*******************************************************************************
 Revised: Apr 21, 2022    Mars Reconnaisance Orbiter (MRO)  / (Sun)         -74
                            http://marsprogram.jpl.nasa.gov/mro/

 NOTE (2014-Jun-10):
  C/2013 A1 (Siding Spring) will have its closest approach to Mars on Oct 19, 
  2014 at a distance of about 135,000 km. 
  
  Location of predicted MRO minimum risk from comet particles 
  (occultation mid-point):

   Latitude: 7.6083 deg
   Time:     19-OCT-2014 20:08:07.182392952 ET (CSS CA + 98 min)

 MISSION LAUNCH DATE:                                        MARS ARRIVAL DATE:
  Aug 12, 2005 11:43 UTC (it's up and away)                  March 10, 2006

  Notes:  Aug 10, 2005: Original launch was scrubbed (gyros)
          Aug 11, 2005: Second attemped was launch scrubbed (fueling sensors)

 LAUNCH VEHICLE:
  Atlas V two-stage. Separation from Centaur: 2005-Aug-12 12:40:51.68 UTC

 BACKGROUND:
  MRO aerobraked for 6 months from the post-insertion 35 hour orbit, saving 
  450 kg of fuel. Primary science phase starts in November of 2006 and 
  nominally operates for 2 Earth years from a 112 minute, near circular polar 
  orbit. 

 SPACECRAFT PHYSICAL PROPERTIES:
  Height=  6.5 m                          Solar panels =   20 m^2
  Width = 13.6 m (tip-to-tip)             launch weight= 2180 kg

 SPACECRAFT TRAJECTORY: 
  Trajectory starts after Centaur launch stage separation (cruise phase).
  Trajectory after 2022-Apr-21 is PREDICTION.

  Trajectory files (from MRO Nav., JPL)      Start (TDB)         End (TDB) 
  --------------------------------------  -----------------  -----------------
  mro_cruise                              2005-Aug-12 12:42  2006-Mar-10 22:06
  mro_ab                                  2006-Mar-10 22:06  2006-Sep-12 06:40
  misc reconstruction (mro_psp1-62)       2006-Sep-12 06:40  2022-Apr-01 01:01
  mro_psp_rec                             2022-Apr-01 01:01  2022-Apr-17 16:34
  mro_psp                                 2022-Apr-17 16:34  2022-Sep-02 02:55
*******************************************************************************


*******************************************************************************
Ephemeris / API_USER Mon May 23 05:19:05 2022 Pasadena, USA      / Horizons
*******************************************************************************
Target body name: Mars Reconnaissance Orbiter (spacecraft) (-74) {source: MRO_MERGED}
Center body name: Mars Barycenter (4)             {source: DE441}
Center-site name: BODY CENTER
*******************************************************************************
Start time      : A.D. 2022-May-22 00:00:00.0000 TDB
Stop  time      : A.D. 2022-May-23 00:00:00.0000 TDB
Step-size       : 720 minutes
*******************************************************************************
Center geodetic : 0.00000000,0.00000000,0.0000000 {E-lon(deg),Lat(deg),Alt(km)}
Center cylindric: 0.00000000,0.00000000,0.0000000 {E-lon(deg),Dxy(km),Dz(km)}
Center radii    : (undefined)                                                  
Output units    : KM-S
Output type     : GEOMETRIC cartesian states
Output format   : 1 (position only)
Reference frame : Ecliptic of J2000.0
*******************************************************************************
JDTDB
   X     Y     Z
*******************************************************************************
$$SOE
2459721.500000000 = A.D. 2022-May-22 00:00:00.0000 TDB 
   2.615353755143860E+03  5.410112782583881E+02 -2.491150185148976E+03
2459722.000000000 = A.D. 2022-May-22 12:00:00.0000 TDB 
  -3.495159540344693E+03 -5.551069096048225E+02  9.252465537814477E+02
2459722.500000000 = A.D. 2022-May-23 00:00:00.0000 TDB 
   3.491185350937938E+03  4.083500559468409E+02  1.096540860137564E+03
$$EOE
*******************************************************************************
 
TIME

  Barycentric Dynamical Time ("TDB" or T_eph) output was requested. This
continuous relativistic coordinate time is equivalent to the relativistic
proper time of a clock at rest in a reference frame comoving with the
solar system barycenter but outside the system's gravity well. It is the
independent variable in the solar system relativistic equations of motion.

  TDB runs at a uniform rate of one SI second per second and is independent
of irregularities in Earth's rotation.

  Calendar dates prior to 1582-Oct-15 are in the Julian calendar system.
Later calendar dates are in the Gregorian system.

REFERENCE FRAME AND COORDINATES

  Ecliptic at the standard reference epoch

    Reference epoch: J2000.0
    X-Y plane: adopted Earth orbital plane at the reference epoch
               Note: IAU76 obliquity of 84381.448 arcseconds wrt ICRF X-Y plane
    X-axis   : ICRF
    Z-axis   : perpendicular to the X-Y plane in the directional (+ or -) sense
               of Earth's north pole at the reference epoch.

  Symbol meaning:

    JDTDB    Julian Day Number, Barycentric Dynamical Time
      X      X-component of position vector (km)
      Y      Y-component of position vector (km)
      Z      Z-component of position vector (km)

ABERRATIONS AND CORRECTIONS

 Geometric state vectors have NO corrections or aberrations applied.

Computations by ...

    Solar System Dynamics Group, Horizons On-Line Ephemeris System
    4800 Oak Grove Drive, Jet Propulsion Laboratory
    Pasadena, CA  91109   USA

    General site: https://ssd.jpl.nasa.gov/
    Mailing list: https://ssd.jpl.nasa.gov/email_list.html
    System news : https://ssd.jpl.nasa.gov/horizons/news.html
    User Guide  : https://ssd.jpl.nasa.gov/horizons/manual.html
    Connect     : browser        https://ssd.jpl.nasa.gov/horizons/app.html#/x
                  API            https://ssd-api.jpl.nasa.gov/doc/horizons.html
                  command-line   telnet ssd.jpl.nasa.gov 6775
                  e-mail/batch   https://ssd.jpl.nasa.gov/ftp/ssd/hrzn_batch.txt
                  scripts        https://ssd.jpl.nasa.gov/ftp/ssd/SCRIPTS
    Author      : Jon.D.Giorgini@jpl.nasa.gov
*******************************************************************************

