🚀 Apollo Systems Engineering Workbench

Saturn V Delta-V Trade-offs, Subsystem Redundancy Trees & FMEA Anomaly Engine

PRESET BENCHMARKS:

Total Launch Mass 2,970,000 kg

Stage 1 Initial TWR 1.20

Calculated Delta-V 9,220 m/s

Max Q Altitude 13.5 km

Payload to TLI 47,000 kg

FMEA Status NOMINAL

📡 Trajectory Simulation & Thrust Vectoring T+ 00:00:00

⚡ Redundancy & Fault Injector

S-II Center Engine NOMINAL

Fuel Cell Bus B NOMINAL

SM RCS Quad B Leak NOMINAL

Stage 1 Propellant Valve NOMINAL

🎛️ Architecture Trade-off Trade Space

Subsystem Redundancy Channels Dual-Redundant (Channel 2)

Structural Factor of Safety 1.40x

S-IC Stage Propellant Load (% Capacity) 100% (2,160,000 kg)

CSM/LM Payload Dry Mass (kg) 47,000 kg

📊 Multi-Axis Telemetry Analytics

📋 Real-Time FMEA (Failure Mode & Effects Analysis) Propagation Log

FMEA CRITICALITY INDEX: NOMINAL_OPTIMAL PAYLOAD SAFETY MARGIN: +12.4% SYSTEM ARCHITECTURE: DUAL_REDUNDANT

Subsystem Node	Active Fault / Anomaly	Propagated Failure Mode	Automated Compensation / Cross-feed	Mission Criticality