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Maximum elevation is not included. The marker symbols in the table indicate that the event took place sometime in the previous step interval. This RTS-only mode can be turned on at two different points in the program command-line interface :. Three types of criteria are available for the rise and set conditions, relative to an input elevation angle nominally 0 degrees. Select by specifying, when prompted at 1 or 2, one of these symbols:.

Thus, if there are local hills, one could set the elevation cut-off at 10 degrees and get RETS relative to that elevation. To speed RTS-only searches, use the largest step-size compatible with the required accuracy.

Setting a search-step of 5 minutes will then produce a table 5 times faster than 1 minute searching. Radar, other low frequency observations, or optical observations at higher elevations, can be less affected by atmospheric effects and warrant finer resolution determination.

The program computes approximate refraction angles assuming yellow-light observations at 10 deg C sea-level with pressure of millibars. Transit and maximum elevation are based on the center of the target body. Maximum elevation is the highest angle above the local horizons. The two conditions can occur at times differing by seconds or even minutes for close objects moving quickly.

One output value that may be requested for an observer table is the constellation it is observed to be in corrected for light-time. The output field will contain a three letter abbreviation of the constellation name, from the list shown below. Constellation boundaries are those delineated by Gould and Delporte under the auspices of the International Astronomical Union. The JPL DE solar system solution [1] is the basis of planetary barycenter motion data over the interval from B.

The Chebyshev polynomial representation of DE permits rapid recovery of the original barycenter integrator state to the sub-meter level. This difference in representation is much less than the uncertainty associated with the trajectory solution itself.

Natural satellites and planet-centers are determined separately, and available over various shorter intervals, as warranted by their observational data arc, but generally hundreds of years. Planet-center offsets from the planetary system barycenter they move with respect to barycentric shift vectors are defined by the satellite solutions.

For example, while the center of Mars is available over a few hundred years as defined by the solution for the motions of the moons Phobos and Deimos, the Mars system barycenter 4 is available over B. The difference between the position of a planet center and planetary system barycenter is often not important unless one has a spacecraft in the vicinity or is studying the offset.

Therefore, specifying barycenters body-code integers less than 10 is typically acceptable if the longer time-span is of interest. Comets and asteroids are numerically integrated on demand over a maximum interval of A.

Some ancient comets may be available outside that span for their relevant historical period. Only a relatively small number of such small-bodies have sufficiently well-determined orbits to justify rigorous integration over time-spans of hundreds of years. Statistical uncertainty information derived from mapped covariances is available to help the user determine the limits of useful numerical integration.

For the time-span of Jan-1 to Jan-1, the IAU precession model of Lieske is used [9]. As published, this model is valid for only ~ years on either side of the J This is due to round-off error in the published coefficients and truncation to a 3rd order polynomial in the expressions for the Euler rotation angles.

The IAU model of Wahr is used [11]. This is the same table printed in the Explanatory Supplement to the Astronomical Almanac. Note there is an error in the Explanatory Supplement for the Node term, given on p.

This program internally uses the TDB time-scale of the ephemerides the independent variable in the equations of motion. This program currently uses the analyses of [8] as follows:.

For dates prior to Jan, the periodically varying distinction between TDB and TT with maximum offset of 0. As one progresses to earlier times, particularly those prior to the telescopic data span, uncertainties in conversion to UT generally though not always and not uniformly increase due to less precise observations and sparser records.

At B. The GMST used for topocentric ephemerides is related to UT1 using a standard model consistent with the adopted IAU system of constants:. Nautical Almanac Office. The JPL EOP file is currently updated daily based on GPS and other Earth-monitoring measurements. Horizons uses it to obtain calibrations for UT1-UTC, polar motion, and nutation correction parameters necessary to determine the rotation between the Earth-fixed reference frame IRTF93 to the inertial reference frame ICRF.

The EOP file provides data from to the present, with predictions about 78 days into the future from the date of file release. For future times outside the available EOP data-fit or prediction intervals, Horizons uses the last predicted values available in the EOP file as constants. For historical TDB-UT calculations prior to , it switches to the published reconstruction estimates described and referenced above.

Because EOP values are fit to data and include a near-term prediction interval, it is possible an ephemeris may very slightly differ from one produced days or weeks or months later, especially, if the original ephemeris extended into the predicted region of the EOP file. The most recent ephemeris will be more accurate, but if it is necessary to reproduce results exactly, contact JPL.

