Due to the oblateness of the Earth (the Earth's equatorial bulge), a geocentric satellite's orbital plane will precess (rotate) relative to inertial space.
The rate at which the line of nodes moves owing to this bulge is given by
$$
\dot\Omega = -\frac{3}{2}J_2\left(\frac{r_E}{ℓ}\right)^2 n\cos\iota
$$
where $J_2$ is the is the zonal harmonic coefficient ($1.08262668\times10^{-3}$ for Earth), $r_E$ is the body's equatorial radius ($6\,378\,137$ m for Earth), $ℓ$ is the orbit parameter (the semi-latus rectum), $n$ is the mean motion, and $\iota$ is the inclination of the orbit.
For a given orbit parameter ($ℓ$) and mean motion ($n$), the inclination of a geocentric satellite orbit can be selected to obtain, for example, a Sun-synchronous orbit ($\dot\Omega=360^\circ$ per $365.26$ days, or $0.9856$ degrees per day).
Coordinate System
This Wikipedia article (and diagram from that article) describes the coordinate system used.
The orbital plane (yellow) intersects a reference plane (gray). For Earth-orbiting satellites, the reference plane is usually the Earth's equatorial plane. The intersection is called the line of nodes, as it connects the center of mass with the ascending and descending nodes. This plane, together with the vernal point ($\gamma$), establishes a reference frame.
Two elements that define the size and shape of the elliptical orbit
are the semi-major axis, $a$, and the eccentricity, $e$. The
semi-latus rectum is related to $a$ and $e$ by $ℓ=a(1-e^2)$.
Two elements define the orientation of the orbital plane in which the
ellipse is embedded: the inclination, $\iota$, and the longitude of the ascending node, $\Omega$.
