ROCKET NOZZLES
In addition to transitioning away from toxic propulsion technologies in launch systems, we believe that work towards low cost space access should also include strategic near-term technology investments in optimized nozzle design.
[1] Lamont, E.A. The Aerospike Engine System for the Space Tug –
A Status Report. AIAA-73-1245, (1973).
[2]. Besnard, E., & G. Garvey, G., Aerospike Engines for
Nanosat and Small Launch Vehicles, AIAA-2004-6005. (2004)
- Near the completion of the Apollo program, the U.S. was already actively investigating similar enhancements in expanded space exploration capability
- In the field of propulsion, the aerospike vacuum engine nozzles were one of these enhancements that included 100’s hours of hot-fire tests before the Apollo era ended.
- 20%-30% of nominal engine size for ready scaling up to longer-stay lunar vehicles.
- Aerospike programs dwindled despite significant improvements over conventional bell nozzles after RL10 development was selected for flight development.
- We have opportunity to look at significantly reduced scale engines but optimized for new monopropellant architecture.
- 20%-30% of nominal engine size for ready scaling up to longer-stay lunar vehicles.