this problem deal with classical orbit parameters. a bold letter indicates a vector. ex:r is 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 find vXh using eq1, since r.(vXh=h.(rXv=h.h=h^2 so i find h, but idk how can i find the vector h. anyone have a better approach?