close all
clear all

m = 1000;  %kg
a = 1.53/2;  %radius (m)
b = 35/39.4;  % height (m)
g = 9.8;  %m/s^2
rho = 1025; %kg/m^3


Vol = pi*a*a*b; %m^3

W = rho*g*Vol-m*g;
u = rho*Vol;  % Added mass coeff = 1 (flat circular plate)


t = 0:.05:2.0;
n = 1;
for V=-1:-1:-4
y(n,:) = (.5*W/(m+u))*t.^2+V.*t;
vel(n,:) = (W/(m+u)).*t+V;
n = n+1;
end

plot(t,y)

legend('Vel = -1 m/s','Vel = -2 m/s','Vel = -3 m/s','Location','southwest');


foo = axis;

foo(4) = 0;
axis(foo);

xlabel('time (seconds after anchor impact)');
ylabel('meters');
foo = sprintf('Landing Transient of Termination after Anchor Touchdown \n Inertial Considerations only, Drag neglected \n m = %d kg, %2.1f m X %2.1f m cylinder',m,2*b,2*a);
title(foo);


print -depsc2 'LandingTransient'