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Circular areosynchronous orbit in the Martian equatorial plane
An areostationary orbit, areosynchronous equatorial orbit (AEO), or Mars geostationary orbit is a circular areosynchronous orbit (ASO) approximately 17
Areostationary_orbit
orbit (ASO): A synchronous orbit around the planet Mars with an orbital period equal in length to Mars' sidereal day, 24.6229 hours. Areostationary orbit
List_of_orbits
telecommunications network for the exploration of Mars. Areostationary orbit Geosynchronous orbit List of orbits Lay, N.; C. Cheetum; H. Mojaradi; J. Neal (15 November
Areosynchronous_orbit
Topics referred to by the same term
Martian orbit may refer to: the orbit of Mars around the Sun an areocentric orbit, orbit of an object around Mars an areostationary orbit an areosynchronous
Martian_orbit
orbit at the 22,300-mile altitude. An areostationary orbit or areosynchronous equatorial orbit (abbreviated AEO) is a circular areosynchronous orbit
Stationary_orbit
Circular orbit above Earth's Equator and following the direction of Earth's rotation
same method, we can determine the orbital altitude for any similar pair of bodies, including the areostationary orbit of an object in relation to Mars
Geostationary_orbit
Trajectory of Earth around the Sun
Earth orbits the Sun at an average distance of 149.60 million km (92.96 million mi), or 8.317 light-minutes, in a counterclockwise direction as viewed
Earth's_orbit
Amount by which an orbit deviates from a perfect circle
value of 0 is a circular orbit, values between 0 and 1 form an elliptic orbit, 1 is a parabolic (escape orbit or capture orbit), and greater than 1 is
Orbital_eccentricity
Orbit keeping the satellite at a fixed longitude above the equator
A geosynchronous orbit (sometimes abbreviated GEO) is an Earth-centered orbit with an orbital period that matches Earth's rotation on its axis, 23 hours
Geosynchronous_orbit
Orbit around Earth
Earth's orbit List of orbits Orbital mechanics Celestial sphere Heliocentric orbit Areosynchronous orbit Areostationary orbit Escape velocity Satellite
Geocentric_orbit
Orbit around the planet Mars
Soviet orbiters: Mars 2 (27 November 1971) and Mars 3 (2 December 1971). Areostationary orbit Heliocentrism List of orbits Cytherocentric orbit Edward
Areocentric_orbit
Quasi-periodic orbital trajectory
trajectory In orbital mechanics, a Lissajous orbit (pronounced [li.sa.ʒu]), named after Jules Antoine Lissajous, is a quasi-periodic orbital trajectory that
Lissajous_orbit
Type of geocentric orbit
A Sun-synchronous orbit (SSO), also called a heliosynchronous orbit, is a nearly polar orbit around a planet, in which the satellite passes over any given
Sun-synchronous_orbit
Orbit of an astronomical body equal to that body's average rotational period
corresponding terms for synchronous orbits around Mars are areostationary and areosynchronous orbits. For a stationary synchronous orbit: R s y n = G ( m 2 ) T 2
Synchronous_orbit
Orbit around the barycenter of the Sun
heliocentric orbit (also called circumsolar orbit) is an orbit around the Sun. The inner planets are mainly influenced by the Sun's gravity, and orbit points
Heliocentric_orbit
Speed at which a body orbits around the barycenter of a system
the orbital speed of an astronomical body or object (e.g. planet, moon, artificial satellite, spacecraft, or star) is the speed at which it orbits around
Orbital_speed
Time an astronomical object takes to complete one orbit around another object
The orbital period (also revolution period) is the amount of time a given astronomical object takes to complete one orbit around another object. In astronomy
Orbital_period
Periodic, three-dimensional orbit
Halo orbit A halo orbit is a periodic, non-planar orbit associated with one of the L1, L2 or L3 Lagrange points in the three-body problem of orbital mechanics
Halo_orbit
Type of high-latitude satellite orbit
A Molniya orbit (Russian: Молния, IPA: [ˈmoɫnʲɪjə] , "Lightning") is a type of satellite orbit designed to provide communications and remote sensing coverage
Molniya_orbit
Field of classical mechanics concerned with the motion of spacecraft
Orbital mechanics , astrodynamics or space dynamics is the application of ballistics and celestial mechanics to rockets, satellites, and other spacecraft
Orbital_mechanics
Orbit around Earth between 160 and 2000 km
A low Earth orbit (LEO) is an orbit around Earth with a period of 128 minutes or less (making at least 11.25 orbits per day) and an eccentricity less
Low_Earth_orbit
Kepler orbit with an eccentricity of less than one
elliptical orbit or eccentric orbit is an orbit with an eccentricity of less than 1;[citation needed] this includes the special case of a circular orbit, with
Elliptic_orbit
The Moon's circuit around Earth
The orbit of the Moon is, while stable and known, highly complex, and as such still studied by lunar theory. Most models describe the Moon's orbit geocentrically
Orbit_of_the_Moon
Orbit of an object around the Moon
spaceflight, a lunar orbit (also known as a selenocentric orbit) is an orbit by an object around Earth's Moon. In general these orbits are not circular.