EOP files are archived and the one used in your initial run indicated in your output can be retrieved. The current IAU rotational models for the planets and satellites are simply extended in time as necessary. The results are therefore consistent with the IAU rotational models, including any of their deficiencies: the rotation models of some satellites may be realistically valid only for much shorter periods of time, such as around the Voyager spacecraft encounters, and produce invalid results outside those windows.

Users should consult the IAU cartographic report for more information and limitations on specific body models. A best fit is developed to statistically minimize those errors. The resulting ephemeris has an associated uncertainty that fluctuates with time. For example, only a limited percentage of asteroid orbits are known to better than 1 arcsec in the plane-of-sky over significant periods of time. While JX center-of-mass was known to within 30 meters along the line-of-sight during the Goldstone radar experiment, errors increase outside that time-span.

Cartesian state vectors are output in all their 16 decimal-place glory. This does not mean all digits are physically meaningful. The full-precision may be of interest to those studying the ephemerides or as a source of initial conditions for subsequent integrations. On top of this basic uncertainty, the mass parameter GM used to compute osculating element output is rarely known to better than 5 significant figures.

Small-body osculating orbital elements are reported in the ICRF reference frame of the planetary ephemeris. This frame is currently thought to differ by no more than 0. The Earth is assumed to be a rigid body and solid Earth tides affecting station location are not included generally around 70 cm. Of course, precession and nutation effects are included, as is polar motion. TDB-TAI terms less than 20 usec are omitted.

These and other Earth-model approximations result in topocentric station location errors, with respect to the reference ellipsoid, of less than 10 meters. However, many optical site positions latitude and longitude are reported far less accurately and could be many kilometers off. Solar relativistic effects are included in all planet, lunar, and small body dynamics, excluding satellites. Relativity is included in observables via 2nd order terms in stellar aberration and the deflection of light due to gravity fields of the Sun and Earth, for topocentric observers.

Light-time iterations are Newtonian. For many small natural satellites, the orbit orientation is well known, but the position of the body along the ellipse is not. Errors may be significant, especially for the lesser satellites of outer planets. Satellite osculating elements output by Horizons should NOT be used to initialize a separate integration or extrapolation. Such elements assume Keplerian motion two point masses, etc.

which does not match, for example, kinematic models such as a precessing ellipse, used for some satellites. Spacecraft in low Earth orbit such as ISS, HST, Swift, GALEX need frequent updates to maintain high accuracy.

If accurate predicts are needed, and the last update was more than a few days ago, an update can be done on request. For interplanetary spacecraft, users having high-precision applications such as mission data reduction should contact JPL Solar System Dynamics to verify the status of the specific trajectory in Horizons.

Such files may be used as input to SPICE-enabled visualization and mission design programs, allowing them to quickly retrieve accurate target body observation and data analysis ephemerides without having to integrate equations of motion. It is a file element of the SPICE system devised and maintained by the NAIF Navigation and Ancillary Information Facility team at JPL:.

SPK files may hold ephemerides for any kind of spacecraft, vehicle, or solar system body, but the SPK files produced by Horizons are only for comets and asteroids. Users must have a computer with a FORTRAN or C compiler, or MATLAB or IDL, or Python. Internet access is needed to obtain the necessary SPICE components as well as the SPK files generated by Horizons. SPK files can be produced on demand using the Horizons telnet interface.

Horizons allows a maximum of 20 small-bodies per SPK file. Internal data from the integrator difference tables are written directly to the SPK file as this occurs.

SPK files are capable of storing trajectory data with a fidelity greater than 1 millimeter more accurately than should ever be required. Summary information is stored in the SPK file comment area. Files produced autonomously by Horizons users are considered informal file releases and should not be used for purposes affecting the safety and success of spacecraft hardware or missions without first contacting the JPL Solar System Dynamics Group:.

Although not stored in an SPK file, the statistical uncertainty of the trajectory as a function of time is available from the JPL Horizons system.

This can help interpret the accuracy of the trajectory. The orbit solutions used to produce SPK files on demand are updated in Horizons as new measurements are made.

Therefore, a trajectory in a previously generated SPK file may be superceded by more recent solutions. The small-body database Horizons uses to obtain initial integrator conditions and basic physical parameters can be retrieved and used separately outside of Horizons:. zip file is updated as warranted, but as often as hourly between minutes after the hour to capture database changes.

