cfn_rock.m

导弹控制系统的鲁棒控制设计实例

% Coefficients of the rocket model
L              = 1.6;         % m       rocket length
S              = 0.081;       % m^2     reference surface area
x_R            = 0.3;         % m       rocket fins coordinate
%
% Rocket parameters,forces and moments
[m,G,P,J_x,J_y,J_z,x_G,x_C] ...
               = prm_rock(t,V,H); 
Q_a            = c_x*q*S;
Q_c            = c_x_delta_z*abs(delta)*q*S;
Q              = Q_a + Q_c;
Y_alpha        = c_y_alpha*q*S;
Y_delta        = c_y_delta_z*q*S;
m_z_alpha      = (c_x + c_y_alpha)*(x_G - x_C)/L;
m_z_omega_z    = -0.321;                          % 
m_z_delta_z    = c_y_delta_z*(x_G - x_R)/L;
%
% Equation for Theta variations
a_Theta_Theta  = (P + Y_alpha)/(m*V);
a_Theta_delta  = Y_delta/(m*V);
%
% Equation for theta variations
a_theta_dtheta = m_z_omega_z*q*S*L^2/(V*J_z);
a_theta_theta  = m_z_alpha*q*S*L/J_z;
a_theta_delta  = m_z_delta_z*q*S*L/J_z;
%
% Equation for acceleration variations
a_ny1_alpha    = (Q + Y_alpha)/G;
a_ny1_delta    = Y_delta/G;