Liquid Oxygen (LOX)+Liquid Methane (LNG) fueled rocket engine technology provides the opportunity to reduce the cost of space travel, space science, space exploration, etc.
Besides the cost advantage, other advantages of this technology include reusability, non-toxicity, environmental-friendliness, In-Situ-Resource-Utilization (ISRU), and higher performance.
1. Specification (Prototype)
Length – 6.5 ft.
Weight – 360 lb.
Thrust (vacuum) – 22,000 lb. (10 metric-ton)
ISP (sea) – 277 sec.
ISP (vacuum) – 321 sec.
Nozzle Expansion - 16.5
Turbo machinery – 15 MPa (2,200 psi)
Regenerative Chamber and Nozzle Cooling
Operability on commercial LNG
Simple, robust design
Reusability (estimated at over 10,000sec)
Short purge and rapid turnaround time
Advanced manufacturing techniques and a simple, robust design makes DARMA's LOX+Methane engine the lowest cost alternative in its class
The use of Methane as the propellant avoids the buildup of soot inside the combustion chamber and greatly increases the engine lifespan. DARMA's LOX+Methane engine's lifespan is estimated at about 10,000 seconds.
DARMA's LOX+Methane engine was designed with reliability as the highest priority. Generous design margins have been used throughout. Fuel feed and the combustion process are inherently stable. A rigorous testing process has been applied to the engine design all the way from concept proof to prototype. We have performed over 180 firing tests from 10 seconds to 200 seconds burn time.