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232 lines
11 KiB
Plaintext
232 lines
11 KiB
Plaintext
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Revised: Mar 27, 2018 Tesla Roadster (spacecraft) -143205
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(solution #10)
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Tesla Roadster (AKA: Starman, 2018-017A)
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NOTE:
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Visibility:
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20th magnitude until Feb 20,
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22nd magnitude through mid-April
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Brighter than 26th magnitude into mid-June
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2018-Mar-01: Radial non-gravitational acceleration A1 estimated from data
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(nominally solar radiation pressure)
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2018-Mar-27: Two reporting sites (J04 & K93) extend data arc one month.
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A1 estimate of s10 is reduced 1.2-sigma compared to s9.
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LAUNCHED:
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2018-Feb-06 20:45 UTC by Falcon Heavy (FH-1) from Kennedy Space Center, USA
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(launchpad 39A)
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BACKGROUND:
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Dummy payload from the first launch of SpaceX Falcon Heavy launch vehicle.
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Consists of a standard Tesla Roadster automobile and a spacesuit-wearing
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mannequin nicknamed "Starman".
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Also includes a Hot Wheels toy model Roadster on the car's dash with a
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mini-Starman inside. A data storage device placed inside the car contains
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a copy of Isaac Asimov's "Foundation" novels. A plaque on the attachment
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fitting between the Falcon Heavy upper stage and the Tesla is etched with
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the names of more than 6,000 SpaceX employees.
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After orbiting the Earth for 5 hours, a third burn by the second stage was
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completed at approximately 02:30 UTC Feb 7, placing the dummy payload in a
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heliocentric orbit having a perihelion of 0.99 au and aphelion ~1.67 au.
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The object stack consists of a Merlin 1D Vacuum second stage with Extended
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Nozzle, Payload Attachment Fitting, and Tesla Roadster on mount.
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Roadster mass: ~1250 kg (with batteries), ~800 kg (without ESS/batteries)
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TRAJECTORY:
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This trajectory is based on JPL solution #10, a fit to 364 ground-based
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optical astrometric measurements spanning 2018 Feb 8.2 to March 19.1
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Trajectory name Start (TDB) Stop (TDB)
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-------------------------------- ----------------- -----------------
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tesla_s10 2018-Feb-07 03:00 2090-Jan-01 00:00
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Encounter predictions for s10 (w/radial 1/r^2 non-gravitational acceleration)
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Date (TDB) Body CA Dist MinDist MaxDist Vrel TCA3Sg Nsigs P_i/p
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----------------- ----- ------- ------- ------- ------ ------ ------ ------
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2018 Feb 08.09690 Moon .000936 .000936 .000936 3.961 0.41 47509. 0.000
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2020 Oct 07.26768 Mars .049530 .048923 .050242 8.150 27.40 6.63E5 0.000
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2035 Apr 22.35934 Mars .015504 .004378 .027978 8.219 170.47 31247. 0.000
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2047 Jan 11.89023 Earth .031919 .031716 .032123 4.493 249.70 78398. 0.000
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2050 Mar 19.52949 Earth .119113 .113778 .124369 7.397 538.54 2.61E5 0.000
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2052 Sep 05.15606 Mars .176363 .172469 .180319 5.738 2185.5 8.68E5 0.000
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2067 Apr 15.90202 Mars .043270 .025712 .061471 7.192 1115.0 42565. 0.000
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2084 Sep 17.92284 Mars .116962 .093449 .141170 9.753 787.45 6.55E5 0.000
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2085 Jan 01.96490 Earth .083063 .049368 .112186 6.224 5208.9 1.00E5 0.000
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2088 Mar 09.95754 Earth .049146 .033491 .063322 5.106 4505.2 1.17E5 0.000
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Date = Nominal encounter time (Barycentric Dynamical Time)
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CA_Dist = Highest probability close approach distance to body, au
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MinDist = 3-sigma minimum encounter distance, au
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MaxDist = 3-sigma maximum encounter distance, au
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Vrel = Relative velocity at nominal encounter time, km/s
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TCA3Sg = 3-sigma uncertainty in close encounter time, minutes
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Nsigs = Number of sigmas to encounter body at nominal encounter time
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P_i/p = Linearized probability of impact
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NOTE:
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How to obtain optional statistical uncertainty output & generate an SPK file:
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Since this is a spacecraft and not part of the asteroid and comet database
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which normally holds orbit covariance data, some functions like statistical
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output and SPK file generation aren't automatically available for this object.
