Phoenix 1

Phoenix 1 (launch configuration) [ATMOS]

Phoenix 1 (inflated) [Atmos]

Phoenix 1 is a technology demonstrator capsule developed by ATMOS Space Cargo GmbH to gather data on atmospheric reentry of an inflatable heatshield and validate systems for the operational PHOENIX capsules.

The PHOENIX capsule is designed to achieve an industry-leading downmass efficiency ratio of 1:2, setting a new benchmark for recovery missions. Central to PHOENIX’s design is a novel inflatable heat shield system, developed by ATMOS, which enables efficient and reliable atmospheric re-entry.

The mission objectives for the first test flight are:

• Collect in-flight data from the capsule and its sub-systems while in orbit.
• Gather scientific data from customer payloads operating in Low Earth Orbit (LEO).
• Record data on the deployment and stabilization performance of the inflatable heat shield during re-entry into Earth’s atmosphere.

The maiden test flight of PHOENIX will carry four payloads, featuring a combination of biological experiments and technological demonstrations in microgravity conditions:

• DLR (Germany) – German Aerospace Center, Institute of Aerospace Medicine: Developing radiation detectors for future space missions. Their M-42 radiation detector will measure the radiation environment during the orbital phase.
• IDDK (Japan) – Specializing in space laboratories for biological and life science experiments, IDDK will employ its patented Micro Imaging Device (MID) technology for microscopic observations in space.
• FRONTIER SPACE (United Kingdom) – Working on a modular and scalable ‘lab-in-a-box’ SpaceLab and bioreactor aimed at advancing in-space manufacturing capabilities for the commercial microgravity sector.
• Undisclosed Payload

The mission will be launched on the Bandwagon-3 rideshare mission with SpaceX in April 2025.

The capsule will complete two orbits around Earth before attempting its atmospheric re-entry. Phoenix 1 , unlike planned subsequent missions, has not yet a propulsion system and is deorbited together with stage 2 of the launch vehicle. It is only seperated after the de-orbit burn has occured.