mmn_rock.m

导弹控制系统的鲁棒控制设计实例

function [M_x,M_y,M_z] = mmn_rock(t,V,H,alpha,beta,omega_x,omega_y,omega_z, ...
                                  delta_x,delta_y,delta_z)                              
% Aerodynamics moments
%
% Construction parameters
L           = 1.6;         % m       rocket length
S           = 0.081;       % m^2     reference surface area
x_R         = 0.3;         % m       rocket fins coordinate
%
% 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);
% 
% Rocket parameters
[m,G,P,J_x,J_y,J_z,x_G,x_C]   = prm_rock(t,V,H);
%
m_x_alpha   = 0.004;
m_x_beta    = 0.004;
m_x_omega_x = -0.396; 
m_y_omega_y = -0.321; 
m_z_omega_z = -0.321;  
m_y_beta    = (c_x - c_z_beta)*(x_G - x_C)/L; 
m_z_alpha   = (c_x + c_y_alpha)*(x_G - x_C)/L;
%
M_x_f = (m_x_alpha*alpha + m_x_beta*beta)*q*S*L;
M_y_f = m_y_beta*beta*q*S*L;
M_z_f = m_z_alpha*alpha*q*S*L;
%
M_x_d = m_x_omega_x*omega_x*q*S*L^2/V;
M_y_d = m_y_omega_y*omega_y*q*S*L^2/V;
M_z_d = m_z_omega_z*omega_z*q*S*L^2/V;
%
M_x_a = M_x_f + M_x_d;
M_y_a = M_y_f + M_y_d;
M_z_a = M_z_f + M_z_d;
%
m_x_delta_x = 0.015;
m_y_delta_y = -c_z_delta_y*(x_G - x_R)/L;
m_z_delta_z = c_y_delta_z*(x_G - x_R)/L;
%
M_x_c = m_x_delta_x*delta_x*q*S*L;
M_y_c = m_y_delta_y*delta_y*q*S*L*cos(beta);
M_z_c = m_z_delta_z*delta_z*q*S*L*cos(alpha);
%
M_x = M_x_a + M_x_c;
M_y = M_y_a + M_y_c;
M_z = M_z_a + M_z_c;