Aeronautical Engineering

Automatic Flight Control Systems by Donald McLean

By Donald McLean

An entire therapy of computerized flight regulate structures (AFCS) for mounted wing and rotary wing plane, this article covers intimately the topic of balance and regulate conception. all of the important AFC modes are coated and the consequences of atmospheric turbulance and structural flexibility of the air body upon the functionality of AFCS are taken care of. leader engineers, flight dynamics engineers, flight regulate procedure engineers and pilots, digital and aeronautical engineers, and people taking classes in flight regulate structures might locate this an invaluable textual content.

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6. Using the stability axis system, in which W o = 0 and e0= yo, eq. 71) may be expressed as: + Zww + Uoq - g sin yo0 + ZsE8E 4 = MUu + MWw + MGw f M,q + M 6 E 8 ~ w = Z,u whereas eq. 6 Direction of stability axes with respect to the relative wind. (a) Steady flight. (b) Perturbed flight. For Steady Manoeuvring Flight Conditions + = rlcos yo The cross-product inertia terms which appear in eq. 81) can be eliminated by a simple mathematical procedure: the use of primed stability derivatives. By ignoring second order effects, the cross-product of inertia terms are taken into account in the following primed stability derivatives: LkA = LsA + ZBNaA NgA = NZiA + I A L s ~ LkR = LgR + zBNaR NkR = NsR + ZALFiR in which Then eq.

T. and&. GRAHAM. 1981. Eighty years of flight control: triumphs and pitfalls of the systems approach. J . Guid. and Cont. 4(4): 353-62. NEUMARK, S. 1943. The disturbed longitudinal motion of an uncontrolled aeroplane and of an aeroplane with automatic control. ARC R&M 2078. January. OPPELT, W. 1976. An historical review of Autopilot development, research and theory in Germany. J. Dyn. , Meas. and Cont. 98(3): 215-23. S. 1 INTRODUCTION If the problems associated with designing an AFCS were solely concerned with large area navigation then an appropriate frame of reference, in which to express the equations of motion of an aircraft, would be inertial, with its centre in the fixed stars.

G. and I, is measured positive downwards. Heading angle, X, is defined as the sum of sideslip, P, and yaw angle, q. 1 The State Equation A state equation is a first order, vector differential equation. It is a natural form in which to represent the equation of motion of an aircraft. Its most general expression is: 42 Equations of Motion of an Aircraft E Rn is the state vector, u E Rm is the control vector. The elements of the vector x are termed the state variables and the elements of the vector u the control input variables.

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