Lunar_orbit
Type of co-orbital motion of a small orbiting body relative to a larger orbiting body
horseshoe orbit of (419624) 2010 SO16 around the Earth-Sun system over 900 years In celestial mechanics, a horseshoe orbit is a type of co-orbital motion
Horseshoe_orbit
Earth-centered orbit above low Earth orbit and below geostationary orbit
A medium Earth orbit (MEO) is an Earth-centered orbit with an altitude above a low Earth orbit (LEO) and below a high Earth orbit (HEO) – between 2,000
Medium_Earth_orbit
Kind of planetary orbit
supersynchronous orbit is an orbit with a period greater than that of a synchronous orbit, or an orbit whose major axis is larger than that of a synchronous orbit. A
Supersynchronous_orbit
Proposed type of space transportation system
low orbit and intersects the Equator regularly (twice every orbital period of 11 h 6 min). Phobos and Deimos may get in the way of an areostationary space
Space_elevator
Transfer manoeuvre between two orbits
astronautics, the Hohmann transfer orbit (/ˈhoʊmən/) is an orbital maneuver used to transfer a spacecraft between two orbits of different altitudes around
Hohmann_transfer_orbit
Type of astronomical orbit
A semi-synchronous orbit is an orbit with a period equal to half the average rotational period of the body being orbited, and in the same direction as
Semi-synchronous_orbit
Type of orbit around an astronomical body
near-equatorial orbit is an orbit that lies close to the equatorial plane of the primary body orbited. Such an orbit has an inclination near 0°. Such orbits lie near
Near-equatorial_orbit
Maintenance of a particular orbit
thruster burns to keep the active craft in the same orbit as its target. For many low Earth orbit satellites, the effects of non-Keplerian forces, i.e
Orbital_station-keeping
Topics referred to by the same term
improving the visibility of a mobile app in an App Store Areostationary orbit, a circular synchronous orbit around Mars in the equatorial plane Aso ebi – Yoruba
ASO
Parameters that define a specific orbit
Kepler orbit. There are many different ways to mathematically describe the same orbit, but certain schemes are commonly used in astronomy and orbital mechanics
Orbital_elements
Spacecraft end-of-life orbit
graveyard orbit, also called a junk orbit or disposal orbit, is an orbit that lies away from common operational orbits. One significant graveyard orbit is a
Graveyard_orbit
Angle between a reference plane and the plane of an orbit
Orbital inclination measures the tilt of an object's orbit around a celestial body. It is expressed as the angle between a reference plane and the orbital
Orbital_inclination
Series of orbital maneuvers
(/ˈrɒndeɪvuː/) is a set of orbital maneuvers during which two spacecraft, one of which is often a space station, arrive at the same orbit and approach to a very
Space_rendezvous
Astrodynamic equation
In astrodynamics, an orbit equation defines the path of orbiting body m 2 {\displaystyle m_{2}\,\!} around central body m 1 {\displaystyle m_{1}\,\!}
Orbit_equation
Transfer orbit used to reach geosynchronous or geostationary orbit
transfer orbit (GTO) or geosynchronous transfer orbit is a highly elliptical type of geocentric orbit, usually with a perigee as low as low Earth orbit (LEO)
Geostationary_transfer_orbit
Curved path of an object around a point
mechanics, an orbit is the curved trajectory of an object under the influence of an attracting force. Alternatively, it is known as an orbital revolution
Orbit
Satellite orbit with high inclination
A polar orbit is one in which a satellite passes above or nearly above both poles of the body being orbited (usually a planet such as the Earth, but possibly
Polar_orbit
Spaceflight where spacecraft orbits an astronomical body
An orbital spaceflight (or orbital flight) is a spaceflight in which a spacecraft is placed on a trajectory where it could remain in space for at least
Orbital_spaceflight
Movement during spaceflight
In spaceflight, an orbital maneuver (otherwise known as a burn) is the use of propulsion systems to change the orbit of a spacecraft. For spacecraft far
Orbital_maneuver
Exploitation of raw materials from asteroids
