TechEdSat

Technology Education Satellite (TechEdSat) is a successful nano-sat flight series conducted from the NASA Ames Research Center in collaboration with numerous universities (San Jose State University, University of Idaho, University of California, University of Minnesota, and Smith College). While one of the principal aims has been to introduce young professionals and university students to the practical realm of developing space flight hardware, considerable innovations have been introduced. In addition, this evolving flight platform has tested concepts for Low Earth Orbit (LEO) sample return, as well as planetary nano-sat class mission concepts.

TechEdSat-1

Computer-aided design drawing of TechEdSat-1
Names	TES-1
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University · University of Idaho · JAXA · ÅAC Microtec
COSPAR ID	2012-038D (1998-067CQ) [1]
SATCAT no.	38854
Mission duration	213 days (achieved) 100 days (planned)
Spacecraft properties
Spacecraft type	CubeSat
Bus	CubeSat
Launch mass	1.2 kg (2.6 lb)
Dimensions	11.35 cm x 10.0 cm x 10.0 cm (1U)
Power	1.229 watts
Start of mission
Launch date	21 July 2012, 02:06:18 UTC
Rocket	H-IIB F3
Launch site	Tanegashima Space Center, Yoshinobu LC-Y2
Contractor	Mitsubishi Heavy Industries
Deployed from	ISS Kibō Delivered by Kounotori 3
Deployment date	4 October 2012, 15:44:15.297 UTC
End of mission
Decay date	5 May 2013
Orbital parameters
Reference system	Geocentric orbit
Regime	Low Earth orbit
Perigee altitude	402 km (250 mi)
Apogee altitude	422 km (262 mi)
Inclination	51.66°
Period	92.80 minutes

The first TechEdSat (later renamed "TechEdSat-1" or "TES-1")^[2][3] was a 1U-Cubesat designed to evaluate Space Plug-and-play Avionics (SPA) designed in Sweden by ÅAC Microtec. It was also originally intended to perform a communications experiment utilizing the Iridium and Orbcomm satellite phone network,^[4] although this function was disabled before launch.^[5] TechEdSat was deployed into orbit from the International Space Station (ISS) on 4 October 2012. It reentered to atmosphere on 5 May 2013.^[6]

• Quake Global Q1000 Modem (Orbcomm) (deactivated) ^[7]
• Quake Global Q9602 Modem (Iridium) (deactivated)
• Stensat Radio Beacon
• 4 x nanoRTU (ÅAC Microtec)
• Main Power Distribution Board (ÅAC Microtec)
• RTU Lite (ÅAC Microtec)
• 2 meter band Monopole Antenna
• 70 cm band Monopole Antenna
• 1600 MHz Patch Antenna
• Pumpkin, Inc. 1U Skeletonized CubeSat Structure
• Canon BP-930 Lithium-ion battery

• Dimensions: 11.35 cm x 10.0 cm x 10.0 cm
• Mass: 1.2 kg (2.6 lb)
• Power Consumption (Safe Mode): 0.350 W
• Power Consumption (Safe Mode, Stensat Transmitting): 3.400 W
• Power Consumption (Nominal Mode): 3.965 W
• Power Consumption (Q1000 Transmitting): 27.125 W
• Power Consumption (Q9602 Transmitting): 10.490 W
• Power Consumption (Nominal Mode, Stensat Transmitting): 7.015 W
• Solar Array (Average): 1.229 W
• Power Storage: 17 Wh

TechEdSat was launched from pad 2 of the Tanegashima Space Center, Yoshinobu Launch Complex (LC-Y2) on 21 July 2012, at 02:06 UTC,^[8] aboard Kounotori 3 atop an H-IIB launch vehicle. Kounotori 3 carried the satellite, along with the RAIKO, WE WISH, Niwaka, and F-1 spacecraft, to the International Space Station (ISS), from where it was deployed via the JAXA J-SSOD deployer, from the Kibō module on 4 October 2012 at 15:44:15.297 UTC.^[9]

TechEdSat-1 transmitted a heartbeat packet over amateur radio every 4 seconds. These packets are 122 ASCII character AX.25 packets. Amateur band radio frequency is 437.465 MHz.^[10] Two consecutive 12 bit raw Analog-to-digital converter (ADC) data values are parsed into one 3 byte chunk in order to save data space.