Unzipping the archive will create a sub-directory with a file called. txt , explaining usage. Other directories will contain the latest FORTRAN source code for a reader library and application program called dxlook which accesses the database interactively or with scripts. They are displayed for general informational purposes only, to confirm the selected object, and are from a variety of sources but primarily collected from the scientific literature and summarized in the following:.

Yoder, C. Clawson, J. Gilmore, These parameters can be used in Horizons computations; includes radius, rotation period, taxonomic class, albedo, etc. Updated a few times a year from the Light Curve Database LCDB, reference below , with some other cases manually input based on data from the radar team and miscellaneous sources:.

Park, W. Folkner; J. Williams; D. Boggs, The Astronomical Journal, 15pp , March. For a list of mass-parameters used by Horizons when converting from state vectors to osculating elements and back , see:.

Other planetary and satellite constants used by Horizons, such as body triaxial dimensions, rotation, and orientation, are from:. Mallama, A. Krisciunas, K. Society of Pacific, , Sep. Urban, S. Stephenson F. A , Nov Morrison, L. Lieske, J. Inquiries can be sent to Jon. Giorgini jpl. gov , who is probably responsible for any errors or omissions. Solar System Dynamics Group, Jet Propulsion Laboratory, Oak Grove Drive, Pasadena, CA USA.

The system described in this document was developed at the Jet Propulsion Laboratory Solar System Dynamics Group , California Institute of Technology, under contract with the National Aeronautics and Space Administration. Giorgini, P. Chodas, D. Giorgini, J. NASA JPL Caltech. Toggle navigation Home. About What does SSD do?

Please enable JavaScript for this website. About App Manual Tutorial Time Spans News. Introduction Connecting to the System General Definitions Object Selection Spacecraft Trajectories in Horizons Coordinate Center Observing Site Selection Other Commands Saving Program Settings Integrator Display Specification of Time Reference Frames Searching for Small-Bodies User-Specified Small-Bodies User-Specified Two-Line Elements TLEs Customizing Output Definition of Observer Table Quantities Close-Approach Tables Understanding Rise, Transit and Set Indicators Constellation Identification Long-Term Ephemerides Statement of Ephemeris Limitations SPK File Generation External DASTCOM Small-Body Database External References Acknowledgements.

Introduction Version 4. The information is grouped into five general types of customizable output requests: Observables plane-of-sky angles, rates, visibility, physical aspect Osculating orbital elements Cartesian state vectors Close approaches to planets and 16 largest asteroids SPK binary trajectory files asteroids and comets only The first four are ASCII tables containing output at user-specified discrete time-steps.

Overview of Usage There are four supported ways to access the program. html Command-line full access, active interactive prompt-based interface : Connect keyboard directly to the system telnet ssd. gov No account or password is required. Specify an object to get a summary data screen. Follow prompts. At any prompt, type? for short or long explanations of the prompt. Transmit results to your system by e-mail or FTP E-mail full access, except for SPK file production, batch interface : Send e-mail to horizons ssd.

An example command file will be mailed back to you. See the Acknowledgements section for contact information. html Connecting to the System Command-line The Horizons on-line ephemeris and data system is available as a command-line terminal service. gov … where is a required port number.

gov However, few modern browsers may recognize this form without additional configuration by the user. If the connection is refused, the two most likely causes are: The port number was not specified or passed along by software: A few PC-type telnet programs do not to fully implement the telnet protocol and may not pass the port number to the network, or may need to be reconfigured to function properly, or may have a different syntax for specifying port numbers.

There is a firewall security restriction at your end Contact your local computer system administrator in this case. html This graphical interface is intended for the more casual user or general public but offers access to program features using pull-down menus, fill-in boxes and clickable buttons. html E-mail Horizons can also be controlled by sending e-mail messages to the address horizons ssd. General Definitions The remainder of this document will use some terms and abbreviations defined below: Reference Frame The set of three axes at right angles to each other that define the cartesian x, y, z basis directions.

East The counter-clockwise direction around the north-pole of rotation. RA Right ascension; the angular distance on the celestial sphere counter-clockwise eastward along the celestial equator from the reference equinox to the meridian of the object.

DEC Declination; the angular distance on the celestial sphere north positive or south negative of the reference frame equator. AZ Azimuth; the angle measured clockwise from the north along the horizon defined by the plane perpendicular to the local zenith to the point where the meridian passing through local zenith and the object intersects the horizon plane.

