Search NASA⌕ Search
Home/Archive/NASA NTRS

NASA NTRS · 20150023019

Fiber Optic Sensing System Technology (FOSS): A New Sensor Paradigm for Comprehensive Subsystem Model Validation throughout the Vehicle Life-Cycle

Pena, Francisco·Richards, Lance·Parker, Allen R., Jr.·Piazza, Anthony·Chan, Patrick·Hamory, Phil
View original source ↗Export metadata ↓

Abstract

This presentation highlights the usefulness of the measurement capabilities without disclosing the methods required toobtain the measurements.

Explore related subjects

FOSSFiber Grating Braggfiber optics

Keep this discovery

Explore connections, maps & timelines

BibTeXRIS

Pena, Francisco, Richards, Lance, Parker, Allen R., Jr., Piazza, Anthony, Chan, Patrick, Hamory, Phil. 2015-10-26. Fiber Optic Sensing System Technology (FOSS): A New Sensor Paradigm for Comprehensive Subsystem Model Validation throughout the Vehicle Life-Cycle. https://ntrs.nasa.gov/citations/20150023019

Cite the original work for its findings. Save a collection to share your selection of sources.

KEEP EXPLORING

Related reports

NASA NTRS2018

Active In-Flight Load Redistribution Utilizing Fiber-Optic Shape Sensing and Multiple Control Surfaces

Morphing wing technologies have gained research interest in recent years as technological advancements pave the way for such innovations. A key benefit of such a morphing wing concept is the ability of the wing to transition into an optimal configuration at multiple flight conditions. Such a morphing wing will have applications not only in drag reduction but also in flutter suppression and gust alleviation. By manipulating the wing geometry to match a given flight profile it is likely that the wing will yield increases in not just aerodynamic efficiency but also structural efficiency. These structurally efficient designs will likely rely on some type of structural sensing system which will ensure the wing maintains positive margins throughout its flight profile.

FOSS↗
NASA NTRS2012

Validation Tests of Fiber Optic Strain-Based Operational Shape and Load Measurements

Aircraft design has been progressing toward reduced structural weight to improve fuel efficiency, increase performance, and reduce cost. Lightweight aircraft structures are more flexible than conventional designs and require new design considerations. Intelligent sensing allows for enhanced control and monitoring of aircraft, which enables increased structurally efficiency. The NASA Dryden Flight Research Center (DFRC) has developed an instrumentation system and analysis techniques that combine to make distributed structural measurements practical for lightweight vehicles. Dryden's Fiber Optic Strain Sensing (FOSS) technology enables a multitude of lightweight, distributed surface strain measurements. The analysis techniques, referred to as the Displacement Transfer Functions (DTF) and Load Transfer Functions (LTF), use surface strain values to calculate structural deflections and operational loads. The combined system is useful for real-time monitoring of aeroelastic structures, along with many other applications. This paper describes how the capabilities of the measurement system were demonstrated using subscale test articles that represent simple aircraft structures. Empirical FOSS strain data were used within the DTF to calculate the displacement of the article and within the LTF to calculate bending moments due to loads acting on the article. The results of the tests, accuracy of the measurements, and a sensitivity analysis are presented.

FOSS↗