TechEdSat-2

Names	TES-2 PhoneSat v2a PhoneSat 2.0 Beta Alexander
Mission type	Technology demonstration
Operator	NASA Ames Research Center
COSPAR ID	2013-016C
SATCAT no.	39144
Mission duration	7 days (planned) 6 days (achieved)
Spacecraft properties
Spacecraft type	CubeSat
Manufacturer	NASA Ames Research Center
Launch mass	0.5 kg (1.1 lb)
Dimensions	10 cm x 10 cm x 10 cm (1U)
Start of mission
Launch date	21 April 2013, 21:00:02.2 UTC[11]
Rocket	Antares 110 A-ONE
Launch site	Wallops Island MARS, LP-0A
Contractor	Orbital Sciences
End of mission
Decay date	27 April 2013
Orbital parameters
Reference system	Geocentric orbit[12]
Regime	Low Earth orbit
Perigee altitude	218 km (135 mi)
Apogee altitude	228 km (142 mi)
Inclination	51.64°
Period	88.95 minutes

An Iridium transceiver flew aboard the PhoneSat v2a CubeSat as the TechEdSat-2 mission, separate from the spacecraft originally planned as TechEdSat-2.^[13]

Alexander, also known as PhoneSat 2.0 Beta or PhoneSat v2a is a technology demonstration satellite operated by NASA's Ames Research Center, which was launched on 21 April 2013. Part of the PhoneSat programme, it was one of the first three PhoneSat spacecraft, and the first Phonesat-2.0 satellite, to be launched. A PhoneSat-2.0 satellite, Alexander, was built to the single-unit (1U) CubeSat specification, and measures 10 cm (3.9 in) in each dimension. The satellite is based around an off-the-shelf Samsung Electronics Nexus S smartphone which serves in place of an onboard computer. The satellite is equipped with a two-way S-band transponder and solar cells for power generation. The spacecraft uses the phone's gyroscopes, along with a GPS receiver, to determine its position and orientation, and a system of reaction wheels and magnetorquer coils for attitude control.^[14]

TechEdSat-3p

Names	TES-3
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University · University of Idaho ·
COSPAR ID	1998-067DD (TECHEDS3P) [1]
SATCAT no.	39415
Mission duration	47 days (achieved)
Spacecraft properties
Spacecraft type	CubeSat
Dimensions	30 cm x 10 cm x 10 cm (3U)
Start of mission
Launch date	3 August 2013, 19:48:46 UTC
Rocket	H-IIB F4
Launch site	Tanegashima Space Center, Yoshinobu LC-Y2
Contractor	Mitsubishi Heavy Industries
Deployment date	20 November 2013, 07:58 UTC
End of mission
Decay date	16 January 2014
Orbital parameters
Reference system	Geocentric orbit
Regime	Low Earth orbit
Perigee altitude	410 km
Apogee altitude	415 km
Inclination	51.65°
Period	92.81 minutes

TechEdSat-3p was the third spacecraft flown in the TechEdSat series. Its dimensions were approximately 30 cm x 10 cm x 10 cm, or three CubeSat units long, making it three times larger than TechEdSat-1. TechEdSat-3p was launched to the International Space Station (ISS) on 3 August 2013 from Tanegashima Space Center, Japan on the Kounotori 4 (HTV-4) International Space Station cargo resupply mission and subsequently deployed into orbit by the JEM-Small Satellite Orbital Deployer (J-SSOD).

