Transonic Stability Test of Variable Drag Ballute

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$598,822.00
Award Year:
2005
Program:
SBIR
Phase:
Phase II
Contract:
NND05AA05C
Award Id:
67345
Agency Tracking Number:
035145
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
505 5th Ave South, Suite 300, Seattle, WA, 98104
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
092968127
Principal Investigator:
Dana Andrews
Principal Investigator
(206) 438-0630
dandrews@andrews-space.com
Business Contact:
Marian Joh
Chief Executive Officer
(206) 438-0600
mjoh@andrews-space.com
Research Institute:
n/a
Abstract
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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