- #1
CptHeadCrab
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Homework Statement
A satellite is orbiting Earth with a period time of T=110 min.
At the ascending node, the state vector of the satellite is rAN =[4500 7100 ?]T km
At the northernmost latitude, the state vector of the satellite is rn=[1700 ? 7000]T km. The question marks imply that the information is missing.
The question asks to complete the vectors, and find orbit's elements: a, e, i, ω, Ω
Homework Equations
Given a state vector of a satellite, rAN =[x y z]T km
the latitude is:
there is also the following Kepler rule:
and the 2 body problem generalized solution:
where:
though i don't think the last two would help solving the missing vector.
The Attempt at a Solution
Well completing the rAN is quite easy as it's known that the ascending node is at the equator plane, thus: rAN =[4500 7100 0]T km.
It is also known that the latitude of the northernmost point is the inclination angle (i).
Finding a (the semi major axis) is possible by knowing period time:
was trying to use cross product of rAN and rn and thought that the angle between them is the latitude, but then i figured out i was completely wrong.
I think there's some vector calculus to be done but not sure what exactly.
Your help is appreciated.