Petal Brake Hypersonic Entry System

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,867.00
Award Year:
2011
Program:
SBIR
Phase:
Phase I
Contract:
NNX11CD56P
Award Id:
n/a
Agency Tracking Number:
105190
Solicitation Year:
2010
Solicitation Topic Code:
X9.02
Solicitation Number:
n/a
Small Business Information
3415 South 116th Street, Suite 123, Tukwila, WA, 98168-1978
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
Y
Duns:
092968127
Principal Investigator:
Jeffrey Cannon
Principal Investigator
(206) 438-0609
jcannon@andrews-space.com
Business Contact:
Denise Masters
Business Official
(206) 438-0607
dmasters@andrews-space.com
Research Institute:
n/a
Abstract
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.

* information listed above is at the time of submission.

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