NASA SBIR 2020-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 20-1- H5.02-5721
SUBTOPIC TITLE:
 Hot Structure Technology for Aerospace Vehicles
PROPOSAL TITLE:
 Low Cost Enhanced Conductivity C-C for Reusable Hot Structure and Leading Edge Applications
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Allcomp, Inc.
209 Puente Avenue
City of Industry, CA 91746
(626) 369-1273

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Dr. Alex Shih
E-mail:
alex.shih@allcomp.net
Address:
209 Puente Avenue City of Industry, CA 91746 - 2304
Phone:
(626) 369-1273

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Michael Escalera
E-mail:
michael.escalera@allcomp.net
Address:
209 Puente Avenue City of Industry, CA 91746 - 2304
Phone:
(626) 369-1273
Estimated Technology Readiness Level (TRL) :
Begin: 1
End: 3
Technical Abstract (Limit 2000 characters, approximately 200 words)

Owing to their low density and exceptional ability to maintain strength at extremely high temperatures, advanced carbon-carbons (C-C) composite is the preferred structural material for atmospheric entry applications where the vehicles at hypersonic speed are exposed to extreme temperatures (2000°F to 4000°F) and oxidizing atmospheres.  In addition to structural integrity at temperatures up to 4000°F, the material used for the leading edge also needs good thermal conductivity in order to spread the highly localized heat flux to a larger radiating surface and avoid thermal runaway.

 

Operations using the advanced C-C composites are generally expensive due to high material fabrication costs and oxidation wear-out / single use.  Reusable load-carrying ceramic matrix composites (CMC) have being developed for hot structure applications with some success; however, only C-C composites have shown ability to meet the extreme temperature & heat conduction requirements for leading edge applications.

 

Building on knowledge gained with aircraft break products, a novel C-C composite architecture with readily tunable thermal mechanical properties that employs lower-cost carbon fibers and has a shorter manufacturing lead time is proposed.  Additionally, nano-inhibition is proposed to mitigate the oxidation concerns, hence improved damage tolerance and structure re-usability are expected.

 

In Phase I, Allcomp proposes to focus on the leading edge application requirements and demonstrate (1) manufacturability of a lower cost, shorter lead time C-C architecture, (2) feasibility to modulate thermal mechanical properties with preform stack design and densification process enhancements, and (3) inclusion of selected anti-oxidation technology to improve damage tolerance.  Once proven, this architecture will offer other hot structure applications, such as aero-shell and propulsion components, lower cost options with improved reliability.

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

Hot structures for both vehicle body and propulsion systems

  • Atmospheric entry / re-entry vehicles (aero-shell and leading edge), replacing parasitic thermal protection systems
  • Expendable and re-usable hypersonic vehicles,  (aero-shell and leading edge)
  • Scramjet components, hot gas path
  • Exit cones / nozzle extensions

 

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

Both DoD and Commercial Space / Transportation applications:

  • Leading edges and fins for hypersonic vehicles, 
  • Re-usable load-carrying aero-shell and control surface elements,
  • hot gas ducts for scramjet, hot gas valves, throats, nozzle extensions
Duration: 6

Form Generated on 06/29/2020 21:10:52