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

******************************************************************************
 Revised: Sep 01, 2026    Chandrayaan-2 Orbiter Spacecraft / (Moon)       -152 

 NOTE: This is the ORBITER trajectory. The lander ("Vikram") separated from 
       the orbiter on 2019-Sep-02 07:45 UTC. The LANDER trajectory ID is -153.

 PURPOSE
  The primary objective of ISRO's Chandrayaan-2 is to demonstrate the ability 
  to soft-land on the lunar surface and operate a robotic rover on the surface. 
  Scientific goals include studies of lunar topography, mineralogy, elemental 
  abundance, the lunar exosphere, and signatures of hydroxyl and water ice.

 BACKGROUND
  Chandrayaan-2 launched 2019-July-22 @ 09:13 UTC from Satish Dhawan Space 
  Centre on Sriharikota Island, India. Launch vehicle was a GSLV-MK3.

  Mission consists of an orbiter, a lander ("Vikram") and a rover ("Pragyan")

  After launch into Earth parking orbit (170 x 40400 km altitude), a series
  of maneuvers will progressively raise the apogee of the spacecraft until 
  a subsequent trans-lunar injection burn. Injection to lunar transfer orbit
  will occur 2019-Aug-14.
 
  It was inserted into an initial elliptic lunar orbit on Aug 20 
  (114 x 18072 km) and the first of a sequence of maneuvers executed,
  lowering apoapsis to 4412 km.

  The orbiter was eventually placed in a 119 x 127 km nearly circular polar
  orbit after a series of engine burns.

  The lander subsequently separated on 2019-Sep-02 07:45 UTC and will touch
  down at predetermined site close to the lunar south pole.  

  Touchdown is to occur 2019-Sep-07 on a high plain between two craters, 
  Manzinus C and Simpelius N, about 70 degrees south of the equator.

  [NOTE: landing failed, lander & rover were lost]

  The orbiter mission covers 1 year, in a 100-km circular polar orbit.

  The six-wheeled Pragyan rover, whose name means "wisdom" in Sanskrit, will
  be deployed from a ramp after landing. It is solar-powered and capable of 
  traveling up to 500 meters on the lunar surface at a speed of 1 cm/s. 

  The lander/rover missions are planned for 14-15 days (1 lunar daylight
  interval).

 SPACECRAFT DETAILS
  Launch mass       : 3850 kg
  Lunar orbital mass: 2379 kg (solar arrays ~1000 W
  Lunar lander  mass: 1471 kg (solar arrays ~ 650 W)
  Rover mass        : 27 kg   (solar arrays ~  50 W)

 TRAJECTORY: 
  This is a merge of post-launch trajectory solutions fit to tracking data 
  through 2026-Aug-31, with a prediction thereafter.
 
  Trajectory name                             Start (TDB)        Stop (TDB)
  ----------------------------------------- ----------------- -----------------
  ch2o_spk_190722-[200901_od*]_v*_dsn.V0.*  2019-Jul-22 09:31 2020-Jun-01 09:01
  ISRO_CH2*-OD*                             2020-Jun-01 09:01 2026-Oct-10 17:00
*******************************************************************************

Input ELEV_CUT must be between -90.0 <= e <= 90.0 degrees -- try again