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Case Study

LACO Supports NASA’s OSIRIS-REx Mission

Thermal vacuum testing for a mission to asteroid Bennu

Before spacecraft instruments can be trusted to perform millions of miles from Earth, they must be tested in an environment that closely replicates the conditions of space. LACO provided a thermal vacuum system for Arizona State University to validate the OSIRIS-REx Thermal Emission Spectrometer (OTES), an instrument designed to help scientists study asteroid Bennu and support NASA’s sample return mission.

The Challenge

NASA’s OSIRIS-REx mission was developed to travel to the asteroid Bennu, collect a sample, and return it to Earth for scientific analysis. One of the mission’s key instruments was the OSIRIS-REx Thermal Emission Spectrometer (OTES), developed by Arizona State University to measure the mineral composition and temperature distribution of the asteroid’s surface.

Before launch, the instrument needed to undergo rigorous environmental testing to verify its performance under the extreme conditions it would experience during the mission. NASA’s testing requirements demanded a thermal vacuum environment capable of accurately simulating both the vacuum of space and the severe temperatures encountered during flight.

Key project requirements included:

  • Simulating the vacuum conditions of deep space
  • Replicating extreme spacecraft operating temperatures
  • Supporting testing of sensitive scientific instruments
  • Providing a stable platform for instrument mounting
  • Enabling both automated and manual system operation
  • Meeting NASA’s stringent environmental testing requirements

Our Solution

LACO designed and built a Frontier thermal vacuum chamber for Arizona State University specifically to support testing of the OTES instrument. The system featured a 60″ diameter by 96″ deep chamber with a vibration-isolated platen and drilled mounting locations for secure instrument installation. Internal thermal shrouds cooled with liquid nitrogen allowed the system to recreate the cold temperatures experienced in space.

A cryogenic vacuum pump provided the high-vacuum environment required for testing, while the integrated control system supported both automatic and manual operation. Together, these capabilities enabled ASU to subject OTES to mission-like conditions prior to launch, helping validate instrument performance before deployment aboard the OSIRIS-REx spacecraft.

The completed system delivered:

  • 60″ diameter x 96″ deep thermal vacuum chamber
  • High-vacuum performance to 5 x 10⁻⁷ Torr
  • Thermal capability down to -192 °C
  • Liquid nitrogen-cooled thermal shrouds
  • Vibration-isolated instrument mounting platen
  • Automatic and manual control modes
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