TechEdSat-3p was the first satellite of the TechEdSat series to include an exo-brake, a parachute-like drag device to demonstrate passive deorbit capability.^[15] The deployment of an exo-brake increases the surface area of a satellite, increasing its coefficient of drag in the thin upper atmosphere and causing the satellite to deorbit faster than it otherwise would. This technology could be used to more quickly dispose of satellites in Low Earth Orbit that have completed their missions, decreasing the amount of potentially hazardous debris in space. The exo-brake is currently being developed for use as part of the Small Payload Quick Return (SPQR) concept, which would enable science materials to be returned to Earth from the International Space Station whenever is most convenient for scientists rather than just a few times per year aboard a returning cargo resupply vehicle.

According to smallsat logistics company ÅAC Microtech, a main power distribution board designed for TechEdSat-1 was reused on the TechEdSat-3p mission.^[16]

TechEdSat-4

Names	TES-4
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University · University of Idaho
COSPAR ID	1998-067FY
SATCAT no.	40455
Mission duration	263 days
Spacecraft properties
Spacecraft type	CubeSat
Launch mass	3 kg (6.6 lb)
Dimensions	10 cm x 10 cm x 30 cm (3U)
Start of mission
Launch date	13 July 2014, 16:52:14 UTC
Rocket	Antares-120
Launch site	Wallops Island MARS, LP-0A
Contractor	Orbital Sciences Corporation
Deployment date	4 March 2015
End of mission
Decay date	3 April 2015
Orbital parameters
Reference system	Geocentric orbit
Regime	Low Earth orbit
Perigee altitude	393 km (244 miles)
Apogee altitude	402 km (250 miles)
Inclination	51.64°
Period	92.50 minutes

TechEdSat-4 was a 3U CubeSat mission developed, integrated, and tested at NASA Ames Research Center in partnership with student interns from San Jose State University (SJSU) in California and the University of Idaho in Moscow, Idaho. The objective of the TechEdSat-4 mission was to demonstrate new technologies including satellite-to-satellite communications and an upgraded Exo-Brake device to demonstrate a passive deorbiting. TechEdSat-4 was launched as a secondary cargo payload on the Cygnus CRS Orb-2 ISS resupply mission. The launch vehicle was the Orbital Sciences Corporation Antares-120, launching from the Mid-Atlantic Regional Spaceport on Wallops Island, Virginia on 13 July 2014.^[17] TechEdSat-4 was deployed from the International Space Station via the Nanoracks CubeSat Deployer on 4 March 2015.^[18][19]

The satellite decayed from orbit on 3 April 2015.^[20]

TechEdSat-5

Names	TES-5
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University · University of Idaho
COSPAR ID	1998-067LB
SATCAT no.	42066
Mission duration	144 days
Spacecraft properties
Spacecraft type	CubeSat
Launch mass	4 kg (8.8 lb)
Dimensions	10 cm x 10 cm x 35 cm (3.5U)
Start of mission
Launch date	9 December 2016
Rocket	H-IIB F6
Launch site	Tanegashima Space Center, Yoshinobu LC-Y2
Contractor	Mitsubishi Heavy Industries
Deployment date	6 March 2017, 18:20:00 UTC
End of mission
Decay date	29 July 2017
Orbital parameters
Reference system	Geocentric orbit
Regime	Low Earth orbit
Perigee altitude	397 km (247 miles)
Apogee altitude	408 km (254 miles)
Inclination	51.64°
Period	92.61 minutes

TechEdSat-5 was a 4 kg, 3.5U CubeSat that was launched on 9 December 2016 aboard the Kounotori 6 (HTV-6) cargo resupply spacecraft, and was deployed from the International Space Station (ISS) at 18:20 UTC on 6 March 2017.^[21] It was the first satellite in the TechEdSat program to include a modulated Exo-Brake that was could adjust the amount of atmospheric drag on the spacecraft, enabling a targeted re-entry.^[22] The TechEdSat-5 Exo-Brake was cross-shaped, made of mylar, and used a combination of mechanical struts and flexible cords.^[23] Its surface area was approximately 0.35 square metres.^[21] A "Cricket" Wireless Sensor Module (WSM) was included with TechEdSat-5.^[24] The satellite reentered the atmosphere on 29 July 2017 after successfully operating for 144 days.^[23]

