NASA SBIR 2011 Solicitation


PROPOSAL NUMBER: 11-1 S5.04-8453
SUBTOPIC TITLE: Spacecraft Technology for Sample Return Missions
PROPOSAL TITLE: A LOX-Cooled, Pump-Fed Rocket Engine for Sample Return Applications

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Ventions, LLC
1142 Howard Street
San Francisco, CA 94103 - 3914
(415) 543-2800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Adam London
1142 Howard Street
San Francisco, CA 94103 - 3914
(202) 213-2846

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 3

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
To-date, the realization of small-scale, high-performance propulsion systems for challenging in-space maneuvers requiring high delta-V and acceleration over a short period of time (i.e. sample return), has largely been limited by the lack of regeneratively-cooled thrust chamber assemblies and turbopumps in the 100-1,000lbf thrust class. Ventions proposes to overcome this limitation by developing a 500lbf, LOX-cooled, pump-fed engine for in-space propulsion applications. The Phase I effort will focus on: 1. Overall design of a 500lbf engine; 2. Detailed design and fabrication of a sub-scale, LOX-cooled main combustion chamber; and 3. Experimental hot-fire testing of a LOX / IPA combustion chamber assembly to evaluate cooling channel performance and LOX quality at the injector inlet.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The propulsion system proposed herein represents a low-cost technology that can be integrated into a number of spacecraft designs with the ultimate goal of providing high-performance liquid bipropellant rocket engines for challenging in-space missions. The use of LOX for regenerative cooling of the main combustion chamber enables propellant combinations, engine cycles and / or operating points not currently available for in-space missions. The availability of on-board pressurization for higher chamber pressure operation (without the excessive weight penalty of propellant storage tanks), can further result in a significant increase in the capability for missions requiring large Delta-V over a short period (such as sample return, powered landings and ascent, orbit insertion and change, etc.), thereby easing implementation of space borne operations through a combination of reduced size, weight, improved reliability and lower cost.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Non-NASA commercial applications include: 1. Upper stage propulsion. 2. Apogee kick motors for small- and medium-scale
spacecraft. 3. Standalone non-aerospace applications of the pump technology in industrial and desalination settings for water and cryogenics, and as an alternative to other high-pressure liquid pumps.

TECHNOLOGY TAXONOMY MAPPING (NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.)
Cryogenic/Fluid Systems
Heat Exchange
Maneuvering/Stationkeeping/Attitude Control Devices

Form Generated on 11-22-11 13:43