EL Elevation; the angular distance above or below the plane perpendicular to the local zenith. When an object is at some position, an observer far away will still see it at a prior position that depends on how far away the observer is, due to the finite speed of light Astrometric coordinates are generally used when comparing positions to nearby stars in a star catalog.

Apparent Coordinates Positions or values like RA and DEC which take into account factors that appear to change the target position with respect to the background coordinate system: light-time, the deflection of light due to large or nearby masses, and stellar aberration. Refracted Coordinates Apparent coordinates can additionally be corrected for atmospheric refraction. Small Body Refers to a comet or asteroid for which the trajectory is numerically integrated on demand from an initial set of previously statistically estimated orbital elements in the JPL database.

Major Body Refers to planet, natural satellite, spacecraft, Sun, barycenter, or other objects having pre-computed trajectories. Target Body Refers to the object of interest for which an ephemeris is to be created. Center or coordinate origin, or observering location This is the point to which output quantities for the target such as coordinates are referred: 0,0,0. Primary Body Refers to closest body about which a target body orbits. Interfering Body Refers to the largest body in a system other than the one the observer is on, or the target.

Object Selection When connecting by command-line, the primary thing one must know to use Horizons effectively is how to select objects. There are two categories of objects in Horizons: Major Bodies planets, natural satellites, spacecraft, special cases : Major bodies are represented in pre-computed trajectory files which are interpolated to very accurately retrieve position and velocity at any instant.

Small Bodies comets and asteroids : Small-bodies have their statistically estimated position and velocity at one instant compactly stored in a database as initial conditions and are then numerically integrated on-demand by Horizons, to other times of interest, using the necessary physics.

Major Bodies Type MB to get a list of all major-body strings that can be used to search on. To select a major body, enter one of the following: A string to search on Mars or Trit. Case insensitive. Example targets might be specific craters, topographic features, or spacecraft landing sites.

Long, latitude, h } BODY Cylindrical coordinates: {c: E. Long, DXY, DZ } BODY … where the brackets {} indicate optional components of the general specification. For example, while specifies the target to be the center of the Moon, and Apollo 11 specifies the Apollo 11 landing site as target, the following … g: The same keyword can be used more than once in a search command. gov SSDG analyst Some archival mission trajectories are available. For example, to obtain ….

Non-Earth Sites For non-Earth major bodies, station also represents the body center. Specifying a Predefined Observing Site There are several equivalent ways of specifying an observing location. Element Tables For an osculating element table, the different assumption for abbreviated input of specified center is made that a coordinate center request lacking a symbol is a major body. Code Meaning Mimas body center geo " g " g Mimas " Deimos Deimos body center geo Earth Geocenter g Earth Geocenter User-Defined Topocentric Site Coordinates Many small or recently discovered natural satellites do not have defined rotation models, thus do not support topocentric site definition.

Interpreting non-Earth Observer Tables When selecting a site on a body other than the Earth, some definitions and quantities slightly shift in meaning: Visually interfering body The largest other body in the system. AIRMASS There is no airmass model or airmass cut-off available for non-Earth sites. TIME Time tags refer to the time-scale conversion from TDB on Earth regardless of observer location within the solar system, although clock rates may differ due to the local gravity field and no analogous time-scales are locally defined.

Other Commands Program information: MB Display program news new capabilities, updates, etc. Extended help '? Program controls: LIST Toggle display of small-body match-parameter values. Toggle screen paging scrolling on or off. EMAIL {X} Set your email address to {X} for output delivery. Enter Two-Line Elements input mode artificial sats TTY {R} {C} Check or reset screen size; "tty" or "tty 24 79" to set.

Exit JPL on-line system also "QUIT" or "EXIT". Return to the previous prompt back-up! Storing format default settings: LOAD {macro} Load previously SAVED output-format {macro}. SAVE {macro} DELETE {macro}.. Delete previously saved output-format macro. Short-cuts: Move backward through the prompts by typing -. Quit from ANY prompt by entering q. To use a default or previously entered value , press return.

Saving Program Settings command-line interface only Command-line interactive users may go through program options once, then save all settings for recall during future sessions. Type SAVE {NAME} , where {NAME} contains characters. Input a password that allows you to later DELETE or REPLACE the macro Next time you telnet to Horizons, type LOAD {NAME}.