TechEdSat-6

Names	TES-6
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University · University of Idaho
COSPAR ID	1998-067NK
SATCAT no.	43026
Mission duration	175 days (achieved)
Spacecraft properties
Spacecraft type	CubeSat
Launch mass	3.6 kg (7.9 lb)
Dimensions	10 cm x 10 cm x 35 cm (3.5U)
Start of mission
Launch date	12 November 2017, 12:19:51 UTC
Rocket	Antares 230
Launch site	Wallops Island MARS, LP-0A
Contractor	Orbital Sciences Corporation
Deployment date	20 November 2017
End of mission
Decay date	14 May 2018
Orbital parameters
Reference system	Geocentric orbit
Regime	Low Earth orbit
Perigee altitude	397 km (247 mi)
Apogee altitude	406 km (252 mi)
Inclination	51.65°
Period	92.59 minutes

TechEdSat-6 was a CubeSat 3.5U that was launched at 12:19:51 UTC on 12 November 2017 aboard the Cygnus CRS-8 cargo resupply mission to the International Space Station (ISS).^[25][26] It was deployed from the Nanoracks CubeSat Deployer on 20 November 2017.^[27] In addition to the primary payload, it contained a CubeSat Identity Tag (CUBIT), a Radio Frequency Identification (RFID) tag developed by DARPA and SRI International to assist in future identification of satellites. It successfully reentered the atmosphere on 14 May 2018.^[28][29]

TechEdSat-7

Names	TES-7
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University
COSPAR ID	2021-002D
SATCAT no.	47312
Mission duration	60 days (planned) 471 days (final)
Spacecraft properties
Spacecraft type	CubeSat
Launch mass	3 kg (6.6 lb)
Dimensions	10 cm x 10 cm x 22 cm (2U)
Start of mission
Launch date	17 January 2021, 19:39:00 UTC
Rocket	LauncherOne
Launch site	Cosmic Girl (Boeing 747), Mojave Air and Space Port, California
Contractor	Virgin Orbit
Deployment date	17 January 2021
End of mission
Decay date	4 May 2022
Orbital parameters
Reference system	Geocentric orbit[12]
Regime	Low Earth orbit
Perigee altitude	485 km (301 mi)
Apogee altitude	513 km (319 mi)
Inclination	60.7°
Period	94.6 minutes

TechEdSat-7 was a 2U CubeSat that was intended to test a High Packing Density Exo-Brake. It was launched on the first successful flight of Virgin Orbit's LauncherOne launch vehicle on 17 January 2021 as part of NASA's ELaNa program. It flew with a CubeSat Identity Tag (CUBIT), a Radio Frequency Identification (RFID) tag developed by DARPA and SRI International to assist in future identification of satellites.^[30] The satellite decayed from orbit on 4 May 2022.^[31]

TechEdSat-8

Names	TES-8 Technical and Educational Satellite-8
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University · University of Idaho
COSPAR ID	1998-067PY
SATCAT no.	44032
Mission duration	501 days (achieved)
Spacecraft properties
Spacecraft type	CubeSat
Launch mass	6 kg (13 lb)
Dimensions	10 cm x 10 cm x 60 cm (6U)
Start of mission
Launch date	5 December 2018, 18:16:00 UTC
Rocket	Falcon 9 Block 5
Launch site	Cape Canaveral, SLC-40
Contractor	SpaceX
Deployment date	31 January 2019, 16:45 UTC
End of mission
Decay date	20 April 2020
Orbital parameters
Reference system	Geocentric orbit
Regime	Low Earth orbit
Perigee altitude	402 km (250 mi)
Apogee altitude	409 km (254 mi)
Inclination	51.64°
Period	92.67 minutes

TechEdSat-8 (Technical and Educational Satellite-8) was CubeSat 6U. It was built as a conjoined project between San Jose State University (SJSU) and the University of Idaho as a collaborative engineering project, with oversight from the NASA Ames Research Center. It was a technology demonstration mission to further develop and demonstrate the Exo-Brake system through, designed for continued operation in high temperature environments, the full recovery of a payload. It featured a semi-autonomous control system to target the entry face point, as well as capabilities to measure a unique ablation device on the forebody. This technology, known as a "Hot Exo-Brake" could enable more precisely-targeted atmospheric reentries. An ablation device was also flying on the spacecraft.

