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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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33
code/M3dxdt.m
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@@ -1,22 +1,23 @@
function MxDot = M3dxdt(Mt,missileState,targetState)
%% Missile is a 120 mm Rocket with an IR Seeker
% Compute Missile xDot = [velocity; acceleration]'
g = 9.8066; % acceleration due to gravity
gravity = [0; 0; -g]; % gravity vector
diameter = 0.120; % missile diameter in m.
S = XX; % reference area in m^2
[acousticSpeed,rho] = getRho(missileState);
Mspeed = norm(missileState(4:6));
mach = Mspeed/acousticSpeed;
timeCurve = [XX]'; %seconds
thrustCurve = [XX]'; % Newtons
massCurve = [XX]'; % kg
machCurve = [XX];
dragCurve = [XX];
machCurveB = [XX];
dragCurveB = [XX];
g = 9.8066; % acceleration due to gravity
gravity = [0; 0; -g]; % gravity vector
diameter = 0.120; % missile diameter in m.
S = pi*(diameter/2)^2; % reference area in m^2
[acousticSpeed,rho] = getRho(missileState);
Mspeed = norm(missileState(4:6));
mach = Mspeed/acousticSpeed;
% Transcribed from the provided missile-data plots.
timeCurve = [0 2.8 2.8001 11.6 11.6001 25]'; %seconds
thrustCurve = [6200 6200 1200 1200 0 0]'; % Newtons
massCurve = [31.8 25.1 25.1 20.9 20.9 20.9]'; % kg
machCurve = [0 0.5 0.7 0.9 1.0 1.05 1.1 1.2 1.5 2.0 2.5 3.0];
dragCurve = [0.185 0.180 0.220 0.280 0.330 0.360 0.355 0.330 0.250 0.165 0.110 0.090];
machCurveB = [0 0.5 0.7 0.8 0.9 1.0 1.05 1.1 1.2 1.5 2.0 2.5 3.0];
dragCurveB = [0.150 0.145 0.145 0.160 0.200 0.300 0.315 0.305 0.275 0.205 0.130 0.080 0.045];
if(Mt<=timeCurve(end-1))
Cd = interp1(machCurveB,dragCurveB,mach,'linear','extrap');