Orbital state vectors
In astrodynamics or celestial dynamics orbital state vectors (sometimes state vectors) are vectors of position () and velocity () that together with their time (epoch) () uniquely determine the state of an orbiting body.
State vectors are excellent for pre-launch orbital predictions when combined with time (epoch) expressed as an offset to the launch time. This makes the state vectors time-independent and good general prediction for orbit.
Frame of reference
The state vectors must be considered in a particular inertial frame of reference setting. For most practical applications in astrodynamics this is usually assumed to have the following properties:
- cartesian right-handed coordinate system:
- with x-axis pointing to vernal equinox,
- with z-axis pointing upwards, meaning the x-y plane is the reference plane.
The orbital position vector is a cartesian vector describing the position of the orbiting body in Frame of reference. Together, the orbital position vector and orbital velocity vector describe uniquely the state of an orbiting body and thus are called Orbital state vectors.
Orbital velocity vector is a cartesian vector describing velocity of the orbiting body in frame of reference. Orbital velocity vector together with orbital position vector describe uniquely state of the orbiting body and thus are called Orbital state vectors.
Orbital velocity vector can be derived from orbital position vector by differentiation with respect to time:
Orbital position is when a planet rotates another planet.
Both state vectors and orbital elements have unique advantages over the other. Computed in advance state vectors are more useful for orbital prediction. A time-independent state vector can be combined with the launch time using xxx method in order to arrive at a valid set of orbital elements whereas computed in advance orbital elements are valid only when launch occurs without the slip.
In astrodynamics orbital state vectors ( and ) are used with the help of following auxiliary vector:
Orbital state vectors can then be used to calculate following orbital elements (Keplerian elements) (see their definitions for directions):
- Inclination ()
- Eccentricity ()
- Longitude of ascending node ()
- Argument of periapsis ()
- Mean anomaly ()
- Orbital period ()
together with time () (epoch) those can be used to compute other orbit's parameters:
- True anomaly ()
- Semi-major axis ()
- Semi-minor axis ()
- Beta Angle ()
- Linear eccentricity ()
- Periapsis distance ()
- Apoapsis distance ()
- Eccentric anomaly ()
- Mean longitude ()
- True longitude ()
Keplerian elements typically define an osculating orbit because of perturbations in the orbital path. The osculating orbit is valid only at the epoch of the original Cartesian elements.
Orbits Types General Geocentric About other points Parameters Classical Other Maneuvers Other orbital mechanics topicsApsis · Celestial coordinate system · Characteristic energy · Direct motion · Epoch · Ephemeris · Equatorial coordinate system · Ground track · Interplanetary Transport Network · Kepler's laws of planetary motion · Lagrangian point · n-body problem · Orbit equation · Orbital speed · Orbital state vectors · Perturbation · Retrograde motion · Specific orbital energy · Specific relative angular momentum List of orbits
- cartesian right-handed coordinate system:
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