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Stpsat 3



General


Designation 39380 / 13064A
Launch date 20 Nov 2013
Country of origin United States
Mission Technology
Perigee/Apogee 500 km
Inclination 40.5°
Period 94.6 min
Launch vehicle Minotaur #15

Owned by the US Air Force. Bus built in 47 days

Carries 5 payloads and a de-orbit module.

sat-index articles


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Technical data



Specifications


Prime contractor Ball Aerospace
Platform BCP-100
Mass at launch  
Dry mass  
Dimension  
Solar array  
Stabilization  
DC power  
Design lifetime  

iMESA-R (Integrated Miniaturized Electrostatic Analyzer Reflight), a U.S. Air Force Academy mission designed to measure plasma densities and energies

J-CORE (Joint Component Research), a space phenomenology mission sponsored by the Air Force Research Laboratory (AFRL) /EO Countermeasures Technology Branch (RYMW) & Army Space and Missile Defense Command (SMDC)

SSU (Strip Sensor Unit), an AFRL Directed Energy (RD) experiment to provide risk reduction through on-orbit testing and operation of a sensor assembly

SWATS (Small Wind and Temperature Spectrometer), a Naval Research Laboratory (NRL) mission to provide in-situ measurements of the neutral and plasma environment to characterise the Earth's ionosphere and thermosphere

TCTE (TSI Calibration Transfer Experiment, also called TIM (Total Irradiance Monitor)), a NASA/NOAA mission to collect high accuracy, high precision measurements of Total Solar Irradiance to monitor changes in solar irradiance incident at the top the Earth's atmosphere with TCTE instrument provided by the Laboratory for Atmospheric and Space Physics

In addition, the spacecraft has new capability, the MMA Design LLC De-Orbit Module used to de-orbit the satellite in less than 25 years.

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