Transonic Stability Test of Variable Drag Ballute

Award Information
Agency:
National Aeronautics and Space Administration
Amount:
$69,962.00
Program:
SBIR
Contract:
NND04AA51C
Solitcitation Year:
2003
Solicitation Number:
N/A
Branch:
N/A
Award Year:
2004
Phase:
Phase I
Agency Tracking Number:
035145
Solicitation Topic Code:
A7.02
Small Business Information
ANDREWS SPACE & TECHNOLOGY
505 Fifth Avenue South, Suite 300, Seattle, WA, 98104-3894
Hubzone Owned:
N
Woman Owned:
Y
Socially and Economically Disadvantaged:
N
Duns:
092968127
Principal Investigator
 Dana Andrews
 Principal Investigator
 (206) 342-9934
 dandrews@andrews-space.com
Business Contact
 Curtis Gifford
Title: Business Official
Phone: (206) 342-9934
Email: cgifford@andrews-space.com
Research Institution
N/A
Abstract
Low cost, reliable atmospheric entry technology is needed to support NASA cargo recovery from the ISS, earth return of small payloads, planetary aerocapture, and planetary probe missions. Fixed aeroshields and winged structures are well proven, but are not appropriate for many missions due to envelope, weight, and cost constraints. Inflatable ballute technology offers a low weight, cost effective alternative. Studies and demonstrations of ballute re-entry technology have focused on fixed drag designs (e.g., Small Payload Re-entry Inflatable Transporter (SPRINT), Inflatable Re-Entry Descent Technology (IRDT)). Fixed drag results in large downrange landing dispersions that cause regulatory and recovery challenges. A variable drag ballute significantly reduces downrange dispersions and allows trajectory tailoring to meet peak heating and deceleration constraints. Andrews Space is pursuing a variable drag ballute system for re-entry of payloads. The aerodynamic and aeroelastic behavior of the ballute during the transonic regime is a key development issue. The complexities of this flight regime warrant an early flight test. The Phase I objectives are to design a ballute transonic flight experiment, design the test unit, and define test requirements and plans. These preparations would lead to the construction and transonic flight testing of the variable drag ballute during Phase II.

* information listed above is at the time of submission.

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