JPSS Spacecraft

Spacecraft Overview

Carrying the same main instruments, the JPSS-1 spacecraft will be very similar to NASA's NPP spacecraft, the precursor to JPSS. Ball Aerospace is designing and building the spacecraft bus, under contract to NASA's Goddard Space Flight Center on behalf of NOAA, and is responsible for integrating the instruments and for performing satellite-level testing and launch support. The JPSS-2 spacecraft will be selected based on a full and open competition in the future.

JPSS-1 and Suomi NPP are both members of the Ball Configurable Platform (BCP) family of spacecraft designed for cost-effective, remote sensing applications. Its proven design accommodates a wide range of payloads. The BCP 2000 was designed to accommodate a wide variety of Earth-observing payloads that require precision pointing control, flexible high-data throughput and downlinks, and controlled re-entry.

JPSS artist rendition
Spacecraft characteristics
Lifetime: 7yr (Spacecraft)
Mass: 2540 kg
Dimensions (in launch configuration): 3.6M x 1.4M
Power: 18539 W (EOL)
X-band and Ka-band 300 Mbps Stored Mission Data (SMD) downlink X-band 15 Mbps High Rate Data (HRD)

The JPSS payload of Scientific Instruments includes:

  • Visible/Infrared Imager/Radiometer Suite (VIIRS)
  • Cross-track Infrared Sounder (CrIS)
  • Advanced Technology Microwave Sounder (ATMS)
  • Ozone Mapping and Profiler Suite –Nadir (OMPS-Nadir)
  • Cloud and Earth Radiant Energy System (CERES)
  • Total Solar Irradiance Sensor (TSIS)

In addition to its scientific instruments, JPSS also integrates sensors from NOAA Climate Sensor Program and data communications packages (DCS and SARSAT).

See Instruments Page for more information.

JPSS visaul timelne from 1995 to 2018
  • NPP Launch-October 2011
  • TSIS-1 Launch-September 2014
  • JPSS-1 Launch-2016
  • JPSS-2 Launch-2018

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