Spacecraft Reentry Optimization
NGSS Alignment
Design a solution to a complex real-world problem by breaking it down into smaller, more manageable problems.
Use a computer simulation to model the impact of proposed solutions to a complex real-world problem with numerous criteria and constraints on interactions within and between systems relevant to the problem.
Phenomenon & Task
Returning a spacecraft to Earth is one of the most difficult engineering challenges. As a spacecraft hits the atmosphere at orbital velocities, immense kinetic energy is converted into heat, creating a superheated plasma. Concurrently, the spacecraft experiences massive deceleration (G-forces). If the heat shield fails, the spacecraft burns up. If the deceleration is too severe, the crew or sensitive payload will not survive. How can you design a reentry vehicle by optimizing mass, heat shield size, entry angle, and material to ensure survival within constraints?
Mission Briefing
Target Safety Limits for payload survival:
- • Max G-force: ≤ 15.0 G
- • Max Temp: ≤ 2000 °C
Vehicle Parameters
Steeper angles = deeper atmosphere faster.
Telemetry & Visualization
Peak Temp
--- °C
Limit: 2500°C
Max G-Force
--- G
Limit: 8.0 G
Trial Data
| Tr# | Mass | Diam | Ang | Temp | G's | Res |
|---|