acf_rock.m

导弹控制系统的鲁棒控制设计实例

function [c_x,c_x_delta_y,c_x_delta_z,c_y_alpha,c_z_beta,c_y_delta_z,c_z_delta_y,q] = acf_rock(t,V,H,alpha,beta)
% Aerodynamic coefficients
%
% Fly parameters
[p,ro,M,Tm] = air_data(V,H);
q           = ro*V^2/2;
%
c_x         =  cx_fct(M);
c_x_delta_y =  0.032;
c_x_delta_z =  0.032;
c_y_alpha   =  cy_fct(M);
c_z_beta    = -c_y_alpha;
%
c_y_delta_z = 0.27;
c_z_delta_y = -0.27;