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However, such optional extended output is possible with some extra steps.
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To propagate statistical uncertainties for this object, the full statistical
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orbit solution (given below) can be manually input back into Horizons as a
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"user-defined object" using the telnet or e-mail interfaces (not possible
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with the browser interface).
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To do this and activate statistical or SPK file output ...
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Using the telnet interface (command-line "telnet ssd.jpl.nasa.gov 6775"),
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enter ";" to drop into user-input mode then cut-and-paste each line shown
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below, one at a time. The lines of numbers after SRC must be in the order
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shown.
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For SPK file generation, only the first four lines need be input: the
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EPOCH, orbital element lines starting with "EC" and "OM", and the
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non-gravitational acceleration model (line starting with "A1").
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SRC lines are needed only for (optional) statistical output and the
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H & G values only for (optional) visual magnitude output.
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EPOCH= 2458164.5
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EC= .2585469914787243 QR= .9860596231806226 TP= 2458153.620483722645
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OM= 317.3549094214575 W = 177.3203028023227 IN= 1.088451292866039
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EST=A1 A1= 2.960683526738534E-9 R0= 1. ALN= 1. NM= 2. NK= 0.
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SRC= -2.057839421666802E-7 7.966781900129693E-9 -1.720426606925749E-9
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-4.722542923190676E-7 2.197679131968537E-9 -1.230413802372471E-6
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-2.500290306870021E-7 -3.361070889248183E-9 -1.765963020682463E-5
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-3.047907547965759E-7 -4.640202045440381E-7 -4.271481116360573E-9
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2.657789409005983E-5 1.726818074599357E-6 -1.359673746135991E-6
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-2.478836748687631E-5 -2.309863204867099E-8 -.0002351644867403515
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-1.875169281895894E-6 -2.063647245529267E-6 -1.670539551586607E-6
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-4.019207817588603E-6 -3.128134469402375E-9 -3.034540373576942E-5
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1.733661692209129E-7 -7.052327854535979E-7 -2.650181216776434E-7
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-1.310976135791957E-10
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H= 25.289 G= 0.15
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When done, press a blank return to exit input mode.
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Enter "J" at the prompt to indicate heliocentric J2000 ecliptic data has
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been supplied. Then at the next prompt, input an arbitrary name
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(i.e., Roadster).
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Horizons will then proceed as usual, but with statistical output and SPK
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file generation now available as options.
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A basic and identical tracking ephemeris can be produced without doing any
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of this, but statistical uncertainty quantities requested will be marked
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"n.a.", meaning not available, and SPK generation won't be an option.
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NOTE: long-term predictions
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Over time, trajectory prediction errors could increase more rapidly than
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the formal statistics indicate due to unmodeled thermal re-radiation or
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outgassing accelerations that are not currently characterized but may exist.
