Sim files and calculations

Calculations.m

+Re = 6378;
+mu = 398600.4;
+
+a_p = 638+Re;%parking orbit
+a_Leo = 550+ Re;
+a_Geo = 35786 +Re;
+
+i_p = 46 *pi/180; %average inclnation
+i_geo = 0;
+i_leo = 53* pi/180;
+
+A = 0.00001; %Based on thrusters 
+
+deltaT = -sqrt(mu)/(A*sqrt(a_p)) + sqrt(mu)/(A*sqrt(a_Leo))
+deltaV = A*deltaT; %km/hr
+
+deltaTHours = deltaT/(3600);
+deltaTDays = deltaT/(24*3600);
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SputnikSim.m

+Re = 6378;
+mu = 398600.4;
+
+R0 = [-8.058685464116713e+002;...
+-4.135050989428283e+003;...
+5.071447347723579e+003];
+
+V0 = [6.04068079277917;
+3.52422658592595;
+3.83339310219652];
+
+X0 = [R0; V0];
+
+t0 = 0;
+tstep = 20;
+tfinal = 96.2*60*5;
+
+tspan = t0: tstep: tfinal;
+
+options = odeset('AbsTol', 1e-6, 'RelTol', 1e-8);
+[Tp, Xp] = ode45(@newton, tspan, X0, options);
+
+figure(1); hold off;
+plot3(Xp(:,1), Xp(:,2), Xp(:,3), 'g-', 'linewidth', 3);
+xlabel('x (km)');
+ylabel('y (km)');
+zlabel('z (km)');
+
+[XS, YS, ZS] = sphere(30);
+figure(1);
+hold on;
+surf(XS*Re, YS*Re, ZS*Re);
+axis([-1e4, 1e4, -1e4, 1e4, -1e4, 1e4]);
+
+figure(2);
+plot(Tp, sqrt(Xp(:,1).^2 + Xp(:,2) + Xp(:,3).^2) - Re,'linewidth', 3);
+ylabel('h = r-R_e (km)')
+xlabel ('t (sec)')
+
+
+

newton.m

+function Xdot = newton(t, X)
+
+mu = 398600.4405;
+
+r= X(1:3);
+v = X(4:6);
+
+Xdot(1:3) = v;
+rn = norm(r);
+Xdot(4:6) = -mu/rn^3*r;
+
+Xdot = Xdot(:);
+
+return;
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