this problem deal with classical orbit parameters. a bold letter indicates a vector. ex:r is a vector while r is a scalar.
Homework Statement
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...
Homework Statement
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.
Homework Equations
r=h^2/u(1+ecostheta)
The Attempt at a Solution
The problem statement just doesn't...
Homework Statement
3. Find the partial fraction expansions of the following polynomials
a) 10/[(s^2)(s^2+6s+10)]
The Attempt at a Solution
I assume i should expan the polynomial in the form A/s^2+B/s+(Cs+D)/(s^2+6s+10) but i stuck at finding B. Maybe my expansion is just wrong .. :(