Editing Orbital state vectors (section)

==Position and velocity vectors==
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The ''[[position vector]]'' <math>\mathbf{r}</math> describes the position of the body in the chosen [[#Frame of reference|frame of reference]], while the ''[[velocity vector]]'' <math>\mathbf{v}</math> describes its velocity in the same frame at the same time. Together, these two vectors and the time at which they are valid uniquely describe the body's trajectory as detailed in [[Orbit determination#Orbit Determination from a State Vector|Orbit determination]]. The principal reasoning is that Newton's law of gravitation yields an acceleration <math>\ddot \mathbf{r}=-GM/r^2</math>; if the product <math>GM</math> of gravitational constant and attractive mass at the center of the orbit are known, position and velocity are the initial values for that second order differential equation for <math>\mathbf{r}(t)</math> which has a unique solution.

The body does not actually have to be in orbit for its state vectors to determine its trajectory; it only has to move [[ballistically]], i.e., solely under the effects of its own inertia and gravity. For example, it could be a spacecraft or missile in a [[suborbital]] trajectory. If other forces such as drag or thrust are significant, they must be added vectorially to those of gravity when performing the integration to determine future position and velocity.

For any object moving through space, the velocity vector is [[tangent]] to the trajectory. If <math> \hat{\mathbf{u}}_t</math> is the [[unit vector]] tangent to the trajectory, then
<math display="block">\mathbf{v} = v\hat{\mathbf{u}}_t</math>

===Derivation===
The velocity vector <math>\mathbf{v}\,</math> can be derived from position vector <math>\mathbf{r}</math> by [[Differentiation (mathematics)|differentiation]] with respect to time:
<math display="block">\mathbf{v} = \frac{d\mathbf{r}}{dt}</math>

An object's state vector can be used to compute its classical or Keplerian [[orbital elements]] and vice versa. Each representation has its advantages. The elements are more descriptive of the size, shape and orientation of an orbit, and may be used to quickly and easily estimate the object's state at any arbitrary time provided its motion is accurately modeled by the [[two-body problem]] with only small perturbations.

On the other hand, the state vector is more directly useful in a [[numerical integration]] that accounts for significant, arbitrary, time-varying forces such as drag, thrust and gravitational perturbations from third bodies as well as the gravity of the primary body.

The state vectors (<math>\mathbf{r}</math> and <math>\mathbf{v}</math>) can be easily used to compute the [[specific angular momentum]] vector as
:<math>\mathbf{h} = \mathbf{r}\times\mathbf{v}</math>.

Because even satellites in low Earth orbit experience significant perturbations from non-spherical [[Earth's figure]], [[Radiation Pressure#Solar Radiation Pressure|solar radiation pressure]], lunar [[tide]], and [[atmospheric drag]], the Keplerian elements computed from the state vector at any moment are only valid for a short period of time and need to be recomputed often to determine a valid object state. Such element sets are known as ''[[osculating orbit|osculating]] elements'' because they coincide with the actual orbit only at that moment.