NASA SBIR 2010 Solicitation

FORM B - PROPOSAL SUMMARY


PROPOSAL NUMBER: 10-1 X9.02-8810
SUBTOPIC TITLE: Advanced Integrated Hypersonic Entry Systems
PROPOSAL TITLE: Petal Brake Hypersonic Entry System

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Andrews Space, Inc.
3415 South 116th Street Suite 123
Tukwila, WA 98168 - 1978
(206) 342-9934

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Jeffrey H Cannon
jcannon@andrews-space.com
3415 South 116th Street Suite 123
Tukwila, WA 98168 - 1978
(206) 438-0609

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

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
Future NASA exploration plans will realize significant performance advantages with aerocapture and aerobraking of large, heavy payloads for Mars, Titan, and the gas giant planets. During a previous NASA LaRC funded High Mass Mars Entry System study, Andrews Space found that while inflatable aerobrake designs potentially offer the lowest-mass solution, they are challenged from the uncertainties of dynamic response of large soft structures at the sizes required, and from the risks associated with cleanly separating the lander/payload from the decelerator. A "Petal Brake" concept was introduced as an integrated hypersonic entry system design that addresses these issues. The design performs hypersonic aerocapture and entry maneuvers as a biconic aeroshell, then deploys to provide higher drag just prior to terminal descent and landing. It covers a wide range of EDL environments, is structurally determinate, with minimal aero-elastic issues, and with positive separation characteristics during jettison. During Phase I of this project, Andrews proposes to further advance the operational Petal Brake concept by designing and evaluating a point-of-departure petal-brake design for Mars entry, defining a potential test program, then generating a detailed subscale petal-brake design suitable for manufacture, wind tunnel testing, and high altitude deployment testing in Phase II.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The petal brake decelerator has primary application to the aerocapture and aerobraking of large payloads into Mars or other planetary atmospheres. This has direct benefit to future planetary exploration missions. A smaller deployable petal brake could be used for recovery of payloads from Earth orbit as well. A petal brake could be used for controlled de-orbit and disposal, recovery of materials testing cargo, to recover biological and high value cargo from low earth orbit free flyers or from the International Space Station. Larger deployable petal brake configurations could also be used to retrofit existing cargo vehicles, such as the Orbital Cygnus, ATV or HTV and enable a recovery capability.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The petal brake decelerator has commercial applicability to the recovery of large and small payloads from suborbital conditions or from Earth orbit to support low cost launch or cargo recovery. One application of this innovation may include recovery of launch stage hardware for reuse. SpaceX is planning on recovering their Falcon 1E and Falcon 9 second stage, and the deployable petal brake could be an enabler given their physical size and configuration. Booster recovery could also be enhanced by deployable interstage drag devices. A small deployable petal brake could be used to recover biological samples, high value cargo, instrumentation, or defense-related payloads from low earth orbit free flyers.

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.)
Aerobraking/Aerocapture
Deployment
Entry, Descent, & Landing (see also Astronautics)
Entry, Descent, & Landing (see also Planetary Navigation, Tracking, & Telemetry)


Form Generated on 09-03-10 12:12