space elevator would extend over 12,000 km which would be below Areostationary orbit of Mars (17,032 km). A rocket launch would be needed to get the rocket
Asteroid_mining
Geocentric orbit with an altitude entirely above that of a geosynchronous orbit
A high Earth orbit is a geocentric orbit with an apogee farther than that of the geosynchronous orbit, which is 35,786 km (22,236 mi) away from Earth.
High_Earth_orbit
Periodic, three-dimensional orbit
In orbital mechanics a near-rectilinear halo orbit (NRHO) is a halo orbit that passes close to the smaller of two bodies and has nearly stable behavior
Near-rectilinear_halo_orbit
Orbit with a fixed distance from the barycenter
A circular orbit is an orbit with a fixed distance around the barycenter; that is, in the shape of a circle. In this case, not only the distance, but
Circular_orbit
Range of low orbital altitudes
Very low Earth orbit (VLEO) is a range of geocentric orbits with lowest altitudes (at perigee) below 400 km (250 mi). It is of increasing commercial importance
Very_low_Earth_orbit
Concept in astrodynamics
astrodynamics or celestial mechanics, a hyperbolic trajectory or hyperbolic orbit (from Newtonian theory: hyperbola shape) is the trajectory of any object
Hyperbolic_trajectory
Complex type of orbit
A Rosetta orbit is a complex type of orbit. In astronomy, a Rosetta orbit occurs when there is a periastron shift during each orbital cycle. A retrograde
Rosetta_orbit
Kind of planetary orbit
subsynchronous orbit is an orbit of a satellite that is nearer the planet than it would be if it were in synchronous orbit, i.e. the orbital period is less
Subsynchronous_orbit
Celestial orbit whose trajectory is a conic section in the orbital plane
In celestial mechanics, a Kepler orbit (or Keplerian orbit, named after the German astronomer Johannes Kepler) is the motion of one body relative to another
Kepler_orbit
Highly elliptical and highly inclined synchronous orbit
Tundra orbit (Russian: орбита «Тундра») is a highly elliptical geosynchronous orbit with a high inclination (approximately 63.4°), an orbital period of
Tundra_orbit
Parameter in the gravitational two-body problem
two-body problem, the specific orbital energy ε {\displaystyle \varepsilon } (or specific vis-viva energy) of two orbiting bodies is the constant quotient
Specific_orbital_energy
space elevator would extend out over 12,000 km which would be below Areostationary orbit of Mars (17,032 km). A rocket launch would still be needed to get
Colonization_of_Mars
Type of orbit
mechanics a parabolic trajectory is a Kepler orbit with the eccentricity (e) equal to 1 and is an unbound orbit that is exactly on the border between elliptical
Parabolic_trajectory
Laws describing planetary orbits
astronomy, Kepler's laws of planetary motion give good approximations for the orbits of planets around the Sun. They were published by Johannes Kepler from 1609
Kepler's laws of planetary motion
Kepler's_laws_of_planetary_motion
Type of spacecraft orbit
In orbital mechanics, a distant retrograde orbit (DRO) is a highly stable retrograde orbit around the smaller of two bodies, passing outside the system's
Distant_retrograde_orbit
Orbital data format
three-line element set (3LE) is a data format encoding a list of orbital elements of an Earth-orbiting object for a given point in time, the epoch. Using a suitable
Two-line_element_set
Movement around a celestial body that remains below its Karman line
orbit (TAO) is an orbit around a celestial body in which a portion of the orbit intersects with the defined atmosphere. Transatmospheric Earth orbits
Transatmospheric_orbit
Parameter of Keplerian orbits
parameter that defines the position of a body moving along a Keplerian orbit. It is the angle between the direction of periapsis and the current position
True_anomaly
Defunct foundation and company that promoted Mars colonization
the Mars base. Mars One proposed at least two satellites, one in areostationary orbit above Mars and a second at the Earth – Sun L4 or L5 point to relay
Mars_One
Equilibrium points near two orbiting bodies
