NASA SBIR 2018-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 18-1- Z7.03-1414
SUBTOPIC TITLE:
 Deployable Aerodynamic Decelerator Technology
PROPOSAL TITLE:
 Mars Entry and Earth Rrturn Re-Entry Drag Brake Decelerators
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Blazetech Corporation
29 B Montvale Avenue
Woburn , MA 01801-7021
(617) 661-0700

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Hartmut Legner
hlegner@blazetech.com
29 B Montvale Avenue Woburn, MA 01801 - 7021
(781) 759-0700

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)
N. Albert Moussa
amoussa@blazetech.com
29 B Montvale Avenue Woburn, MA 01801 - 7021
(781) 759-0700
Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 4
Technical Abstract

Blazetech Corporation is pleased to submit this Small Business Innovation Research (SBIR) proposal to the National Aeronautics and Space Administration (NASA) to develop an innovative decelerator concept with application to Mars Entry and Earth Return Entry (Earth-Mars Decelerator). The Earth-Mars Decelerator has its foundation with the Drag Brake concept as an alternative approach to safely returning astronauts from orbit.  There are three important innovative features of the Drag Brake that distinguish its benefits.  First, the use of a large umbrella-like shape forces vehicle slowdown at the higher atmospheric altitudes essentially reducing the heating rate so much that it eliminates the need for a heavy thermal protection system.  Second, the ability to modulate the lift and drag behavior by reorienting the drag brake at the lower altitudes permits more precise landing locations and slower landing speeds.  Third, carbon-based material choices and structural designs (as opposed to stainless steel materials) provide lighter and stronger decelerators with appropriate surface emissivity and anti-oxidative coatingsIn addition to these three features, the new Drag Brake concept also has the following additional beneficial characteristics. Flexible Decelerator has never demonstrated in re-entry flight.  This is a unique program goal.  Blunt shape aerodynamically stable through entire re-entry flight regime. The technical approach accommodates secondary deceleration (inflatables, parachutes), if necessary. 

Potential NASA Applications

*Decelerator for Mars entry

*Decelerator for Earth return re-entry

*Earth re-entry decelerators from moon orbital and landing missions

*Mars gentle entry decelerators of sensors, probe vehicles and personnel

*Venus entry decelerators

Potential Non-NASA Applications

*Safety “lifeboat” decelerator from the International Space Station (ISS)

*Rescue decelerators for recreational space flight missions 

*Decelerators placing sensors in remote earth locations

*Decelerators delivering foldable, erectable unmanned aircraft safely to low altitudes from low Earth orbit (LEO)

*Decelerators delivering personnel worldwide in two hours from LEO

 


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