NASA SBIR 2018-II Solicitation

Proposal Summary

 18-2- Z11.01-1793
 NDE Sensors
 Textile Strain Measurement System
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Katabasis Engineering, LLC
708 Goodale Hill Road
Glastonbury, CT 06033
(860) 690-2243

PRINCIPAL INVESTIGATOR (Name, E-mail, Mail Address, City/State/Zip, Phone)
Allen Witkowski
708 Goodale Hill Road
Glastonbury, CT 06033 - 4042
(860) 690-2243

BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Allen Witkowski
708 Goodale Hill Road
Glastonbury, CT 06033 - 4042
(860) 690-2243

Estimated Technology Readiness Level (TRL) :
Begin: 3
End: 5
Technical Abstract (Limit 2000 characters, approximately 200 words)

The use of textile devices for spacecraft structures and deceleration provides significant stowed versus deployed volume and mass advantages. However, the long-standing problem with textile devices is the fact that measurement of physical and functional properties, especially during deployment and dynamic events, has been incredibly difficult if not impossible. Generally speaking, the sensors used to measure the textile behaviors have been of sufficient mass/stiffness/wiring/etc. as to alter the base behavior of the material being measured. Current evaluations of stress in textile structures such as parachutes, parafoils, inflatable shelters, etc. rely heavily on analytical estimation and empirical “go/no go” test results without adequate means of data collection to validate or improve simulations.

The current concept for this proposal, hereinafter referred to as the Textile Strain Measurement System or TSMS, includes design of a direct measurement data recorder, with size and mass goals that do not influence the textile structure's natural movement and dynamic characteristics. Additionally, the proposed effort includes investigation and characterization of various strain sensitive materials suitable for non-invasive application to previously constructed textile assemblies, with initial focus on Aerodynamic Decelerator Systems (ADS), to allow dynamic stress measurement of flexible structures. Phase I resulted in the planned technology at TRL 3 and delivered a lab prototype of the data recorder with test samples of sensor-infused parachute material.  Phase II, when selected, would progress TSMS to at least TRL 5 including fully functional hardware examples for use on free-flying inspection platforms during parachute operation including deployment and inflation.  It is our intention to add an accelerometer as an additional sensor during Phase II.

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

NASA JPL efforts associated with Mars 2020/ASPIRE and Fluid Structure Interaction (FSI) parachute modeling, NASA-wide efforts associated with balloon/inflatable development for Venus, starshade sunshields, deployable antennas, deployable solar arrays,deployable solar sails, NASA JSC efforts to characterize inflatable human habitats, Orion CPAS and commercial capsule recovery systems, NASA ARC/LaRC efforts to advance ADEPT and HIAD flexible heatshields.

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

US Army efforts to characterize and improve soldier parafoil and ballistic deceleration systems, government-wide efforts to develop and characterize inflatable shelters and emergency facilities, and government-wide efforts to develop small satellite and sample return decelerator systems.

Duration: 24

Form Generated on 05/13/2019 13:34:03