Nyx Mission Possible (original) (raw)

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Nyx Mission Possible [The Exploration Company]

Nyx Mission Possible is a subscale demonstration mission conducted by The Exploration Company, designed to validate key technologies for their future reusable cargo capsule, Nyx. This test article is approximately 2.5 meters in diameter, with a mass of 1.6 tonnes, and carries around 300 kg of customer payloads. The mission aims to demonstrate end-to-end capability of capsule recovery, including orbital operation, atmospheric re-entry, and splashdown.

The capsule will be launched aboard SpaceX�s Transporter-14 rideshare mission and will orbit Earth for approximately three hours before before deorbit (by the upper stage), re-entry, and splashdown.

Mission possible has following objectives:

• Demonstrate clean mechanical separation from launch vehicle
• Validate in-space attitude control and orientation systems
• Verify re-entry trajectory and heatshield integrity
• Test full parachute deployment sequence
• Ensure survivability and buoyancy post-splashdown
• Recover capsule and assess onboard data

The mission has five phases:

1. Separation from Launcher
   The mission begins with clean separation from the Falcon-9 upper stage after the deorbit burn, managed in coordination with SpaceX. While mechanically simple, this operation is critical to ensure nominal deployment, particularly in a rideshare environment where multiple payloads deploy in sequence. Attitude control immediately post-separation ensures a stable initial state for the capsule.
2. Detumbling and Heatshield Orientation
   Following separation, the capsule performs detumbling maneuvers and orients itself heatshield-first in preparation for re-entry. This phase tests the capsule�s guidance, navigation, and control (GNC) system, using onboard inertial measurement units (IMUs). Accurate attitude control is essential: incorrect orientation can lead to unstable re-entry or thermal failure.
3. Atmospheric Re-entry
   This is the mission�s core demonstration objective. The capsule�s thermal protection system (TPS), consisting of bonded thermal tiles, will be tested under real flight conditions. The capsule�s aerothermal behavior has been previously modeled and validated through wind tunnel and plasma arc jet testing, but this flight provides the first opportunity to compare those results against actual atmospheric re-entry dynamics. Key parameters include re-entry angle, deceleration profile, and heat flux endured by the TPS.
4. Parachute Deployment and Controlled Descent
   As the capsule descends through the atmosphere and slows to Mach 0.8�0.6, the parachute system is triggered. This system includes a drogue chute for initial stabilization, followed by a main parachute to reduce descent speed to target splashdown velocity. The system features redundant logic and flight-proven components, ensuring high reliability.
5. Splashdown and Recovery
   Final descent results in splashdown at approximately 28 km/h. The capsule is designed to remain buoyant and stable in open water. Redundant recovery beacons and onboard telemetry systems assist with localization and post-flight diagnostics. Recovery operations will commence within a 3-day window, with the recovery vessel standing by outside the splash zone safety perimeter.

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