Transonic Stability Test of Variable Drag Ballute

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NND05AA05C
Agency Tracking Number: 035145
Amount: $598,822.00
Phase: Phase II
Program: SBIR
Awards Year: 2005
Solitcitation Year: 2003
Solitcitation Topic Code: A7.02
Solitcitation Number: N/A
Small Business Information
Andrews Space & Technology
911 Western Ave, Suite 506, Seattle, WA, 98104-1047
Duns: 092968127
Hubzone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: Y
Principal Investigator
 Dana Andrews
 Principal Investigator
 (206) 438-0630
Business Contact
 Marian Joh
Title: Chief Executive Officer
Phone: (206) 438-0600
Research Institution
Ballutes, or inflatable decelerators, offer significant advantages over rigid shells for aerocapture of planetary spacecraft and for earth reentry of cargo by providing mass savings and simplified packaging features. Traditional ballutes, however, have provided little or no trajectory control. For new platform functionality, high drag must be accompanied by some degree of control; also, incorporating thermal protection into the design provides additional weight savings. Ballutes are typically designed to create a low ballistic coefficient, reducing heating rates. However, a low ballistic coefficient also makes them inherently susceptible to insertion trajectory errors, atmospheric density variations, and winds. The use of a variable drag design allows for in-flight adjustment of ballistic coefficient. This significantly lowers downrange dispersions, resulting in a higher reliability recovery system. The specific innovation proposed is the design of a forward-attached, variable drag ballute for atmospheric entry. To demonstrate dispersion control in a forward-mounted ballute, Andrews proposes two flight tests of a subscale, pressure-supported, symmetric ballute that modulates drag by internal pressure control. The experiments are designed to demonstrate the ability to actively vary drag and prove transonic stability while avoiding an aeroheating environment requiring specialized thermal materials.

* information listed above is at the time of submission.

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