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Implement atmosphere and dynamics data

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This commit is contained in:
deamonkai
2026-03-28 16:33:32 -05:00
parent 563dbee7eb
commit c0f275caeb
9 changed files with 127 additions and 92 deletions
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11
code/Interceptor_3DOF.m
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@@ -1,8 +1,8 @@
%% * Interceptor 3DOF*
%% Executive
clear all; clc;
t0 = 0; % Initial time. Target launch time.
tCommit = XX.; % Commit time (sec)
t0 = 0; % Initial time. Target launch time.
tCommit = 50.; % Commit time (sec)
sigEl = 0; % Missile elevation angle standard deviation
maxTime = 150; % estimated maximum engagement time in sec
dt = 0.01; % integration interval (sec)
@@ -21,9 +21,10 @@ Toutput_vector(1,:)= [t0,targetState',TxDot(4:6)'];
%% Missile initial conditions
Mp0 = [0; 0; 0]; % Missile initial position in ENU frame (m)
Mspeed0 = 1.e-06;% Missile initial speed in ENU frame (m/sec); must be non-zero for unit vector calculation.
Maz = XX; Mel = XX; % Missile launch azimuth and elevation (deg).
Mv0 = Mspeed0*[cosd(Mel)*cosd(Maz); cosd(Mel)*sind(Maz); sind(Mel)];%initial velocity vector in ENU frame
Mspeed0 = 1.e-06;% Missile initial speed in ENU frame (m/sec); must be non-zero for unit vector calculation.
Maz = 0; % Assumed coplanar engagement geometry until a source doc says otherwise.
Mel = 40; % Missile launch elevation (deg).
Mv0 = Mspeed0*[cosd(Mel)*cosd(Maz); cosd(Mel)*sind(Maz); sind(Mel)];%initial velocity vector in ENU frame
missileState = [Mp0; Mv0]; % Missile state vector in ENU frame (m. and m/sec.)
Moutput_vector(1,:)= [t0,missileState', 0, 0, 0];
missileSpeed(1,:) = [t0,norm(missileState(4:6))];