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*******************************************************************************
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*******************************************************************************
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Ephemeris / API_USER Mon May 23 04:45:58 2022 Pasadena, USA / Horizons
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*******************************************************************************
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Target body name: SpaceX Roadster (spacecraft) (-143205) {source: tesla_s10}
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Center body name: Solar System Barycenter (0) {source: DE441}
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Center-site name: BODYCENTRIC
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*******************************************************************************
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Start time : A.D. 2022-May-22 00:00:00.0000 UT
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Stop time : A.D. 2022-May-23 00:00:00.0000 UT
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Step-size : 720 minutes
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*******************************************************************************
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Target pole/equ : No model available
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Target radii : (unavailable)
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Center geodetic : 0.00000000,0.00000000,0.0000000 {E-lon(deg),Lat(deg),Alt(km)}
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Center cylindric: 0.00000000,0.00000000,0.0000000 {E-lon(deg),Dxy(km),Dz(km)}
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Center pole/equ : ICRF
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Center radii : (undefined)
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Target primary : Earth
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Vis. interferer : None
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Rel. light bend : Sun {source: DE441}
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Rel. lght bnd GM: 1.3271E+11 km^3/s^2
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Atmos refraction: NO (AIRLESS)
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RA format : HMS
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Time format : CAL
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EOP file : eop.220519.p220812
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EOP coverage : DATA-BASED 1962-JAN-20 TO 2022-MAY-19. PREDICTS-> 2022-AUG-11
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Units conversion: 1 au= 149597870.700 km, c= 299792.458 km/s, 1 day= 86400.0 s
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Table cut-offs 1: Elevation (-90.0deg=NO ),Airmass n.a. , Daylight (NO )
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Table cut-offs 2: Solar elongation ( 0.0,180.0=NO ),Local Hour Angle( 0.0=NO )
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Table cut-offs 3: RA/DEC angular rate ( 0.0=NO )
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*******************************************************************************
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Date__(UT)__HR:MN delta GlxLon GlxLat
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**************************************************************
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$$SOE
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2022-May-22 00:00 1.8974772217E+08 153.481630 -41.900757
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2022-May-22 12:00 1.8945940676E+08 153.792612 -41.651777
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2022-May-23 00:00 1.8917095486E+08 154.102144 -41.401193
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$$EOE
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*******************************************************************************
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Column meaning:
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TIME
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Times PRIOR to 1962 are UT1, a mean-solar time closely related to the
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prior but now-deprecated GMT. Times AFTER 1962 are in UTC, the current
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civil or "wall-clock" time-scale. UTC is kept within 0.9 seconds of UT1
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using integer leap-seconds for 1972 and later years.
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Conversion from the internal Barycentric Dynamical Time (TDB) of solar
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system dynamics to the non-uniform civil UT time-scale requested for output
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has not been determined for UTC times after the next July or January 1st.
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Therefore, the last known leap-second is used as a constant over future
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intervals.
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Time tags refer to the UT time-scale conversion from TDB on Earth
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regardless of observer location within the solar system, although clock
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rates may differ due to the local gravity field and no analog to "UT"
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may be defined for that location.
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Any 'b' symbol in the 1st-column denotes a B.C. date. First-column blank
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(" ") denotes an A.D. date. Calendar dates prior to 1582-Oct-15 are in the
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Julian calendar system. Later calendar dates are in the Gregorian system.
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NOTE: "n.a." in output means quantity "not available" at the print-time.
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'delta' =
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Apparent range ("delta", light-time aberrated) of the target center relative
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to the observer. Units: KM
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'GlxLon GlxLat' =
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Observer-centered Galactic System II (post WW II) longitude and latitude
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of the target centers' apparent position, with light-time, gravitational
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deflection of light, and stellar aberrations. Units: DEGREES
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Computations by ...
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Solar System Dynamics Group, Horizons On-Line Ephemeris System
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4800 Oak Grove Drive, Jet Propulsion Laboratory
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Pasadena, CA 91109 USA
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General site: https://ssd.jpl.nasa.gov/
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Mailing list: https://ssd.jpl.nasa.gov/email_list.html
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System news : https://ssd.jpl.nasa.gov/horizons/news.html
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User Guide : https://ssd.jpl.nasa.gov/horizons/manual.html
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Connect : browser https://ssd.jpl.nasa.gov/horizons/app.html#/x
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API https://ssd-api.jpl.nasa.gov/doc/horizons.html
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command-line telnet ssd.jpl.nasa.gov 6775
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e-mail/batch https://ssd.jpl.nasa.gov/ftp/ssd/hrzn_batch.txt
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scripts https://ssd.jpl.nasa.gov/ftp/ssd/SCRIPTS
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Author : Jon.D.Giorgini@jpl.nasa.gov
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*******************************************************************************
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