Stpsat 3

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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.

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End of life

Decay

11 Mar 2023

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Technical data

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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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