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Celestial mechanics predicts the motion of planets, Moons, stars and spacecraft from gravity and other relevant forces. Its simplest useful approximation is the two-body problem, whose Kepler orbits explain the connection between orbital shape, energy and angular momentum.

Johannes Kepler's orbital description and Isaac Newton's inverse-square law meet in this model. Additional bodies introduce orbital perturbations; general relativity changes the prediction when relativistic corrections matter. Comparing a predicted trajectory with observations tests both the inferred masses and the adopted dynamical model.^[ref]

A gravitational perturbation is a change to a reference motion caused by an additional gravitational force or a correction to the assumed gravitational field. In celestial mechanics, the reference is often a two-body problem with a point-mass central attractor. Another planet or the nonspherical mass distribution of the central body can change the orbital elements. This is a gravitational cause of an orbital perturbation; atmospheric drag is another kind of cause.^[ref]

The third-body acceleration must be relative to the accelerating central body. Let a satellite be at $r$ relative to that body, and let a perturbing mass $m_3$ be at $R$. Subtracting the third body's attraction on the origin givesOmitting the second term would mistake common acceleration of the entire system for a change in the relative orbit. For $\Vert r\Vert \ll R_0=\Vert R\Vert$, expanding yields the tidal approximationThe perturbation stretches separation along $\hat{R}$ and compresses it in perpendicular directions. Its characteristic ratio to a central attraction $GM/\Vert r{\Vert }^2$ is $(m_3/M)(\Vert r\Vert /R_0{)}^3$. This explains why distance as well as mass determines whether a third body strongly disturbs a satellite. Small instantaneous ratios can still produce appreciable accumulated changes over many orbital periods.^[ref]

A heliocentric orbit describes a body's trajectory relative to the centre of the Sun. For a low-mass body whose motion is dominated by solar gravity, a useful first approximation is a Kepler orbit withwhere $\mathbf{r}$ is the body's position relative to the Sun, $r=\Vert \mathbf{r}\Vert$, $G$ the gravitational constant and $M_{\odot }$ the solar mass. A heliocentric description specifies an origin; the two-body equation additionally assumes that other gravitational forces can be neglected.^[ref]

For a bound elliptic orbit with semi-major axis $a$ and orbital eccentricity $e$, the specific orbital energy and orbital period obeyFor example, a hypothetical solar orbit with $a=2\mathrm{AU}$ and $e=1/2$ ranges from one to three astronomical units from the Sun. Its orbital period is $2^{3/2}=2\sqrt{2}$ times that of a circular solar orbit of radius one astronomical unit, independent of its orbital eccentricity in this approximation.^[ref]

The Sun itself accelerates as other bodies attract it. Accurate Solar system calculations must therefore include the relevant orbital perturbations and specify the reference frame. A spacecraft orbiting Earth also travels around the Sun, but solar-centred coordinates alone do not make a solar two-body problem an adequate model of that spacecraft's local motion.

An orbital perturbation is a departure from a specified reference orbit caused by additional forces or corrections. In celestial mechanics, the reference is often a two-body Kepler orbit; other bodies, nonspherical gravity, drag or relativistic terms modify it.

An orbit specified by osculating orbital elements matches the instantaneous position and velocity with a Keplerian ellipse or hyperbola, while its orbital elements evolve under the perturbation. Some changes oscillate and partly cancel; secular changes accumulate over many periods. A small force need not imply a small long-time effect, especially near a resonance.