If I would be given a R and a V vector and I would have to find orbital elements like... (a=semi-major axis)(eccentricity)(inclination)(right ascension of the ascending node)(argument of perigee)(true anomaly). After I defined the vectors and found the magnitudes I was trying to write out my equations but I guess matlab didn't like it. If you could look at my code and point me in the right direction I would appreciate it. I had quite a few of errors just to keep ending my functions over and over again?
First, solve for the angular momentum: h⃗ =r⃗ ×v⃗ h
The eccentricity vector is then: e⃗ =(v2−μ/r)r⃗ −(r⃗ ⋅v⃗ )v⃗
a=−μ/2E
i=cos−1hKhi = cos−1hKh
Ω=cos−1nInΩ = cos−1nIn
ω=cos−1n⃗ ⋅e⃗ neω = cos−1n→⋅e→ne
ν=cos−1e⃗ ⋅r⃗ er
R= [-7953.8073 - 4174.5370 - 1008.9496];
v= [3.6460035 - 4.9118820 - 4.9193608];
h=cross(R,v);
nhat=cross([0 0 1],h)
r=norm(R);
mu=3.986*10^5
energy = mag(v)^2/2-mu/mag(R)
e = mag(evec)
evec = ((mag(v)^2-mu/mag(R))*R-dot(R,v)*v)/mu
if abs(e-1.0)>eps
a = -mu/(2*energy)
p = a*(1-e^2)
else
p = mag(h)^2/mu
a = inf
end
i = acos(h(3)/mag(h))
Omega = acos(n(1)/mag(n))
if n(2)<0
Omega = 360-Omega
argp = acos(dot(n,evec)/(mag(n)*e))
end
if e(3)<0
argp = 360-argp
nu = acos(dot(evec,R)/(e*mag(R))
end
if dot(R,v)<0
nu = 360 - nu
end
