NASA SBIR 2019-II Solicitation

Proposal Summary


PROPOSAL NUMBER:
 19-2- Z8.06-2584
PHASE 1 CONTRACT NUMBER:
 80NSSC19C0248
SUBTOPIC TITLE:
 DragSails for Spacecraft Deorbit
PROPOSAL TITLE:
 Compact, Lightweight Bolt-on Deorbit Device for Spacecraft
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
L'Garde, Inc.
15181 Woodlawn Avenue
Tustin, CA 92780
(714) 259-0771

PRINCIPAL INVESTIGATOR (Name, E-mail, Mail Address, City/State/Zip, Phone)
Arthur Palisoc
art_palisoc@lgarde.com
15181 Woodlawn Avenue
Tustin, CA 92780 - 6487
(714) 259-0771

BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Linden Bolisay
linden_bolisay@lgarde.com
15181 Woodlawn Avenue
Tustin, CA 92780 - 6487
(714) 259-0771

Estimated Technology Readiness Level (TRL) :
Begin: 4
End: 6
Technical Abstract (Limit 2000 characters, approximately 200 words)

Two simple bolt-on de-orbit device configurations developed during Phase I will be carried to the CDR level for Phase II culminating in a ready-to-fly de-orbiter at the end of the project.  The first is a passive de-orbiter suitable for use at altitudes up to 1200 km where no vane sail articulation is needed. For altitudes above 1200 km our analysis showed that in order to decay within the 25-year "requirement" an articulating vane sail type de-orbiter is needed for rough-pointing against solar pressure.  Even if the vane sail of the de-orbiter is mis-pointed by 45 degrees, it will still see about 70 percent solar pressure drag. For these higher altitudes a passively articulating bolt-on de-orbit device based on two-way shape memory alloy is used. The two-way shape memory alloy unfurls to a large area against solar pressure during the sun-side of the orbit when it is warmed, and when its "back is turned against the sun" on its way to the eclipse side of the orbit, it cools down and folds back to a low area device decreasing the solar pressure on it as it exits the sun side.  The de-orbiter area can be tailored such that after it crosses the 1200 km limit on its way down, the active area against the atmosphere is still sufficient for de-orbiting within 25 years.  The SMA based de-orbiter has no need for motors or sources of power and the mass and stowed volume gained can be used for an increase in the amount of material to package making it suitable for both altitude regimes.

Potential NASA Applications (Limit 1500 characters, approximately 150 words)

The potential NASA applications include the use of the Bolt-On De-orbiter to assure that its LEO satellites de-orbit within the 25-year "requirement". The 2-way shape memory based de-orbiter unfurls when warmed and folds when cooled. This means that another potential application of the passively articulating 2-way shape memory de-orbiter is for use as substrates of solar panels that automatically unfurls during the sun-side of orbit to catch sun and folds during eclipse to reduce drag area thereby increasing the satellite lifetime.

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

The 2-way shape memory based de-orbiter unfurls when warmed and folds compactly when cooled. This means that another potential application of the passively articulating 2-way shape memory de-orbiter is for use as substrates of solar panels that automatically unfurls during the sun-side of orbit to catch sun and folds during eclipse to reduce drag area thereby increasing the satellite lifetime.

Duration: 18

Form Generated on 05/04/2020 06:22:37