Your output preferences will then be loaded in as the new defaults. If you make a mistake or want to change a setting later, two commands are relevant: DELETE and SAVE DELETE a macro with command DELETE {NAME}. The last number on the integrator display line is the most recent step size in days. html For observer tables, output may be in either UT or TT timescale. Time Zone Corrections Output time-tags may also be in local civil time. When specifying start time, enter your time-zone correction in the format: YYYY-Mon-Dy HH:MM UT{s}HH{:MM} … where {s} integer hours time-zone difference from UT {:MM} Gregorian and Julian Calendar Dates Input calendar dates Oct and after are assumed to be in the extended Gregorian calendar system.

Here is the progression near the calendar switch point: Calendar Type Calendar Date Julian Day Number Julian Oct In this system, there are no negative years. Output Stepping There are three different ways of specifying when observer-table output should be generated 1.

Fixed time steps Output time steps are specified as integers with some associated units from the set {days, hours, minutes}. Time-varying angular-shift steps: Output is typically at fixed time intervals. Reference Frames Reference frames are used to describe the position and velocity of an object in three-dimensional space.

International Celestial Reference Frame ICRF The primary reference frame is the ICRF. International Terrestrial Reference Frame ITRF93 This is the Earth body-frame to which Earth station coordinates are referred, and is produced from the Earth TOD frame with additional small GPS-derived polar motion corrections.

Asteroid OR comet name fragment C DES Object designation R EPOCH Julian Date of osculating elements R CALEPO Calendar date of osc. elements; YYYYMMDD. ffff R A Semi-major axis au R EC Eccentricity R IN Inclination of orbit plane DEG wrt ecliptic R OM Perihelion Julian Date R CALTP Perihelion calendar date; YYYYMMDD.

ffff R MA Mean anomaly DEG R PER Orbital period YRS R RAD Object radius KM R GM Perihelion distance au R ADIST Aphelion distance au R ANGMOM Heliocentric dist. au of ascending node R DDN au of descending node R L Ecliptic longitude of perihelion DEG R B Ecliptic latitude of perihelion DEG I NOBS Number of astrometric determinations in solution C SOLN Solution ID The next parameters are ASTEROID SPECIFIC.

Asteroid name fragment designation if unnamed R B-V B-V color asteroid R H Absolute magnitude parameter asteroid R G Rotational period, hrs asteroid R ALBEDO Geometric albedo asteroid C STYP Spectral type, Tholen scheme asteroid The next parameters are COMET SPECIFIC.

Comet name fragment designation if unnamed I COMNUM Comet number R M Total absolute magnitude comet R M Nuclear absolute magnitude comet R K Total magnitude scaling factor comet R K Nuclear magnitude scaling factor comet R PHCOF Directives There are 5 special directives that may be used to limit or control searches: Directive Description COM Limit search to comets only AST Limit search to asteroids only LIST Display parameter values for matched objects.

A filter that guarantees only one comet apparition will be returned for each comet. If "CAP;" is specified, the search is automatically recognized as being a comets-only search. Julian Day Number of osculating elements TDB timescale, JDTDB EC Eccentricity QR Perihelion distance au TP Perihelion Julian Day Number OM Mean anomaly DEGREES A Semi-major axis au N Optional Inputs RAD Object radius KM AMRAT Setting to a non-zero value activates calculation of solar radiation pressure acceleration.

Total absorption is assumed, so scale the value to account for reflectivity. For asteroids, additional OPTIONAL parameters can be given: H Absolute magnitude parameter asteroid G Total absolute magnitude comet M Nuclear absolute magnitude comet K Total magnitude scaling factor comet K Nuclear magnitude scaling factor comet PHCOF model constant, normalizing distance, au [2.

model constant, normalizing factor [0. model constant, exponent m [2. model constant, exponent n [5. model constant, exponent k [4. The standard TLE format can be cut-and-pasted into Horizons here. For example: SC-1 1 U A Multiple TLE sets can be input, up to some system limit which may change but is nominally sets data lines … name lines are not counted Input TLEs can be extrapolated over a limited time-span before and after the first and last TLE epochs.

The data does not have to be in chronological order, though that would be a normal thing to do. Local TLE ID Number: Internally, the TLE ID columns , so in the example above is prefixed with a -8 such that the temporary Horizons ID would be User-Defined TLE Objects as Observatories Once defined, a TLE object can be used in the same way as other objects available from this system.

