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

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 Revised: Oct 09, 2026  INTEGRAL Spacecraft (gamma-ray observatory)       -198
            http://www.esa.int/export/esaMI/Integral/ESAR0RPV16D_0.html
 
 INTEGRAL (INTErnational Gamma-Ray Astrophysics Laboratory):
  Deployment (Proton)   = Oct 17, 2002    Diameter/length (meters) = 3.7/5 m
 
 ORBITAL DATA:
  Inclination           = 51  degrees     Orbital period           = ~72 hours
  Apogee altitude       = ~ 155000 km     Perigee altitude         = ~9,000 km
 
  The spacecraft will spend most of its time above an altitude of 40,000 km
  (outside Earth's radiation belts), thus minimizing background radiation
  effects. Will study black holes, neutron stars, active galactic nuclei and
  supernovae, providing information on formation of new chemical elements
  and gamma-ray bursts. ESA mission.
 
 WEIGHTS & PROPULSION:
   Launch Mass: 4 tonnes
 
 SPACECRAFT TRAJECTORY
   Launch to 2005-Jan-31 JPL Multi-Mission Navigation Team, merged solutions:
 
   OD0018_021017, OD0020_021019, OD0022_021021, OD0030_021029, OD0035_021108,
   OD0037_021119, OD0040_021129, OD0042_021206, OD0045_021216, OD0047_021222,
   OD0051_030102, OD0053_030108, OD0057_030120, OD0060_030127, OD0062_030207,
   OD0066_030219, OD0068_030228, OD0071_030310, OD0075_030321, OD0079_030402,
   OD0084_030416, OD0089_030502, OD0090_030505, OD0097_030529, OD0105_030624,
   OD0113_030721, OD0122_030817, OD0127_030907, OD0131_030919, OD0134_031001,
   OD0141_031022, OD0148_031117, OD0153_031201, OD0157_031212, OD0163_031230,
   OD0169_040126, OD0179_040222, OD0182_040302, OD0184_040309, OD0192_040401,
   OD0202_040428, OD0209_040521, OD0212_040530, OD0219_040620, OD0227_040714,
   OD0236_040810, OD0240_040822, OD0246_040906, OD0251_040927, OD0256_041015,
   OD0260_041101, OD0267_041123, OD0277_041215, OD0285_050101.
 
   2005-Jan-31 to 2015-Jan-01: JSpOC TLEs
   2015-Jan-01 to 2015-Dec-02: ESA-provided ephemeris
   2015-Dec-02 to PRESENT    : JSpOC TLEs
 
   NOTE:
    The ESA ephemeris is used for much of 2015 since TLE's issued by JSpOC were
    based on an obsolete predictive ephemeris for the spacecraft that did not
    reflect January 2015 maneuvering of INTEGRAL to a different orbit.
    http://sci.esa.int/integral/55345-integral-manoeuvres-for-the-future/
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Input ELEV_CUT must be between -90.0 <= e <= 90.0 degrees -- try again