NASA SBIR 2019-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 19-1- H5.01-4299
SUBTOPIC TITLE:
 Lunar Surface Solar Array Structures
PROPOSAL TITLE:
 Deployable and Retractable Solar Array for Lunar Surface/Lander Mobility Operations
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Deployable Space Systems, Inc.
153 Castilian Drive
Goleta, CA 93117- 3025
(805) 722-8090

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Steve White
E-mail:
Steve.White@DSS-Space.com
Address:
153 Castilian Drive Goleta, CA 93117 - 3025
Phone:
(805) 722-8090

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Brian Spence
E-mail:
brian.spence@dss-space.com
Address:
460 Ward Drive, Suite F Santa Barbara, 93111 - 2356
Phone:
(805) 722-8090
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Deployable Space Systems, Inc. (DSS) has developed a next-generation high performance solar array system specifically for NASA’s future Lunar Lander and sample return missions.  The proposed Lander solar array has game-changing performance metrics in terms of extremely high specific power, ultra-compact stowage volume, affordability, low risk, high environmental survivability/operability, high power and growth capability, high deployed strength and high strength during deployment (for mission environments that have high gravity and wind loading from atmospheres as examples), high deployed stiffness, high reliability, retraction and re-deployment capability, and broad modularity / adaptability to many missions.  Most importantly, the proposed innovation has a demonstrated in-space capability to provide multiple and reliable deployments, retractions, and re-deployment operations allowing for continuous mobility operations and shuttling.  No other solar array has demonstrated the ability to deploy, retract and re-deploy multiple times in space or through ground testing.  The proposed technology innovation significantly enhances Lander and sample return vehicle capabilities by providing a low cost alternative renewable power generating system in place of the standard RTG systems currently being used.  The proposed innovation greatly increases performance and autonomy/mobility, decreases risk, and ultimately enables missions. 

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

Applications comprise practically all Exploration, Space Science, Earth Science, Planetary Surface, and other missions that require affordable high-efficiency PV power through of an ultra-lightweight, compact stowage, high strength / stiffness, and highly-modular solar array.  The technology is particularly suited for Lander missions that require game-changing performance in terms of affordability, high performance, unsupported deployment in a gravity field, and deployment / retraction / re-deployment capability. 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

Non-NASA applications comprise missions that require affordable high-efficiency PV power through of an ultra-lightweight, compact stowage, high strength / stiffness, and highly-modular solar array.  The technology is particularly suited for missions requiring game-changing performance in terms of low cost, high performance, and deployment / retraction / re-deployment capability for resiliency. 

Duration: 6

Form Generated on 06/16/2019 23:15:12