as orbit corrections, and hence fuel requirements, needed to maintain the desired orbit are kept at a minimum. For any combination of two orbital bodies
Lagrange_point
Temporary orbit used during the launch of a spacecraft
A parking orbit is a temporary orbit used during the launch of a spacecraft. A launch vehicle follows a trajectory to the parking orbit, then coasts for
Parking_orbit
Orbit in the two body case with high eccentricity
A highly elliptical orbit (HEO) or highly eccentric orbit is an orbit of one body about another with high eccentricity, usually referring to one around
Highly_elliptical_orbit
In astrodynamics and celestial mechanics a radial trajectory is a Kepler orbit with zero angular momentum. Two objects in a radial trajectory move directly
Radial_trajectory
Type of gravitational orbit seen in triaxial systems
In stellar dynamics, a box orbit refers to a particular type of orbit that can be seen in triaxial systems, i.e. systems that do not possess a symmetry
Box_orbit
Cartesian vectors of position and velocity of an orbiting body in space
In astrodynamics and celestial dynamics, the orbital state vectors (sometimes state vectors) of an orbit are Cartesian vectors of position ( r {\displaystyle
Orbital_state_vectors
Angle defining a position in an orbit
In orbital mechanics, the eccentric anomaly is an angular parameter that defines the position of a body that is moving along an elliptic Kepler orbit, the
Eccentric_anomaly
Measure of amount of effort to change trajectory
see: Orbital mechanics § Interplanetary Transport Network and fuzzy orbits. C3 Escape orbit GEO Geosynchronous orbit GTO Geostationary transfer orbit L4/5
Delta-v
Propulsive maneuver used to arrive at the Moon
parking orbit around Earth. The large TLI burn, usually performed by a chemical rocket engine, increases the spacecraft's velocity, changing its orbit from
Trans-lunar_injection
System for specifying positions of celestial objects
which include nutation. The fundamental plane is the plane of the Earth's orbit, called the ecliptic plane. There are two principal variants of the ecliptic
Astronomical coordinate systems
Astronomical_coordinate_systems
Angular speed required for a body to complete one orbit
In orbital mechanics, mean motion (represented by n) is the angular speed required for a body to complete one orbit, assuming constant speed in a circular
Mean_motion
Spaceflight maneuver
Orbital inclination change is an orbital maneuver aimed at changing the inclination of an orbiting body's orbit. This maneuver is also known as an orbital
Orbital_inclination_change
Term in geometry; longest and shortest semidiameters of an ellipse
eccentricity of the orbit. In astronomy, the semi-major axis is one of the most important orbital elements of an orbit, along with its orbital period. For Solar
Semi-major and semi-minor axes
Semi-major_and_semi-minor_axes
Region in which an astronomical body dominates the attraction of satellites
planet by a star, a moon by a planet—the less massive body must have an orbit that lies within the gravitational potential represented by the more massive
Hill_sphere
Mathematical equation describing the motion of a rocket
applied to orbital maneuvers in order to determine how much propellant is needed to change to a particular new orbit, or to find the new orbit as the result
Tsiolkovsky_rocket_equation
Orbital plane that is tipped away from the equator
occupy an inclined orbit around Earth if the orbit exhibits an angle other than 0° to the equatorial plane. This angle is called the orbit's inclination. A
Inclined_orbit
Type of orbital maneuver
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
Bi-elliptic_transfer
Type of spacecraft maneuver
a spacecraft to burn its fuel is at the lowest possible orbital periapsis, when its orbital velocity (and so, its kinetic energy) is greatest. In some
Oberth_effect
Vector quantity in celestial mechanics
angular momentum of that body divided by its mass. In the case of two orbiting bodies it is the vector product of their relative position and relative
Specific_angular_momentum
longitude of the periapsis, also called longitude of the pericenter, of an orbiting body is the longitude (measured from the point of the vernal equinox) at
