frc_rock.m

导弹控制系统的鲁棒控制设计实例

function [Q,Y,Z] = frc_rock(t,V,H,alpha,beta,delta_x,delta_y,delta_z)
%
% Aerodynamic forces
%
% Construction parameters
S           = 0.081;      % m^2     reference surface area
%
% Aerodynamic coefficients
[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);
%
Q_a  = c_x*q*S;
Y_a  = c_y_alpha*alpha*q*S;
Z_a  = c_z_beta*beta*q*S;
%
Q_c = (c_x_delta_y*abs(delta_y) + c_x_delta_z*abs(delta_z))*q*S;
Y_c = c_y_delta_z*delta_z*q*S;
Z_c = c_z_delta_y*delta_y*q*S;
%
Q = Q_a + Q_c;
Y = Y_a + Y_c;
Z = Z_a + Z_c;