(adsbygoogle = window.adsbygoogle || []).push({}); 1. The problem statement, all variables and given/known data

An earth satellite has a speed of 7km/s and a flight path angle of 15 degree when its radius is 9000km calculate the true anomaly and eccentricity of the orbit.

2. Relevant equations

r=h^2/u(1+ecostheta)

3. The attempt at a solution

The problem statement just doesn't seem provided enough information. The direction to the solution should deal with lagrange coefficients. Express r and v in the standard earth refrence frame using flight pitch angle, then transfer them to the perifocal fame.

Then in perifocal fame:

h=r cross v (in perifocal fame)

e=1/u*(r cross v) -r(vector)/r

But i don't know how to find the r and v vectors in the standard earth ref frame :(

correct me if my approach is incorrect >.>

the answer given is theta=83.35degree, e=0.2785

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# [spacefight mechanics]how to find true anomaly and eccentricity?

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