The output lunar ephemeris would then be with respect to the user-input TLE object. Examples of satellite-to-satellite specification: To observe the input TLE object from the already-in-Horizons International Space Station ISS , request target TLE or , for the example above , then set observing point as Cartesian state vector table Overview and usage: This type of table provides the position and velocity at an instant of any object with respect to any major body or specified point on its surface.

html … but not through Horizons, which creates and distributes SPK files for asteroids and comets only. The DEFAULT is table type 3 with no statistical uncertainties. Osculating orbital elements table Overview and usage: The instantaneous osculating orbital elements of an object with respect to a planet or barycenter. Targets can also be specified as surface coordinates on another major body, such as a crater. A detailed explanation of the user-selectable output quantities is given later, but are briefly listed here along with their selection integer: 1.

Local apparent sidereal time 8. Airmass and Visual Magnitude Extinction 9. Illuminated fraction Defect of illumination Target angular diameter One-way down-leg light-time Sun-Target-Observer ~PHASE angle Observer-Primary-Target angle Orbit plane angle Constellation Name Galactic longitude and latitude Local apparent SOLAR time Local apparent hour angle ff DD MM SS.

ffffff DD MM SS. Includes dip and refraction Earth only. GEO -- Geometric horizon. Includes refraction Earth only. RAD -- Radar horizon. Geometric horizon, no refraction. Close-approach table small-bodies ONLY Overview and usage: Requesting this table type via telnet or e-mail activates monitoring of close-approaches by the small-body target to the planets and 16 most massive asteroid perturbers.

Close-approach detection limits that trigger output can be changed by users, but the default values are: Other small-bodies i. For example, to change the Earth encounter limit from 0. Definition of Observer Table Quantities The detailed description of the selectable observer table quantities follows. Time One output line for each step. Specific Quantities 1. Labels: R. Adjusted for light-time, gravitational deflection of light, and stellar aberration. No refraction model is available.

airless, HMS-DMS format R. refracted, HMS-DMS format R. airless, decimal degrees format R. refracted, decimal degrees format 3. Adjusted for light-time, the gravitational deflection of light, stellar aberration, precession and nutation.

There is an optional approximate adjustment for atmospheric refraction Earth only. Rates: azimuth and elevation AZ-EL The rate of change of target apparent azimuth and elevation airless.

Local Apparent Sidereal Time The angle measured westward in the body true-equator of-date plane from the meridian containing the body-fixed observer to the meridian containing the true Earth equinox defined by intersection of the true equator of date with the ecliptic of date.

Units are HH MM SS. ffff or decimal hours HH. Airmass is the ratio of the absolute optical airmass at the targets' refracted elevation angle with the absolute optical airmass at zenith. Also output is the estimated visual magnitude extinction due to atmosphere, as seen by the observer.

The Saturn rings are included when phase angle is less than 6. Reduced precision values are output for phase angles greater than degrees, since the errors could be large and unknown.

Some comets have custom magnitude laws that are described at the end of the requested ephemeris output. Illuminated fraction Percent of target objects' assumed circular disk illuminated by Sun phase , as seen by observer.

Defect of illumination The maximum angular width of the target body's assumed circular disk diameter NOT illuminated by the Sun. The observer cannot be on the primary body. Light-time is considered. Target angular diameter The equatorial angular width of the target body full disk, if it were fully illuminated and visible to the observer.

If the target body diameter is unknown, "n. Labels: Ang-diam This is not exactly the same as the "nearest point" for a non-spherical target shape since the center of the disc might not be the point closest to the observer , but is generally very close if not a very irregular body shape. The IAU rotation models are used except for Earth and MOON, which use higher-precision models. For the gas giants Jupiter, Saturn, Uranus and Neptune, IAU longitude is based on the "System III" prime meridian rotation angle of the magnetic field.

Down-leg light travel-time from target to observer is taken into account. Latitude is the angle between the equatorial plane and perpendicular to the reference ellipsoid of the body and body oblateness thereby included. The reference ellipsoid is an oblate spheroid with a single flatness coefficient in which the y-axis body radius is taken to be the same value as the x-axis radius.

Whether longitude is positive to the east or west for the target will be indicated at the end of the output ephemeris. Units: DEGREES Labels: ObsSub-LON ObsSub-LAT The apparent planetodetic longitude and latitude of the center of the target disc as seen from the Sun, as seen by the observer at print-time.

Light travel-time from Sun to target and from target to observer is taken into account. Latitude is the angle between the equatorial plane and the line perpendicular to the reference ellipsoid of the body. Uses IAU rotation models except for Earth and Moon, which uses a higher precision models. Values for Jupiter, Saturn, Uranus and Neptune are Set III, referring to rotation of their magnetic fields.