TechEdSat-8 was selected in 2017 by the CubeSat Launch Initiative (CSLI) of the NASA to be launched as part of the ELaNa program. TechEdSat-8 was originally planned to launch with the Cygnus NG-10 (17 November 2018) cargo resupply mission to the International Space Station as part of the ELaNa program, but instead was launched aboard the SpaceX CRS-16 ISS cargo resupply mission at 18:16 UTC on 5 December 2018,^[32] arriving at the International Space Station (ISS) on 8 December 2018.^[33][34]

TechEdSat-8 was deployed into orbit by the Kibō JEM-Small Satellite Orbital Deployer (J-SSOD) at 16:45 UTC on 31 January 2019.^[35]

The satellite established communication with controllers and, as of 20 February 2019, was reportedly performing well in advance of a targeted reentry.^[36] The satellite failed shortly after deployment due to a loss of power from its solar panels, and re-entered in the atmosphere of Earth on 20 April 2020.^[37][38]

TechEdSat-10

Names	TES-10
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University
COSPAR ID	2020-067RQ
SATCAT no.	45917
Mission duration	393 days (final)
Spacecraft properties
Spacecraft type	CubeSat
Launch mass	6 kg (13 lb)
Dimensions	10 cm x 10 cm x 60 cm (6U)
Power	150 watt-hour
Start of mission
Launch date	15 February 2020, 20:21:01 UTC
Rocket	Antares 230+
Launch site	MARS, LP-0A
Contractor	Northrop Grumman
Deployment date	13 July 2020, 16:55:25 UTC
End of mission
Decay date	15 March 2021, 08:37:00 UTC
Orbital parameters
Reference system	Geocentric orbit
Regime	Low Earth orbit
Perigee altitude	413 km (257 mi)
Apogee altitude	419 km (260 mi)
Inclination	51.60°
Period	92.00 minutes

TechEdSat-10 (TES-10) was a 6U (1 x 6U) (previously announced as 3U) CubeSat that was selected in 2018 to launch as part of the ELaNa program.^[39]

On 15 February 2020, TechEdSat-10 was launched to the International Space Station (ISS) aboard the Cygnus NG-13 cargo spacecraft.^[40]

Deployed on 13 July 2020, TechEdSat-10 tested radio communication devices, precision deorbit technologies for National Oceanic and Atmospheric Administration (NOAA) and others, radiation tolerant electronics, and artificial intelligence hardware for future experiments.^[41][37][40]

The mission demonstrated increased storage and power capabilities that could enable future science and exploration using small spacecraft beyond low-Earth orbit. Included on TechEdSat-10 were improvements over previous CubeSat technologies in the areas of communications and radio systems, and new propulsion techniques.^[42]

As the tenth iteration in the Technology Educational Satellite (TES) series, TechEdSat-10 built upon a history of the program's innovative work with early career researchers, students, and volunteers. TechEdSat-10 contained 150 watt-hours of power storage, eight radios, nine processors, and a graphics processing unit. Additionally, the small satellite carried four cameras, including a stereoscopic virtual reality camera experiment.^[42]

Like several TechEdSat missions before it, this mission demonstrated the exo-brake technology in its largest iteration to date. The exo-brake was designed to deploy an umbrella-like "brake" to increase drag and take a small satellite out of orbit. This mission, the exo-brake could be controlled or modulated by commands from the ground in order to target a re-entry point. In the future, this could enable sample return missions from orbit and future planetary missions.^[42]

