6,000 lbf Transpiration Cooled Chamber
Goals:
Demonstrate transpiration cooled combustion chamber using
subcritical methane coolant- Scope: Design, fabricate, and test thruster in 18 months
- Results: Combustion chamber delivered with 26 hot fire tests for a total duration of 123 seconds with no degradation to the hardware
- Customer: NASA/MSFC
- Applications: Validation of transpiration cooled hardware for rocket engine applications in high pressure boosters, space engines, and thrusters
