LOW COST COMBUSTION CHAMBER/NOZZLE

The NASA Marshall Space Flight Center has developed a Fastrac turbopump rocket engine. The Fastrac engine can be built for less than $1 million using commercially available off-the-shelf (COTS) components and simplified manufacturing techniques. Fastrac provides 60,000 pounds of thrust and has many potential launch system applications. The Fastrac engine has been successfully tested.

Benefits - Low Cost of Manufacture

Reduced complexity of engine design
- Simple cycle: liquid oxygen rocket propellant, gas generator
- Simple control system: open loop sequencer
- Simplified geometry: easy to machine
- Fewer parts than previous American-made rockets.
Use of commercially available off-the-shelf components technology
Use of low-cost, high-performance materials

Potential Commercial Uses

Fastrac engine could provide an alternative launch vehicle
Fastrac engine may provide a less expensive launch platform
The Fastrac engine can be used as a reusable launch vehicle thrust system for lower weight launches
Further developments will enable Fastrac to be used as an upper stage engine or scaled to accommodate larger size payloads

Commercial Opportunities with NASA

Patent applications have been filed for three elements of the engine technology: (1) the rocket nozzle and combustion chamber structure, (2) the fuel injector, and (3) the combination of the combustion chamber/nozzle with the injector to form the thrust chamber assembly. Commercial opportunities exist through licensing and cooperative development opportunities with NASA.

Combustion Chamber

The combustion chamber features an ablative cooling layer that decomposes as it absorbs the heat of combustion. The chamber is integrated with the main nozzle assembly into a unitized structure made of state-of-the-art ablative and refractory materials. High-performance silica phenolic tape makes up the ablative liner, which is overwrapped with graphite epoxy to form the complete chamber/nozzle assembly. The ablative behavior of the liner is used to both cool and insulate the metal nozzle shell by resin boil-off and char layer formation. The ablative layer can be replaced after each flight of the engine's expected 7-launch life.

Patent Number

Contact for Licensing Information

If your company is interested in commercializing the Fastrac Engine or if you need additional information, please reference case no. MFS-31138 and contact:

Technology Transfer Department
Patent Licensing Information
Mail Code CD30
Marshall Space Flight Center, AL 35812
Email: sammy.nabors@msfc.nasa.gov