TechEdSat-11

Names	TES-11
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University
COSPAR ID	2024-125F
SATCAT no.	60208
Spacecraft properties
Spacecraft type	CubeSat
Launch mass	7 kg (15 lb)
Dimensions	(6U)
Start of mission
Launch date	4 July 2024
Rocket	Firefly Alpha
Launch site	Vandenberg AFB, California
Contractor	Firefly Aerospace
Deployment date	4 July 2024, 04:50:01 UTC
End of mission
Decay date	UTC
Orbital parameters
Reference system	Geocentric orbit[12]
Regime	Low Earth orbit
Perigee altitude	490 km (300 mi)
Apogee altitude	525 km (326 mi)
Inclination	97.4°
Period	94.8 minutes

TechEdSat-11 is a 6U CubeSat.

TechEdSat-13

Names	TES-13
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University
COSPAR ID	2022-003B
SATCAT no.	51095
Mission duration	252 days (planned) 912 days (actual)
Spacecraft properties
Spacecraft type	CubeSat
Launch mass	4 kg (8.8 lb)
Dimensions	10 cm x 10 cm x 34 cm (3U)
Start of mission
Launch date	13 January 2022
Rocket	LauncherOne # 4
Launch site	Cosmic Girl (Boeing 747), Mojave Air and Space Port, California
Contractor	Virgin Orbit
Deployment date	13 January 2022, 23:47:00 UTC
End of mission
Decay date	13 July 2024, 19:52:00 UTC
Orbital parameters
Reference system	Geocentric orbit[12]
Regime	Low Earth orbit
Perigee altitude	499 km (310 mi)
Apogee altitude	509 km (316 mi)
Inclination	45.0°
Period	92.6 minutes

TechEdSat-13 is a 3U CubeSat that is intended to test and validate three different technologies, including an Exo-Brake. Along with other cubesats (PAN-A and B, GEARRS-3, SteamSat-2, STORK-3, ADLER-1) it was launched on the third successful flight of Virgin Orbit's LauncherOne launch vehicle on 13 January 2022 as part of the STP-27VP mission ("Above the Clouds"). TechEdSat-13 uses the Loihi neuromorphic chip, representing an artificial intelligence/machine learning (AI/ML) payload application.

TechEdSat-15

Names	TES-15
Mission type	Technology demonstration
Operator	NASA Ames Research Center · San Jose State University
COSPAR ID	2022-122?
SATCAT no.	5395?
Mission duration	4 days (final)
Spacecraft properties
Spacecraft type	CubeSat
Launch mass	4.5 kg (9.9 lb)
Dimensions	10 cm x 10 cm x 34 cm (3U)
Start of mission
Launch date	1 October 2022, 07:01:00 UTC
Rocket	Firefly Alpha
Launch site	Vandenberg AFB, California
Contractor	Firefly Aerospace
Deployment date	1 October 2022
End of mission
Decay date	6 October 2022
Orbital parameters
Reference system	Geocentric orbit[12]
Regime	Low Earth orbit
Perigee altitude	215 km (134 mi)
Apogee altitude	285 km (177 mi)
Inclination	137.0°
Period	89.6 minutes

TechEdSat-15 was a 3U CubeSat. It was launched on 1 October 2022 as a rideshare payload on a Firefly Alpha rocket. Despite it being its first mission reaching Earth orbit, due to a lower-than-intended deployment orbit most of the satellites re-entered before reaching their intended design life.^[43]

TechEdSat-9 and TechEdSat-11 are planned to fly at some point in the future.^[44] TechEdSat-9, like TechEdSat-10, is planned to test radio communication technologies for National Oceanic and Atmospheric Administration (NOAA) and others.^[37]

TechEdSat-12 will test technologies for the tracking and identification of small satellites. It will carry a radio-frequency identification (RFID) tag, a radar reflector, and an L-band antenna. It was selected for launch in February 2020 by NASA's CubeSat Launch Initiative, and will be delivered to orbit on a launch contracted through the ELaNa program.^[45]