Units: DEGREES Labels: SunSub-LON SunSub-LAT A negative distance indicates the sub-solar point center of disc is on the hemisphere hidden from the observer. ang SN. ds A negative distance indicates the north-pole is on the hidden hemisphere.

ang NP. Units: DEGREES Labels: hEcl-Lon hEcl-Lat A positive "rdot" means the target was moving away from the Sun, negative indicates movement toward the Sun. Labels: r rdot A positive "deldot" means the target is moving away from the observer, negative indicates movement toward the observer. Labels: delta deldot Down-leg light-time Target one-way down-leg light-time, as seen by observer. The elapsed time since light observed at print-time left or reflected off the target.

These are absolute values of the velocity vectors total speeds and do NOT indicate direction of motion. Target is aligned with Sun center no lead or trail The S-O-T solar elongation angle is numerically the minimum separation angle of the Sun and target in the sky in any direction. It does NOT indicate the amount of separation in the leading or trailing directions, which would be defined along the equator of a spherical coordinate system.

Sun-Target-Observer angle The Sun-Target-Observer angle; the interior vertex angle at target center formed by a vector from the target to the apparent center of the Sun at reflection time on the target and the apparent vector from target to the observer seen at print-time. Closely approximates true PHASE ANGLE requestable separately but is slightly different at the few arcsecond level in that it includes stellar aberration on the down-leg from target to observer.

Units: DEGREES Labels: S-T-O Target-Observer-Moon angle and illuminated fraction Lunar elongation angle and fraction of Moon that is lit by the Sun. The apparent angle between the target and the Moon's center or largest "visually interfering" body in the system , seen from the observers' location, along with fraction of the lunar disk that is illuminated by the Sun.

A negative lunar elongation angle indicates the target center is behind the Moon. Observer-Primary-Target angle Observer-Primary-Target angle; apparent angle between a target satellite, its primarys' center and an observer at print time.

Interior vertex angle at the primary. Units: DEGREES Labels: O-P-T Computed for small-bodies only and primarily intended for ACTIVE COMETS , "PsAng" is an indicator of the comets' gas-tail orientation in the sky being in the anti-sunward direction while "PsAMV" is an indicator of dust-tail orientation. Units: DEGREES Labels: PsAng PsAMV Orbit plane angle Angle between observer and target orbital plane, measured from center of target at the moment light seen at observation time leaves the target.

Small-bodies only. Units: DEGREES. Labels: PlAng Constellation ID The 3-letter abbreviation for the constellation name of targets' astrometric position, as defined by the IAU boundary delineation. See documentation for list of abbreviations. Labels: Cnst TDB-UT Difference between the uniform Barycentric Dynamical time-scale and the Earth-rotation dependent Universal Time.

Prior to , the difference is with respect to UT1 TDB-UT1 and the 0. For and later, the difference is with respect to UTC TDB-UTC and periodic terms less than 1. e-6 second are ignored. Values beyond the next July or January 1st may change if a leap-second is later required by the IERS. Values from the present date forward through the next ~73 days are predictions. Beyond that prediction interval, the last prediction is taken as a constant for all future dates.

Units: SECONDS Labels: TDB-UT For non-Earth sites, the Earth ecliptic at reference-frame standard epoch is used J or B Units: DEGREES Labels: ObsEcLon ObsEcLat Target rotation model is indicated in the header. Units: DEGREES Labels: N. Pole-RA N. Pole-DC Units: DEGREES Labels: GlxLon GlxLat Local Apparent Solar Time Local Apparent SOLAR Time at observing site.

Units are HH. fffffffffff decimal hours or HH MM SS. ffff Earth to site light-time Instantaneous light-time of the station with respect to Earth center at print-time.

The geometric or "true" separation of site and Earth center, divided by the speed of light. Plane-of-sky RA and DEC pointing uncertainty Uncertainty in Right-Ascension and Declination.

Plane-of-sky error ellipse Plane-of-sky POS error ellipse data. These quantities summarize the targets' 3-dimensional 3-standard-deviation formal uncertainty volume projected into a reference plane perpendicular to the observers' line-of-sight. Plane-of-sky ellipse RSS pointing uncertainty The Root-Sum-of-Squares RSS of the 3-standard deviation plane-of-sky error ellipse major and minor axes. This single pointing uncertainty number gives an angular distance a circular radius from the targets' nominal position in the sky that encompasses the error-ellipse.

