STPSat 2, 3 (original) (raw)
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STPSat 2 [Ball]
STPSat 3 [Ball]
STPSat 2 is an experimental spacecraft for STP (Space Test Program). It was the first flight of the Standard Interface Vehicle (STP-SIV).
STPSat-2 carried three experimental payloads that were chosen by the DoD Space Experiment Review Board:
- SPEX (Space Phenomenology Experiment) consisting of two payloads to evaluate sensor compatibility for the space environment
- ODTML (Ocean Data Telemetry MicroSatLink) provides two way data relay from terrestrial (ocean or land) sensors to users (standalone or on the internet).
STPSat 3 is a copy of the STPSat-2 satellite, which carried five experiments, including a module designed to host various space situational awareness sensors and a pair of space environment sensors.
- 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 characterize the Earth�s ionosphere and thermosphere
- TCTE (TSI Calibration Transfer Experiment), 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, originally built as a flight-spare instrument for SORCE.
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.
| Nation: | USA |
|---|---|
| Type / Application: | Technology |
| Operator: | US Air Force (USAF) STP (Space Test Program) |
| Contractors: | Ball Aerospace (prime); AeroAstro (bus) |
| Equipment: | 2 SPEX, ODTML (#2); iMESA-R, J-CORE, SSU, SWATS, TCTE, De-Orbit Module (#3) |
| Configuration: | Astro-200 |
| Propulsion: | |
| Power: | 3 deployable solar arrays, batteries |
| Lifetime: | 1 year |
| Mass: | 180 kg |
| Orbit: | 641 km × 652 km, 72� |
| Satellite | COSPAR | Date | LS | Launch Vehicle | Remarks |
|---|---|---|---|---|---|
| STPSat 2 (USA 217) | 2010-062A | 20.11.2010 | Kd LP-1 | Minotaur-4 HAPS | with FASTRAC 1, FASTRAC 2, FalconSat 5, FASTSat-HSV 01, RAX 1, O/OREOS, NanoSail-D2, Ballast A, Ballast B |
| STPSat 3 | 2013-064A | 20.11.2013 | WI LA-0B | Minotaur-1 | with ORS 3, ORSES, ORS Tech 1, ORS Tech 2, SENSE 1, SENSE 2, Ho`oponopono 2, Firefly, STARE B, Prometheus 1.1, ..., 1.8, Black Knight 1, NPS-SCAT, COPPER, ChargerSat 1, TJ3Sat, Trailblazer 1, Vermont Lunar Cubesat, SwampSat, CAPE 2, DragonSat 1, KySat 2, PhoneSat v2.4 |