws for aircraft applications in which significant and unpredictable changes in vehicle characteristics may occur.

On substituting expressions such as Eq. (14) into the linearized form of 11, a set of linear ordinary differential equations results. Mass and moment-of-inertia terms are typically subsumed into the linear air reaction terms, as, for example, The quantities X u and Lp are referred to as mass- and moment-normalized stability derivatives, and simply as stability derivatives in what follows. The values of the stability derivatives are a function of the AIRCRAFT DYNAMICS AND CONTROL 9 aircraft configuration and the flight condition, the latter being essentially specified by the Mach number and altitude where the equilibrium condition is defined.

Fig. 11. Flight control system for the example, with all loops closed. Gi (z). A number of different emulation techniques exist, each dependent upon the type of discrete integration scheme that the digital computer uses to approximate the Laplace operator 1/ s. The most common of these is the bilinear (Tustin) transform (15). In this approach, the discrete transfer functions suitable for implementation on the digital flight control computer are obtained in the z domain. The z transform of a string of discrete numbers x(kT) is defined as with the infinite sum on the right-hand side amenable to representation as a ratio of polynomials in z, much as the integral on the right-hand side of Eq.

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