Uncertainties in plane-of-sky radial direction Range and range rate radial velocity formal 3-standard-deviation uncertainties. Radar uncertainties plane-of-sky radial direction Doppler radar uncertainties at S-band MHz and X-band MHz frequencies, along with the round-trip total delay to first-order. True anomaly angle Apparent true anomaly angle of the targets' heliocentric orbit position; the angle in the targets' instantaneous orbit plane from the orbital periapse direction to the target, measured positively in the direction of motion.

The position of the target is taken to be at the moment light seen by the observer at print-time would have left the center of the object. That is, the heliocentric position of the target used to compute the true anomaly is one down-leg light-time prior to the print-time.

Local apparent hour angle Local apparent HOUR ANGLE of target at observing site. The angle between the observers' meridian plane, containing Earth's axis of-date and local zenith direction, and a great circle passing through Earth's axis-of-date and the targets' direction, measured westward from the zenith meridian to target meridian along the equator.

Negative values are angular times UNTIL transit. Positive values are angular times SINCE transit. Units: sHH. Phase angle and bisector "phi" is the true PHASE ANGLE at the observers' location at print time.

For an otherwise uniform ellipsoid, the time when its long-axis is perpendicular to the PAB direction approximately corresponds to lightcurve maximum or maximum brightness of the body. PAB is discussed in Harris et al. Units: DEGREES Labels: phi PAB-LON PAB-LAT It is referred to a coordinate system where the x-axis is the equinox direction defined by the targets' instantaneous pole direction and heliocentric orbit plane at reflection time, and is measured positively in an eastward direction counter-clockwise around the positive pole of the solar system angular momentum vector.

Therefore, to determine Earth seasons, request quantity 31 "ObsEcLon" as seen from the geocenter, with the Sun as a target. Sky motion: angular rate, direction position angle, and path angle Total apparent angular rate of the target in the plane-of-sky.

Sky brightness and target visual signal-to-noise ratio SNR Sky brightness due to moonlight scattering by Earth's atmosphere at the target's position in the sky. Output only for topocentric Earth observers when both the Moon and target are above the local horizon and the Sun is in astronomical twilight or further below the horizon, and the target is not the Moon or Sun.

If all conditions are not met, "n. Galactic brightness, local sky light-pollution and weather are NOT considered. Lunar opposition surge is considered. This is the approximate visual signal-to-noise ratio of the target's brightness divided by lunar sky brightness. User-specifications for this table can include the time-span to check, the radius of detection for planets and asteroids, the maximum uncertainty in time-of-close-approach before the table is automatically cut-off, and whether to output optional error ellipse information projected into the B-plane The B-plane mentioned above is defined by the three orthogonal unit vectors T, R, and S the origin being the body center.

Calendar dates prior to Oct are in the Julian calendar system. Later calendar dates are in the Gregorian system. This angle is positive when clockwise around the -S axis, negative when counter-clockwise. Non-zero values less than approximately 0. Understanding Rise, Elevation-max, Transit and Set Indicators There are 2 ways the system can be used to mark rise, maximum elevation, transit, and set RETS conditions: 1 activate the RTS-only print option for an observer-table request OR 2 request a general observer table with output step interval less than 30 minutes.

Normal Table RETS-Marker Mode RETS is indicated automatically during normal observer table generation, when the step-size is less than 30 minutes. Select by specifying, when prompted at 1 or 2, one of these symbols: TVH True visual horizon plane. The horizon seen by an observer on the reference ellipsoid. Allows for horizon dip effect and atmospheric refraction, but not local topography. Geometric horizon plane. The horizon is defined by the plane perpendicular to the reference ellipsoid local zenith no horizon dip.

Atmospheric refraction is estimated.

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The increased transparency brought about by Open Banking brings a vast array of additional benefits, such as helping fraud detection companies better monitor customer accounts and identify problems much earlier. To instead select the small-body named Io immediately, provide more information by specifying it one of these ways:. Asteroid Physical Parameters These parameters can be used in Horizons computations; includes radius, rotation period, taxonomic class, albedo, etc. SPK files can be produced on demand using the Horizons telnet interface. For example, azimuth and elevation for a geocentric ephemeris, or uncertainties for an object with no covariance in the database. Nov 17, · Surface Studio vs iMac — Which Should You Pick?

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