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missile_data.m
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missile_data.m
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%% Missile Data
%==================================================================
% Useful Constants
%==================================================================
d2r = pi/180; % Conversion Deg to Rad
g = 9.80665; % Gravity [m/s^2]
m2ft = 3.28084; % metre to feet
Kg2slug = 0.0685218; % Kg to slug
%==================================================================
% Atmospheric Constants
%==================================================================
T0 = 288.15; % Temp. at Sea Level [K]
rho0 = 1.225; % Density [Kg/m^3]
L = 0.0065; % Lapse Rate [K/m]
R = 287.0531; % Gas Constant J/Kg/K
gam = 1.403; % Ratio of Specific Heats
P0 = 101325.0; % Pressure at Sea Level [N/m^2]
h_trop = 11000.0; % Height of Troposphere [m]
Vs0 = 340.2787; % Speed of Sound at Sea Level [m/s]
%==================================================================
% Missile Configuration
%==================================================================
S_ref = 0.44/m2ft^2; % Reference area [m^2]
d_ref = 0.75/m2ft; % Reference length [m]
Iyy = 182.5/(Kg2slug*m2ft^2); % Inertia
mass = 13.98/Kg2slug; % Mass [Kg]
Thrust = 10e3; % Thrust [N]
%==================================================================
% Missile Aerodynamics
%==================================================================
% Axial Force Coefficient
aa = -0.3;
% Normal Force Coefficient
an = 0.000103/d2r^3; % [rad^-3]
bn = -0.009450/d2r^2; % [rad^-2]
cn = -0.169600/d2r; % [rad^-1]
dn = -0.034000/d2r; % [rad^-1]
% Moment Coefficient
am = 0.000215/d2r^3; % [rad^-3]
bm = -0.019500/d2r^2; % [rad^-2]
cm = 0.051000/d2r; % [rad^-1]
dm = -0.206000/d2r; % [rad^-1]
em = -1.719; % [s/rad]
%==================================================================
% Define Initial Conditions
%==================================================================
x_ini = 0; % Initial downrange position [m]
h_ini = 20000/m2ft; % Initial altitude [m]
Vs_ini = sqrt((T0-L*h_ini)*gam*R); % Speed of sound eq. for 0m <= h <= 11000m
M_ini = 4; % Initial Mach Number
v_ini = M_ini*Vs_ini; % Initial velocity [m/s]
alpha_ini = 0*d2r; % Initial incidence [rad]
theta_ini = 0*d2r; % Initial Body Attitude [rad]
q_ini = 0*d2r; % Initial pitch rate [rad/sec]
%==================================================================
% Missile Actuators
%==================================================================
wn_fin = 150.0; % Actuator Bandwidth [rad/sec]
z_fin = 0.7; % Actuator Damping
fin_act_0 = 0.0; % Initial Fin Angle [rad]
fin_max = 45.0*d2r; % Max Fin Deflection [rad]
fin_min = -45.0*d2r; % Min Fin Deflection [rad]
fin_maxrate = 50*d2r; % Max Fin Rate [rad/sec]
save('missile_data.mat')