this problem deal with classical orbit parameters. a bold letter indicates a vector. ex:(adsbygoogle = window.adsbygoogle || []).push({}); ris a vector while r is a scalar.

1. The problem statement, all variables and given/known data

given that, relative to the geocentric equatorial frame,

r=-6634.2i-1261.8j-5230.9k[km]

the eccentricity vector is

e=-0.40907i-0/48751j-0.63640k

and the satellite is flying towards perigee, calculate the inclination of the orbit.

2. Relevant equations

eq1:e=1/u*(vXh-r/r

eq2:h=rXv

formular for inclination is i=arccos(h.k/h)

3. The attempt at a solution

i managed to findvXhusing eq1,

sincer.(vXh=h.(rXv=h.h=h^2

so i find h, but idk how can i find the vectorh. anyone have a better approach?

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# [spaceflight mechanics] given r and e vector, calculate inclination?

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