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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
Kepler orbit with an eccentricity of less than one
\epsilon } ) of an elliptic orbit is negative and the orbital energy conservation equation (the Vis-viva equation) for this orbit can take the form: v 2 2
Elliptic_orbit
Concept in gravitational orbital mechanics
In astrodynamics, the vis-viva equation is one of the equations that model the motion of orbiting bodies. It is the direct result of the principle of conservation
Vis-viva_equation
Type of orbit
{\displaystyle v_{o}} is orbital velocity of a body in circular orbit. For a body moving along this kind of trajectory the orbital equation is: r = h 2 μ 1 1
Parabolic_trajectory
Field of classical mechanics concerned with the motion of spacecraft
specific orbital energy ( ϵ {\displaystyle \epsilon } ) of elliptic orbit is negative, and the orbital energy conservation equation (the vis-viva equation) for
Orbital_mechanics
Mathematical equation describing the motion of a rocket
The classical rocket equation, Tsiolkovsky rocket equation, or ideal rocket equation is a mathematical equation that describes the motion of vehicles that
Tsiolkovsky_rocket_equation
Orbital mechanics term
In orbital mechanics, Kepler's equation relates various geometric properties of the orbit of a body subject to a central force. It was derived by Johannes
Kepler's_equation
Orbit with a fixed distance from the barycenter
parameter. r {\displaystyle r} is the distance from the center of mass. The orbit equation in polar coordinates, which in general gives r in terms of θ, reduces
Circular_orbit
Time an astronomical object takes to complete one orbit around another object
the above equation simplifies to T = 3 π G ρ {\displaystyle T={\sqrt {\frac {3\pi }{G\rho }}}} (since r now nearly equals a). Thus the orbital period in
Orbital_period
Parameters that define a specific orbit
in the general orbit equation, which can return the distance from the central body given p and the true anomaly for any type of orbit or trajectory. This
Orbital_elements
Concept in astrodynamics
\theta } is linked to the distance between the orbiting bodies ( r {\displaystyle r\,} ) by the orbit equation: r = ℓ 1 + e ⋅ cos θ {\displaystyle r={\frac
Hyperbolic_trajectory
Curved path of an object around a point
In order to get an equation for the orbit from equation (1), the time variable needs to be eliminated. (See also Binet equation.) In polar coordinates
Orbit
Celestial orbit whose trajectory is a conic section in the orbital plane
of the orbiting object and the location in the orbit at which it is closest to the central body (called the periapsis). Alternately, the equation can be
Kepler_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
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
Motion problem in classical mechanics
the case of an attractive force. Energy drift Equation of the center Euler's three-body problem Kepler orbit Kepler problem n-body problem Three-body problem
Two-body_problem
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
Apparent solar time minus mean solar time
the Earth's orbit around the Sun, which is about 0.0167. The equation of time vanishes only for a planet with zero axial tilt and zero orbital eccentricity
Equation_of_time
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
Parameter in the gravitational two-body problem
their reduced mass. According to the orbital energy conservation equation (also referred to as vis-viva equation), it does not vary with time: ε = ε k
Specific_orbital_energy
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
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
gravitational orbit classified by various characteristics. The following is a list of types of orbits: Galactocentric orbit: An orbit about the center
List_of_orbits
Equation giving the form of a central force
The Binet equation, derived by Jacques Philippe Marie Binet, provides the form of a central force given the shape of the orbital motion in plane polar
Binet_equation
Equilibrium points near two orbiting bodies
Lissajous orbit or a halo orbit around L2 in order for its solar panels to get full sun. The location of L3 is the solution to the following equation, gravitation
Lagrange_point
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
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
Paths of particles in the Schwarzschild solution to Einstein's field equations
minimum radius for the circular orbit to be stable in Schwarzschild metric. An exact solution to the Einstein field equations is the Schwarzschild metric
Schwarzschild_geodesics
Process that leads to gradual decrease of the distance between two orbiting bodies
the orbit is simply the sum of kinetic and gravitational potential energies, in an unperturbed two-body orbit. By substituting the vis-viva equation into
Orbital_decay
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
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
Specifies the orbit of an object in space
an elliptical orbit from a set of orbital elements is to calculate the mean anomaly by this equation, and then to solve Kepler's equation for the eccentric
Mean_anomaly
Equation for fixed point of functional composition
h(x), can have its smooth orbit (or flow) reconstructed from the solution of the above Schröder's equation, its conjugacy equation. That is, h(x) = Ψ−1(s
Schröder's_equation
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
Circular orbit above Earth's Equator and following the direction of Earth's rotation
A geostationary orbit, also referred to as a GEO or GSO, is a circular geosynchronous orbit 35,786 km (22,236 mi) in altitude above Earth's equator, 42
Geostationary_orbit
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
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
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