Longitude_of_periapsis
Table of positions of astronomical objects at given times
include ephemeris data used to calculate the position of satellites in orbit. 1st millennium BC – Ephemerides in Babylonian astronomy. 2nd century AD
Ephemeris
Problem in physics and celestial mechanics
predict a planet's motion; i.e., to give its orbital properties: position, orbital diameter, period and orbital velocity. Having done so, he and others soon
N-body_problem
Either of two extreme points in a celestial object's orbit
nearest point in the orbit of a planetary body about its primary body. The line of apsides (also called apse line, or major axis of the orbit) is the line connecting
Apsis
Concept in celestial mechanics
is the minimum speed needed for an object to escape from contact with or orbit of a primary body, assuming: Ballistic trajectory – no other forces are
Escape_velocity
Specifies the orbit of an object in space
argument of pericenter), symbolized as ω (omega), is one of the orbital elements of an orbiting body. Parametrically, ω is the angle from the body's ascending
Argument_of_periapsis
Moment in time used as a reference point in astronomy
of its orbit relative to a reference plane, the direction of the apogee or aphelion of its orbit, or the size of the major axis of its orbit. The main
Epoch_(astronomy)
Low-energy trajectories in the Solar System
solutions exist, most notably the five orbits referred to as "Lagrange points", which are orbital solutions for circular orbits in the case when one body is significantly
Interplanetary Transport Network
Interplanetary_Transport_Network
Space navigation technique
gravitational slingshot in orbital mechanics, is a type of spaceflight flyby which makes use of the relative movement (e.g. orbit around the Sun) and gravity
Gravity_assist
Classical approach to the many-body problem of astronomy
geometrical terms. This is called a two-body problem, or an unperturbed Keplerian orbit. The differences between that and the actual motion of the body are perturbations
Perturbation_(astronomy)
Orbital perturbations
astronomy and astrodynamics the osculating orbit of an object in space at a given moment in time is the orbit it would have around its central body if perturbations
Osculating_orbit
Concept in celestial mechanics
The central body in an orbital system can be defined as the one whose mass (M) is much larger than the mass of the orbiting body (m), or M ≫ m. This
Standard gravitational parameter
Standard_gravitational_parameter
Quasiperiodic orbit around a Lagrange point
In orbital mechanics, a libration point orbit (LPO) is a quasiperiodic orbit around a Lagrange point. Libration is a form of orbital motion exhibited
Libration_point_orbit
Defining the orbit of an object in space
right ascension of the ascending node, is one of the orbital elements used to specify the orbit of an object in space. Denoted with the symbol Ω, it is
Longitude of the ascending node
Longitude_of_the_ascending_node
Measure in astrodynamics
specific orbital energy ϵ {\displaystyle \epsilon } of the escaping object. A spacecraft with insufficient energy to escape will remain in a closed orbit (unless
Characteristic_energy
Specifies the orbit of an object in space
the mean anomaly is the fraction of an elliptical orbit's period that has elapsed since the orbiting body passed periapsis, expressed as an angle which
Mean_anomaly
Fuel-efficient orbital maneuver
low-energy trajectory, is a route in space that allows spacecraft to change orbits using significantly less fuel than traditional transfers. These routes work
Low-energy_transfer
Area rule Areal velocity Arend Joan Rutgers Areostationary orbit Areostationary satellite Areosynchronous orbit Areosynchronous satellite Argo (oceanography)
Index_of_physics_articles_(A)
Path on the surface of the Earth or another body directly below an aircraft or satellite
vertical projection of the satellite's orbit onto the surface of the Earth (or whatever body the satellite is orbiting). A satellite ground track may be thought
Satellite_ground_track
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