Rocket Plumbing and Test Stand
Overview
As Captain of MACH (TMU Liquid Rocketry), I led the design and build of the propulsion ground support equipment (GSE) system. This system provides the critical infrastructure for filling, pressurizing, and controlling the liquid rocket engine during test operations.
System Architecture
Dual Nitrogen Regulator Design
The propulsion system utilizes a dual nitrogen regulator configuration:
- Pneumatics Regulator - Powers all pneumatic valve actuators
- Purge Regulator - Dedicated line for system purging and safety
Instrumentation
Each subsystem is instrumented with dedicated pressure transducers for real-time monitoring:
- Pressure Transmitters: Automation Direct PTD25-10-1000H
- Multiple pressure measurement points throughout the system
- Data logging integration with ground control software
Safety Features
Spring-Biased Valves
All critical valves are spring-biased to fail-safe default positions:
- Loss of pneumatic pressure automatically returns valves to safe state
- Redundant safety interlocks
- Manual override capability for emergency operations
Pneumatic Control Architecture
The system uses pneumatic actuation for:
- Reliable operation - No electrical components in hazardous areas
- Rapid actuation - Fast valve response times for precise control
- Fail-safe design - Predictable behavior during power loss
Fittings and Connections
Industry-standard fittings used throughout:
- Swagelok - High-pressure tube fittings for critical connections
- AN (Army-Navy) - Aerospace-grade fittings for propellant lines
- NPT - National Pipe Thread for utility connections
