By Donald McLean
A whole therapy of computerized flight keep an eye on platforms (AFCS) for fastened wing and rotary wing airplane, this article covers intimately the topic of balance and keep an eye on conception. all of the vital AFC modes are lined and the results 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 keep watch over method engineers and pilots, digital and aeronautical engineers, and people taking classes in flight keep an eye on platforms may well locate this an invaluable textual content.
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Extra resources for Automatic Flight Control Systems
S. of the equation. s. terms involving the first (or even higher) derivatives of any of the state or control variables. Fortunately, w , itself, depends only upon x and u and, therefore, an easy substitution is possible. In eq. 80) the equation for w is given as: Substituting for w in the equation for q yields: Equations of Motion of an Aircraft 44 + ( M , + M,Uo)q - gM,+ sin yoO + (M8E + M G Z ~ ~ ) S E where hi, = ( M u + M,+ZU> MW = ( M w + M,+ZW) M , = (Mq + UoM,) M, = (- gMw sin yo) If there were some other control inputs on the aircraft being considered, say, for example, a change of thrust, 6th, and a deflection of symmetrical spoilers, Ssp, then the order of the driving matrix, B, becomes (4 X 3) and the elements of the matrix become: It must be understood that the state equation is not an unique description of the aircraft dynamics.
7 ADDITIONAL MOTION VARIABLES Even for the straightforward case of straight, steady, wings level, symmetric flight, the designer of AFCSs may be interested in motion variables other than the primary ones of change in forward speed u, in vertical velocity w, in pitch rate q, in pitch attitude 0, in sideslip velocity v, in roll rate p, in yaw rate r , in bank angle 4, and in yaw angle +. Other commonly used motion variables are treated here, with particular regard to the development of their relationship to the primary motion variables.
It a ~ i l lbe shown in Chapter 3 how n, can be determined from the stability derivatives and the equations of motion; thz result obtained there is quoted here for convenience: Usually, for conventional aircraft, Ma E Z, B &,ME,; consequently: n, a = - 2, Uo/g For straight and level flight, at 1g, where CL is the lift curve slope and CL is the coefficient of lift. g. g. 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.
Automatic Flight Control Systems by Donald McLean