Re-Entery Heating

AERODYNAMIC THERMAL PROFILE

SPACECRAFT GEOMETRY PRESET

ENTRY VELOCITY (v IN M/S)

LOCAL AIR DENSITY ( IN KG/M³)

NOSE CONE RADIUS (r IN METERS)

THERMAL PROTECTION FLUX RATIO 0%

IONIZATION FEED

THERMAL RE-ENTRY

ESTIMATED THERMAL RADIAL FLUX (q)

0.00

KILOWATTS PER SQUARE METER (kW/m2)

THERMAL INFRASTRUCTURE MATRIX:

INITIALIZING ENTROPY MATRIX...

NEW HORIZONS MISSION CONTROL • THERMODYNAMIC SIMULATION COMPUTATION 2026

Re-entry Heating

The Kinetic Brake. To land, a rocket must "dump" its orbital energy. The atmosphere acts as a giant brake, but that energy has to go somewhere. It turns into a shield of 3,000°C plasma that envelopes the craft.

🔥 Stagnation Point: Where air is compressed to its peak heat.
🔥 Ablation: Some shields melt away to carry heat away from the ship.
🔥 Blackout: Ionized gas blocks all communication for ~7 minutes.

THERMAL INTERFACE

1,650°C

IONIZATION DETECTED

ENTRY INTERFACE

Shield Materials

The Thermal Barrier. Whether through the sacrifice of an ablative resin or the extreme insulation of a ceramic tile, these materials prevent the spacecraft's aluminum or steel skin from melting.

▦ Thermal Conductivity: Near zero (Stops heat transfer).
▦ Porosity: Often 90% air to minimize weight and heat path.
▦ Survival: Rated for 3,000°F+ (1,650°C+).

Material Analysis

PICA-X

LOW THERMAL DIFFUSIVITY

READY FOR RE-ENTRY

Thermal Sync

Kinetic Mapping. Analyzing the conversion of orbital velocity into thermal energy during atmospheric compression.

☄️ Plasma: Ionization Layer Tracking.
🌡️ Flux: Stagnation Point Heat Load.
📉 Dissipation: Radiative Cooling Buffer.

KINETIC THERMAL SYNC

☄️

MAX Q

1650°C

THERMAL LIMIT SECURE

VELOCITY RATIO NOMINAL

Entry Angle (gamma)

The Precision Window. The entry angle dictates the "Density Profile" the rocket encounters. Engineers must balance the risk of Skip-out (too shallow) against the risk of Thermal Destruction (too steep).

∠ Steep Entry: High Peak Heat, High G-Loads.
∠ Shallow Entry: Lower Heat, Risk of Atmospheric Skipping.
∠ Control: Capsules use an offset center of mass to "fly" through the air.

ATTITUDE REFERENCE

-6.2°

OPTIMAL ENTRY VECTOR

CORRIDOR CAPTURE: NOMINAL

Guidance Failure

When the math fails, Aerodynamics takes over. A deviation of just 1 degree can shift the peak thermal load by thousands of Kilowatts. In these scenarios, the spacecraft either becomes a permanent satellite or a falling star.