AE3613 HW 6 Problem 1

function AE3613HW6P1()
%AE3613 Homework #6
%Christopher Bates
%Due 27 Oct 2016

%Problem Number 1
%Setting variables
rpd = 3.14159/180; % radians per degree
minperhr = 60;
secpermin = 60;
TOFhr = 2.6297; %Time of flight in hours
TOFmin = TOFhr * minperhr;
TOFsec = TOFmin * secpermin;
%%%%%%From HW5 answer%%%%%%
n = 4.3633*10^(-4); % = sqrt(mu/a^3)
e = 0.4528; % e = eccentricity
asd = 220; % Dr.P solution in degrees

% Using MATLAB's Solve function
        %E1 = eccentric anomaly
syms E1
eqn = ((E1-e*sin(E1))==n*TOFsec); %Kepler's Eqn
%Solution in Radians = 3.8397
solE1 = solve(eqn,E1);

%Solution in degrees
solutiondeg = solE1/rpd;  % = 219.997 degrees

%Calculating error using Dr.P's values

error = (asd-solutiondeg)/asd;

%Percent error = 1.4118e-03% error
i = error*100;
j = solE1;
fprintf('\nThe calculated eccentric anomaly is: %12.5e\n',j);
fprintf('The calculated percent error is: %16.4e %% \n',i);

%%%%OUTPUT%%%%
%The calculated eccentric anomaly is:   3.83967e+00
%The calculated percent error is:       1.4118e-03 %
end