Astrodynamics

In astrodynamics apse line (or line of apsides) is a common name for an imaginary line defined by orbit's eccentricity vector. It is strictly defined for elliptic, parabolic and hyperbolic orbits. For those orbits it can be imagined as a line: ...more on Wikipedia about "Apse line"

: This article is about several astronomical terms (apogee & perigee, aphelion & perihelion, generic equivalents based on apsis, and related but rarer terms). In architecture, apsis is a synonym for apse. ...more on Wikipedia about "Apsis"

An areostationary orbit (abbreviated ASO) is a circular areosynchronous orbit in the Martian equatorial plane 11,000 km above the surface, any point on which revolves about Mars in the same direction and with the same period as the Martian surface. Although no artificial satellites have been placed so far in this orbit, it is of interest to some scientists forseeing a future telecommunications network for the exploration of Mars. Areostationary orbit is a concept similar to Earth's geostationary orbit. ...more on Wikipedia about "Areostationary orbit"

Areostationary satellite is an artificial satellite in areostationary orbit (i.e. prograde synchronous orbit in equatorial plane around Mars). ...more on Wikipedia about "Areostationary satellite"

Areosynchronous orbits are class of synchronous orbits for artificial satellites around the planet Mars. As with all synchronous orbits, an areosynchronous orbit has an orbital period equal in length to Mars' sidereal day. A satellite in areosynchronous orbit does not necessarily maintain a fixed position in the sky as seen by an observer on the surface of Mars, however such a satellite will return to the same apparent position every Martian day. ...more on Wikipedia about "Areosynchronous orbit"

Areosynchronous satellite is an artificial satellite in areosynchronous orbit (i.e. synchronous orbits around Mars). ...more on Wikipedia about "Areosynchronous satellite"

In an orbit, the argument of periapsis (ω) is the angle between the ascending node (the point where the orbiting body passes from the southern to the northern hemisphere) and the periapsis (the point of closest approach to the central body), measured in the body's orbital plane and in its direction of motion. It is undefined for equatorial orbits, where there is no defined ascending node, and for circular orbits, where there is no defined periapsis. The argument of periapsis is often called the argument of perihelion for objects orbiting the sun, and the argument of perigee for objects orbiting planets, such as satellites. ...more on Wikipedia about "Argument of periapsis"

The argument of the perihelion is one of the orbital elements describing a body in a Sun-centered orbit (e.g., a planet). It is the angle between the ascending node and the perihelion, measured in the orbital plane. Adding it to the longitude of the ascending node gives the longitude of perihelion of the body in its orbit around the Sun. ...more on Wikipedia about "Argument of the perihelion"

Astrodynamics is the study of the motion of rockets, missiles, and space vehicles, as determined from Sir Isaac Newton's laws of motion and his law of universal gravitation. It is a specific and distinct branch of celestial mechanics, which focuses more broadly on Newtonian gravitation and includes the orbital motions of artificial and natural astronomical bodies such as planets, moons, and comets. Astrodynamics is principally concerned with spacecraft trajectories, from launch to atmospheric re-entry, including all orbital maneuvers, orbit plane changes, and interplanetary transfers. For a less technical treatment, see the article on space mathematics. ...more on Wikipedia about "Astrodynamics"

Astronomical algorithms are the algorithms used to calculate ephemerides, calendars, and positions (as in celestial navigation or satellite navigation). Examples of large and complex astronomical algorithms are those used to calculate the position of the Moon. A simple example is the calculation of the Julian day. ...more on Wikipedia about "Astronomical algorithm"

Atmospheric drag is a form of drag, which is the force that opposes an object moving through a liquid or gas. ...more on Wikipedia about "Atmospheric drag"

In astronautics and aerospace engineering, the Bi-elliptic transfer is an orbital maneuver that moves a spacecraft from one orbit to another and may, in certain situations require less delta-v then a Hohmann transfer. ...more on Wikipedia about "Bi-elliptic transfer"

A capture orbit is the high-energy parabolic orbit that allows the capture other than crashing directly to the central body's surface (or atmospheric re-entry). ...more on Wikipedia about "Capture orbit"

In astrodynamics a central body ( $m_1\,$ ) is a body that is being orbited by orbiting body( $m_2\,$ ). Under standard assumptions in astrodynamics: ...more on Wikipedia about "Central body"

In astrodynamics a characteristic energy ( $C_3\,\!$ ) is a measure of the energy required for an interplanetary mission that requires attaining an excess orbital velocity over an escape velocity required for additional orbital maneuvers. The unit of the characteristic energy is km² s^-2. ...more on Wikipedia about "Characteristic energy"

:For other meanings of the term "orbit", see orbit (disambiguation) ...more on Wikipedia about "Circular orbit"

In general physics, delta-v is simply the change in velocity. ...more on Wikipedia about "Delta-v"

Delta-v budget (or velocity change budget) is a term used in astrodynamics and aerospace industry for velocity change (or delta-v) requirements for the various propulsive tasks and orbital maneuvers over phases of the space mission. ...more on Wikipedia about "Delta-v budget"

Earth orbit is an orbit around the planet Earth. The Moon, Earth's only natural satellite, is in Earth orbit. Artificial satellites are launched into Earth orbit, and spacecraft bound for other locations in the solar system usually begin their missions by first attaining Earth orbit, before altering course to another planet, moon, or heliocentric (solar) orbit. ...more on Wikipedia about "Earth orbit"

The eccentric anomaly is the angle between the direction of periapsis and the current position of an object on its orbit, projected onto the ellipse's circumscribing circle perpendicularly to the major axis, measured at the centre of the ellipse. In the diagram below, it is E (the angle zcx). ...more on Wikipedia about "Eccentric anomaly"

In astrodynamics, under standard assumptions any orbit must be of conic section shape. The eccentricity of this conic section, the orbit's eccentricity, is an important parameter of the orbit that defines its absolute shape. Eccentricity may be interpreted as a measure of how much this shape deviates from a circle. ...more on Wikipedia about "Eccentricity (orbit)" It must be www.shortopedia.com. Astrodynamics

In astrodynamics the eccentricity vector of a conic section orbit is the vector pointing towards the periapsis and with length equal to the orbit's scalar eccentricity. ...more on Wikipedia about "Eccentricity vector"

The ecliptic plane is the geometric plane that contains the orbit of the Earth. The ecliptic is the intersection of the ecliptic plane and the celestial sphere. A more intuitive definition would be to say that the ecliptic is the apparent path of the Sun during a year as seen from Earth. The orbits of most planets in the Solar System lie very close to it. Seen from the Earth, this is a bisecting great circle, superimposed upon the celestial sphere, which contains the different points of the Sun's path, relative to the background stars, over the course of a year. The zodiac also lies along the ecliptic plane. The ecliptic plane is inclined by ~23.5°, with respect to the celestial equator; a result of axial tilt. The orbital plane of the Moon is inclined by ~5°, with respect to the ecliptic. ...more on Wikipedia about "Ecliptic"

Eclipitic orbit is an orbit with inclination to the plane of reference (i.d. ecliptic) equal to zero. ...more on Wikipedia about "Ecliptic orbit"

Under standard assumptions the orbital velocity ( $v\,$ ) of a body traveling along elliptic orbit can be computed as: ...more on Wikipedia about "Elliptic orbit"

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