NASA SBIR 2015 Solicitation

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Extreme Diagnostics, Inc.
6960 Firerock Court
Boulder, CO 80301 - 3814
(303) 523-8924

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert B Owen
rowen@extremediagnostics.com
6960 Firerock Court
Boulder, CO 80301 - 3814
(303) 523-8924

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert B Owen
rowen@extremediagnostics.com
6960 Firerock Court
Boulder, CO 80301 - 3814
(303) 523-8924

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 6

Technology Available (TAV) Subtopics
Precision Deployable Optical Structures and Metrology 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)
This SBIR project creates a CubeSat-based on-orbit Validation System (CVS) that provides performance and durability data for Macro Fiber Composite (MFC) piezocomposite actuators operating in space and matures this precision deployment technology through validation tests in Low Earth Orbit (LEO). NASA customers include active structures like space-based deployable telescopes. Phases I/II advance MFC actuator materials to TRL 6 or better for space.
Implications of the innovation
While the piezocomposites needed for active control have flown and are space qualified, their performance has not been quantified under minimal thermal protection to enable large deployable precision structures like 10�30 m class space telescopes. Data is needed on the viability of piezocomposites as control actuators for deployables. MFC actuators also enable structural health monitoring (SHM) methods that expand the potential commercial market.
Technical objectives
CVS uses a nanosatellite for LEO tests. Nanosatellites provide low-cost rapid access to space-based testing. CVS leverages our previous NASA research and builds on the Phase I TRL 5 prototype, which is defined as a CubeSat payload. Our earlier work found an unexpected deviation in the behavior of MFC actuators reacting to thermal cycles like those experienced on-orbit. This atypical behavior could cause imprecise deployment in active space structures. We established Phase II feasibility by defining and controlling this behavior.
Research description
Phase I developed and validated performance evaluation and thermal compensation tools for MFC actuators subjected to thermal cycling, verified weight, size, and power estimates for a flight payload, and established that CVS will fit into a CubeSat. In Phase II we deliver a flight-ready nanosatellite.
Anticipated results
Phase II produces a ready-to-launch TRL 6 or higher nanosatellite compatible with JPL CREAM space environmental sensors. We plan a 6-12 month LEO mission.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
CVS is the first extensive spaceflight validation for piezocomposite actuator materials. CVS will establish operational limits, determine long-duration space environmental exposure trends, and evaluate thermal compensation options for the piezocomposite materials needed to control large-scale precision active space-structures like large deployable adaptive optical surfaces. Piezocomposite material applications include active control of composite reflectors (for example, see JPL Active Composite Reflector research), large sunshields, external occulters, large solar arrays for solar electric propulsion and other active structures. Examples include structures like the OCT Lightweight Materials and Structures long-duration deployables. Maintaining the shape of large, high-precision reflectors will be quite difficult; active reflectors that adjust their shape in situ will be cheaper and lighter. JPL CREAM compatibility provides a low-cost path to in-situ real-time space environment measurements that can, for example, unravel complex synergistic environment and interaction degradation effects on materials. Other CVS applications include active shape distortion compensation in non-reflector surfaces, e.g., struts, bipods, etc. Additionally, an active, mission-capable SHM system has a host of key applications like crew safety, ISS utilization, deep-space missions, vehicle mass reduction, and Mars and lunar exploration.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Non-NASA MFC actuator applications include small aperture adaptive optics for nanosatellite-based Earth imaging firms like PlanetLabs and nanosatellite space telescopes like ExoplanetSat. Modern tactical aircraft and hypersonic vehicles require that substantial portions of the structure withstand extreme environments that induce major thermal, mechanical and acoustic loads. A fundamental problem is the dependence of the deformation state of the structure (feedback effect) on these loads (heating, aerodynamic, acoustic)?this could be addressed by the proposed work. Active control is needed for jitter suppression and to compensate for thermal and mechanical disturbances. Commercial space companies need SHM to reduce time to launch and operation costs and improve safety. These needs are particularly important for re-useable vehicles, where information on structural integrity during all stages of flight is important for flight recertification, validation of vehicle operation models, and prediction of remaining service life. Other applications include Homeland Security structural analysis to mitigate threats (preparedness) and assess damage (response), smart structures, and SHM of civil infrastructures, land/marine structures, and military structures. Civil infrastructure includes wind turbines (alternative and renewable energy). SHM is an emerging industry driven by an aging infrastructure, malicious humans, and the introduction of advanced materials and structures.