NASA SBIR 2015 Solicitation

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Opto-Knowledge Systems, Inc. (OKSI)
19805 Hamilton Avenue
Torrance, CA 90502 - 1341
(310) 756-0520

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Gordon Scriven
gordon@oksi.com
19805 Hamilton Avenue
Torrance, CA 90502 - 1341
(310) 756-0520 Extension :229

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Nahum Gat
nahum@oksi.com
19805 Hamilton Avenue
Torrance, CA 90502 - 1341
(310) 756-0520 Extension :237

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

Technology Available (TAV) Subtopics
Ablative Thermal Protection Systems Technologies, Sensors and NDE Methods is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
OKSI proposes a minimally invasive in-flight diagnostic to measure heat shield recession during flight tests. These measurements can be used to validate models and ultimately optimize heat shield design to reduce weight while maintaining sufficient safety margins. The concept has two components: 1) specially designed heat shield plugs and 2) a remote spectral sensor.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
NASA is in the process of improving heat shield design either through the use of new heat shield materials or by reducing the thickness of existing heat shields using conventional materials. Currently, NASA heat shield predictive models are not reliably consistent with observed measurements. The proposed concept will provide time-resolved recession measurements that can be used for model validation (both during arc jet test and flight tests). With validated predictive models, NASA can optimize the heat shield design for expected reentry conditions.
Additionally, reliable onboard real-time recession measurements could possibly be used to identify localized excessive recession. This diagnostic could be integrated with capsule flight control system to orient the vehicle to reduce heating loads in damaged areas. Furthermore, this technology could be used to monitor Mars entry events whose heat shields cannot be physically inspected post-entry.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Commercial and DoD applications also exist. For instance, SpaceX (Dragon), Blue Origin (New Shepard), and Boeing (CST-100) are pursuing capsule reentry capabilities. DoD is developing hypersonic cruise vehicles in support of Conventional Prompt Global Strike. These test vehicles undergo very high heating rates which stresses the Thermal Protective System (TPS) design. Non-invasive recession measurements are needed to support development of an optimal TPS.