Measure of amount of effort to change trajectory
Gravity drag Orbital maneuver Orbital stationkeeping Spacecraft propulsion Orbital propellant depot Specific impulse Tsiolkovsky rocket equation Sarigul-Klijn
Delta-v
Classical approach to the many-body problem of astronomy
of general perturbations, general differential equations, either of motion or of change in the orbital elements, are solved analytically, usually by series
Perturbation_(astronomy)
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
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
Laws describing planetary orbits
differential equation. The solutions to this differential equation include the Keplerian motions, as shown, but they also include motions where the orbit is a
Kepler's laws of planetary motion
Kepler's_laws_of_planetary_motion
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
Orbital perturbations
description of orbital motion can be simplified and approximated by choosing orbital elements that are not osculating. Also, in some situations, equations in at
Osculating_orbit
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
Cartesian vectors of position and velocity of an orbiting body in space
at the center of the orbit are known, position and velocity are the initial values for that second order differential equation for r ( t ) {\displaystyle
Orbital_state_vectors
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
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
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
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
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
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
Highly elliptical and highly inclined synchronous orbit
according to equation 1, unless it is constantly corrected with station-keeping thruster burns. where i {\displaystyle i} is the orbital inclination,
Tundra_orbit
Concept in celestial mechanics
{2}}} times the speed in a circular orbit at the same height, (compare this with the velocity equation in circular orbit). This corresponds to the fact that
Escape_velocity
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
Problem in physics and celestial mechanics
produce an equation by straightforward analytical geometry, to predict a planet's motion; i.e., to give its orbital properties: position, orbital diameter
N-body_problem
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
Parameter of Keplerian orbits
limited to orbits where the eccentricity e {\displaystyle e} is small. The expression ν − M {\displaystyle \nu -M} is known as the equation of the center
True_anomaly
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
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
the phasing orbit using the following equation. T 2 = T 1 − t {\displaystyle T_{2}=T_{1}-t} where T1 is defined as period of original orbit T2 is defined
Orbit_phasing
Characteristic of conic sections
equations is by analogy with the conic sections classification; see elliptic, parabolic and hyperbolic partial differential equations. Kepler orbits Eccentricity
Eccentricity_(mathematics)
Orbit around Earth
A geocentric orbit, Earth-centered orbit, or Earth orbit involves any object orbiting Earth, such as the Moon or artificial satellites. In 1997, NASA estimated
Geocentric_orbit
Orbit around the planet Mars
orbit for an orbit around Earth and heliocentric orbit for an orbit around the Sun. As with these other orbits, the apsides of an areocentric orbit are
Areocentric_orbit
Frame of reference for an orbit
‖ r ‖ {\displaystyle r=\|\mathbf {r} \|} may be calculated from the orbit equation. The velocity vector, v, is found by taking the time derivative of the
Perifocal_coordinate_system
Orbital plane that is tipped away from the equator
surface at the same mean solar time every day. These orbits have an inclination governed by the equation: cos ( i ) ≈ − ( T 3.795 hr ) 7 3 {\displaystyle
Inclined_orbit
Description of a quantum-mechanical system
The Schrödinger equation is a partial differential equation that governs the wave function of a non-relativistic quantum-mechanical system. Its discovery
Schrödinger_equation
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
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
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
Estimate of extraterrestrial civilizations
The Drake equation is a probabilistic argument used to estimate the number of active, communicative extraterrestrial civilizations in the Milky Way Galaxy
Drake_equation
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
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
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
Center of mass of multiple bodies orbiting each other
(kéntron) 'center') is the center of mass around which two or more bodies orbit. A barycenter is a dynamical point, not a physical object. It is an important
Barycenter_(astronomy)
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
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
Spaceflight where the spacecraft does not go into orbit
spaceflight. During freefall the trajectory is part of an elliptic orbit as given by the orbit equation. The perigee distance is less than the radius of the Earth
Sub-orbital_spaceflight
Vector quantity in celestial mechanics
the orbit equation r = h 2 μ 1 + C μ cos θ {\displaystyle r={\frac {\frac {h^{2}}{\mu }}{1+{\frac {C}{\mu }}\cos \theta }}} which is the equation of
Specific_angular_momentum
Orbit of an astronomical body equal to that body's average rotational period
synchronous orbit is an orbit in which an orbiting body (usually a satellite) has a period equal to the average rotational period of the body being orbited (usually
Synchronous_orbit
The areosynchronous orbits (ASO) are the synchronous orbits for artificial satellites around the planet Mars. They are the martian equivalent of the geosynchronous
