API VERSION: 1.2
API SOURCE: NASA/JPL Horizons API

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 Revised: Jun 11, 2022         Mars Orbiter Mission (MOM)                   -3
         https://www.isro.gov.in/Spacecraft/mars-orbiter-mission-spacecraft 
  
 LAUNCH DATE:                   EARTH DEPARTURE:           MARS ARRIVAL DATE:
 Nov 5, 2013 09:08 UTC          November 30, 2013          September 24, 2014 

 LAUNCH VEHICLE:
  This Indian Space Research Organization (ISRO) mission was launched on a 
  PSLV-C25 launch vehicle from Satish Dhawan Space Center (SDSC), Sriharikota,
  India.  (PSLV= Polar Satellite Launch Vehicle)

 BACKGROUND:
  Mars Orbiter Mission (MOM), or "Mangalyaan" (Hindi for "Mars Craft") is 
  India's first interplanetary mission to Mars with a spacecraft designed 
  for elliptical orbit. The mission is primarily technology development. 
  The spacecraft has been configured to observe the physical features of 
  Mars and carry out limited study of the Martian atmosphere using five 
  instruments (below) over a span of 6-8 months.

  The spacecraft was initially inserted into a 246 x 23566 km Earth parking 
  orbit (inclination 19.2 deg. wrt equator). Six engine burns will eventually
  establish hyperbolic escape trajectory on 2013-Nov-30 (the sixth being
  648 m/s for "Trans Mars Injection).

  Arrival at Mars periapse is nominally scheduled for 2014-Sep-24 when a 
  capture burn (MOI) will slow it into a 366 x 80000 km Mars orbit with
  inclination 150 degrees and period 76.7 hours.

 SCIENCE INSTRUMENTS (15 kg):
  * Mars Color Camera (MCC)
  * Thermal Infrared Imaging Spectrometer (TIS)
  * Methane Sensor for Mars (MSM)
  * Mars Exospheric Neutral Composition Analyser (MENCA)
  * Lyman Alpha Photometer (LAP)

 SPACECRAFT PHYSICAL PROPERTIES:
  Based on a modified IRS/INSAAT/Chandrayaan-1 bus; roughly a 1.5 m cube
  of aluminum and composite reinforced plastic.
  
  Total launch mass: 1340 kg
  Spacecraft mass  :  488  kg
  Propulsion       : 440 N bi-propellant system (MMH + N2O4) with additional 
                      safety and redundancy features for MOI. 
  Propellant mass  : 852 kg
  Power system     : Solar array, 3 panels 1.8m X 1.4 m 
                     840 W (in Martian orbit), 
                     Battery is 36AH Li-ion
  Communications   : Low Gain (LGA), Medium Gain (MGA), 2.2-m High GAIN (HGA)

 SPACECRAFT TRAJECTORY 
  Merge of DSN/JPL/Nav data-fit tag-up through 2022-Jun-18, prediction 
  thereafter. 

  The interval from 2019-Oct-01 to 2020-Apr-29 may drift slightly from actual, 
  with discontinuties on 2020-Mar-30 and 2020-Apr-18, when the trajectory was 
  updated from a new initial ISRO state integration, not a new data fit.

  Name                                         Start (TDB)        Stop (TDB)
  ---------------------------------------  -----------------  -----------------
  Concatenated trajectories                2013-Nov-05 09:54  2020-May-15 00:01
  ISRO-MOM-2020-0*-**-v1                   2020-May-15 00:01  2020-Jul-10 00:11
  ISRO-MOM-202*-**-**-OD2***-***-v*        2020-Jul-10 00:11  2022-Nov-26 00:00
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No ephemeris for target "Mars Orbiter Mission (MOM) (spacecraft)" after A.D. 2022-NOV-26 00:00:00.0000 UT