Docking maneuvers in orbital mechanics can be described using linear orbit theory. This theory provides a simplified description of the required changes in position and velocity of a vehicle as it approaches and seeks to dock with another vehicle in a reference orbit. When the reference orbit is elliptical, a quantity q appears in the expression for position change with a given by: q= (p/h) (p+r)r sin 0- 1-e 3ept In this equation, e is a dimensionless measure of the elliptical nature of the orbit and is called the eccentricity (e < 1). The radial position of the reference orbit, r, is given in units of km. Time t is given in seconds, and is an angular displacement measured from the perigee of the reference orbit. Find the SI units of h in terms of km and s as well as the corresponding units of q.