Areosynchronous_orbit
symmetric) radial elliptic orbits. Kepler's equation Kepler problem List of orbits Cowell, Peter (1993), Solving Kepler's Equation Over Three Centuries, William
Radial_trajectory
Angle defining a position in an orbit
define a position along an orbit, the other two being the true anomaly and the mean anomaly. Consider the ellipse with equation given by: x 2 a 2 + y 2 b
Eccentric_anomaly
System for specifying positions of celestial objects
equations, derived from spherical trigonometry, for the longitudinal coordinate are presented to the right of a bracket; dividing the first equation by
Astronomical coordinate systems
Astronomical_coordinate_systems
Type of spacecraft orbit
In orbital mechanics, a distant retrograde orbit (DRO) is an highly stable retrograde orbit around the smaller of two bodies, passing outside the system's
Distant_retrograde_orbit
Branch of astronomy
force, and developing a method to use a single polar coordinate equation to describe any orbit, even those that are parabolic and hyperbolic. This is useful
Celestial_mechanics
possible to solve Einstein's field equation using a computer instead of mathematical formulae. As the two bodies orbit each other, they will emit gravitational
Two-body problem in general relativity
Two-body_problem_in_general_relativity
Estimate of total change in velocity of a space mission
about 9.4 km/s. Because of the exponential nature of the rocket equation the orbital rocket needs to be considerably bigger. Launch to LEO—this not only
Delta-v_budget
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
Simple polynomial map exhibiting chaotic behavior
map is a discrete dynamical system defined by the quadratic difference equation It is a recurrence relation and a polynomial mapping of degree 2. It is
Logistic_map
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
Horizontal angle from north or other reference cardinal direction
Hyperbolic orbit Radial orbit Decaying orbit Equations Dynamical friction Escape velocity Kepler's equation Kepler's laws of planetary motion Orbital period
Azimuth
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
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
Type of orbital maneuver
each phase of the transfer is half the orbital period of each transfer ellipse. Using the equation for the orbital period and the notation from above, T
Bi-elliptic_transfer
Keplerian orbital mechanics, the equation of the center is the angular difference between the actual position of a body in its elliptical orbit and the
Equation_of_the_center
Spacecraft launch or descent maneuver
a maneuver used in launching a spacecraft into, or descending from, an orbit around a celestial body such as a planet or a moon. It is a trajectory optimization
Gravity_turn
Relativistic interaction in quantum physics
In quantum mechanics, the spin–orbit interaction (also called spin–orbit effect or spin–orbit coupling) is a relativistic interaction of a particle's spin
Spin–orbit_interaction
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
ORBIT EQUATION
ORBIT EQUATION
Boy/Male
Gujarati, Indian
Time Lord
Boy/Male
English
Raven. Black-haired.
Girl/Female
Arabic, Hebrew
Little Light
Female
Hebrew
(×ï‹×¨Ö´×™×ª) Variant form of Hebrew Ora, ORIT means "light."
Boy/Male
Arabic, Hindu, Indian, Muslim, Sindhi
One who Argues a Lot; Orbit; Eye Socket; Orgument; Debate
Surname or Lastname
English
English : variant spelling of Corbett.
Girl/Female
Bengali, Gujarati, Hindu, Indian, Kannada, Malayalam, Marathi, Telugu
Circumference of the Orbit; Limit; Realm
Boy/Male
Indian
Orbit, Eye socket, Argument
Boy/Male
Muslim/Islamic
Orbit eye socket, Orgument, debate
Boy/Male
Muslim
Orbit, Eye socket, Argument
Boy/Male
British, English, Latin
Raven; Variant of Corbet; Black-haired; Dark as a Raven
ORBIT EQUATION
ORBIT EQUATION
Boy/Male
Afghan, Arabic, French, German, Indian, Muslim
Pure-chaste; Chaste; Modest
Boy/Male
Hindu, Indian, Marathi
The Handsome One
Girl/Female
Biblical
Prepared, arrayed.
Surname or Lastname
English
English : occupational name for someone who looked after animals, Middle English bester, from beste ‘beast’ (see Best).German : habitational name for someone from a place called Beste.Slovenian (Gorenjska; also Bešter) : probably a derivative of Vester 3, a reduced form of the personal name Silvester. Replacement of initial V- with B- is quite common in Slovenian surnames.
Surname or Lastname
English or Scottish
English or Scottish : patronymic from a reduced form of the personal name Steven.
Boy/Male
Hindu, Indian
Lord Venkateshwara
Boy/Male
Arabic, Muslim
Manifest
Boy/Male
Irish American
Seawarrior.
Girl/Female
Arabic, Australian, Iranian, Muslim, Parsi
Dawn
Boy/Male
Muslim
ORBIT EQUATION
ORBIT EQUATION
ORBIT EQUATION
ORBIT EQUATION
ORBIT EQUATION
n.
The skin which surrounds the eye of a bird.
a.
Alt. of Orbical
n.
The elliptical orbit of a planet.
n.
An orb or ball.
a.
Of or pertaining to an orbit.
n.
One of the two points where the orbit of a planet, or comet, intersects the ecliptic, or the orbit of a satellite intersects the plane of the orbit of its primary.
a.
Of or pertaining to the apsides of an orbit.
a.
Situated above the orbit of the eye.
v. t.
To throw out of the proper orbit; to unsphere.
a.
Situated around the orbit; as, the orbitary feathers of a bird.
n.
Alt. of Orbity
n.
Orbation.
a.
Situated under or below the orbit.
n.
A circle; esp., a circle, or nearly circular orbit, described by the revolution of a heavenly body; an orbit.
n.
The path described by a heavenly body in its periodical revolution around another body; as, the orbit of Jupiter, of the earth, of the moon.
n.
An orbit, as of a star; a socket.
a.
Below the orbit; as, the infraorbital foramen; the infraorbital nerve.
a.
Situated in front or the orbit.
n.
The cavity or socket of the skull in which the eye and its appendages are situated.