Fiber-optic sensors are used for their low cost, small size, light weight, minimal associated intrusion, high accuracy, and reliability. The proposed effort will establish feasibility of novel fiber-optic sensors from which an associated sensing platform would derive dramatically-improved performance and/or improvement in platform size, weight, power, and cost compared to current commercial offerings.
The technology will considerably improve NASA’s flight test measurement and in-situ monitoring capability over the current state of the art, opening up new sensing possibilities for real-time, in-situ flight/spaceflight measurements.
With an improved understanding of flight/spaceflight structural dynamics, the technology will lead to improved airframe and component designs. With improved, integrated real-time feedback control signal generation and structural health monitoring capability, future aircraft and spaceflight vehicles will operate more safely, predictably, and efficiently.
The proposed technology enables acquisition of real-time, in-flight strain and temperature data related to structural dynamics analysis and health monitoring of aircraft and spacecraft. In addition, the technology enables feedback control signal generation, NDE / modal analysis, and thermal profiling. The technology can be applied to components, structures, aerodynamic surfaces, fixed and morphable flight control surfaces, and electrical propulsion system power sources.
Non-NASA commercial applications of the technology include renewable wind energy, commercial aerospace & aviation, oil & gas, automotive, nuclear energy, and perimeter security.