NASA STTR 2018-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 18-1- T13.01-1183
SUBTOPIC TITLE:
 Intelligent Sensor Systems
PROPOSAL TITLE:
 Wireless Passive Nanoparticle based Intelligent Sensor System for Extreme Environments
SMALL BUSINESS CONCERN (SBC):
RESEARCH INSTITUTION (RI):
Name:   Sensatek Propulsion Technology, Inc
Name:   Florida State University
Street:  1736 W. Paul Dirac Drive, Suite 113
Street:  874 Traditions Way, Third Floor
City:   Tallahasee
City:   Tallahassee
State/Zip:  FL  32310-3747
State/Zip:   FL 32306 - 4166
Phone:  (850) 321-5993
Phone:   (850) 410-6141


Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Reamonn Soto
rsoto@sensatek.com
1736 W. Paul Dirac Drive, Suite 113 Tallahasee, FL 32310 - 3747
(850) 321-5993

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mrs. Azryana Soto
c.azryana@gmail.com
1736 W. Paul Dirac Drive, Suite 113 Tallahasee, FL 32310 - 3747
(850) 348-0687
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 3
Technical Abstract

Sensatek Propulsion Technology, Inc. proposes to demonstrate the feasibility of a wireless, passive, nanoparticle-based sensor system. The sensor in its current form can be used to measure real time temperatures and pressures wirelessly without the need of an external energy source. It should be noted that the same sensing principle can be used for strain monitoring as well. It comprises of a microwave-resonator-based sensor, a microwave transceiver, and a custom-made antenna. The microwave-resonator-based sensors uses a dielectric resonator structure, a low-profile reflective patch temperature sensor, and a pressure sensor based on evanescent-mode resonator structure. These sensors are made of high-temperature-stable and corrosion-resistant ceramic materials which are suitable for extreme-environment applications. The use of nanoparticles can further reduce the size of the sensor enabling deployment in current hard-to-access areas.

This approach will enable not only surface measurements of pressure and temperature but also provide in-flow measurements of gas path flows at cryogenic and high temperature environments. In-flow measurements within the metal piping of the fluid systems helps provide a dynamic and real time analysis of the operations of the system. Besides, the embedded sensor helps in keeping the structural integrity of the component intact since it’s installation doesn’t require machining pathways as is needed for traditional sensor cables.

The proposed innovation will specifically provide the following benefits for propulsion system test, development & flight applications:

Potential NASA Applications

-Reduced cost and labor requirements associated with instrumentation installation at 8-Foot High-Temperature Tunnel Facility for National Aerospace Plan Concept Demonstration Engine, X43 Hyper-X engine

-Reduce operational costs for various engine test-beds, developmental & launch facilities at SSC, GRC, MSFC and KSC Propulsion Systems Laboratory

-Structural health monitoring into the numerous NASA programs particularly the RS-25 engines on SLS.

Potential Non-NASA Applications

Monitoring of harsh environments in inaccessible locations provides insight to increase the reliability and efficenciy in systems that includes: HyFly Dual Combustor Ramjet Engine, X43C program’s Ground Demonstrator, Air Force Research Laboratory’s SJX61–1 and SJX61–2 engines; Power Generation & Aviation Gas Turbine Engines for Maintenance & Operational Monitoring; Automotive for Continuous Monitoring for Component Health Indication; and Chemical Plants for Process Control, Safety & Automation.


Form Generated on 05/25/2018 11:56:36