Availability of reliable flight sensor data and knowledge of the structural behaviour are essential for safe operation of the Ariane launcher. The Ariane launcher is currently monitored by hundreds of electric sensors during test and qualification. Fibre optic sensors are regarded as a potential technique to overcome limitations of recent monitoring systems for the Ariane launcher [1]. These limitations include cumbersome application of sensors and harness as well as a very limited degree of distributed sensing capability. But, in order to exploit the various advantages of fibre optic sensors (high degree of multiplexing, distributed sensing capability, lower mass impact, etc.) dedicated measurement systems have to be developed and investigated. State-of-the-art fibre optic measurement systems often use free beam setups making them bulky and sensitive to vibration impact. Therefore a new measurement system is developed as part of the ESAstudy [2].
KEYWORDS: Sensors, Fiber Bragg gratings, Fiber optics sensors, Astronomical imaging, Digital signal processing, Temperature metrology, Aerospace engineering, Semiconductor lasers, Signal processing, Space telescopes
We present our work about the development of two complementary interrogation schemes based on fiber optic sensing for the use of structural and thermal monitoring of Ariane launchers. The advantages of fiber optic sensing in particular light-weight, immunity to electromagnetic interferences and the possibility of sensor distribution along optical fibers are driving factors for utilization of this technology in space crafts [1]. The edge-filter (EF) and scanning-laser (SL) interrogators for determination of the mean wavelength of fiber Bragg grating (FBG) sensors have been implemented as two separate demonstrators. Within this paper we describe the functional principles of both interrogators. Furthermore we present test results where the developed systems have been used for readout of FBG sensors which are implemented in an Ariane structural demonstrator during thermal, thermal-vacuum and vibration tests. Functionality of both systems is demonstrated and their potential for further development towards space qualified systems is shown.
Since the performance characteristics of the two systems are different from each other, they are dedicated for different sensing applications on a launcher. The EF sensor interrogator provides a sample rate of 20 kHz at a number of 4 connected sensors and supports parallel readout and aliasing free operation. Therefore it is best suited for high priority measurement. Structural monitoring which requires the acquisition of real time sensor information in order to support control of the launcher is one operation area for a future EF system. The SL interrogator provides an overall measurement rate of 1 kHz at a number of 24 connected sensors distributed on three sensor channels. It can be adapted to any sensors that have design wavelengths lying within the output spectrum of the laser diode. Furthermore the number of overall sensors to be read out with this system can be adapted easily. Thermal mapping of satellite panels is one possible future application for the SL interrogator.
Fibre Bragg gratings are used as temperature or longitudinal strain sensors in a number of applications. Only a few
studies are concerned with transversal stress applied to these sensors. We recently derived an analytical solution for the
reflection spectra of shear strain loaded fibre Bragg gratings. The experimental verification of this theory is presented in
this work. A fibre-coupled spectra analyzer based on a Fabry-Perot tuneable filter was set up in order to measure the
predicted effect. The setup is able to split and measure simultaneously the spectra of the two polarisation main axes of
birefringent fibres. The experimental observations are in agreement with predictions derived by mode coupling theory.
Force-torque sensors are key elements in modern force feedback and robotic control applications. For special applications
resistance against electromagnetic interference, high amount of load cycles or chemical resistance are important. For these
applications, fiber-Bragg-grating based force torque sensors have been seen as possible solutions. Yet the implementation
of a force-torque-sensor with six degrees of freedom and well conditioned sensitivities is still lacking demonstration. In
this work, we demonstrate the design of a miniaturized fiber-Bragg-grating based force-torque sensor with six degrees
of freedom using a numerical nonlinear programming technique. We implement the optimized structure and show its
feasibility and sensitivity.
Today's spacecraft employ hundreds of sensors. With spacecraft becoming increasingly complex, there is the need
for spaceborne measurement systems that are of low mass and volume, yet of high reliability and lifetime in the
harsh space environment. Targeted towards future applications in telecommunication satellites, the presented
FOSAT project aimes at a corresponding fiber-optic measurement system demonstrator. This goal particularly
calls for a vast number of sensors being multiplexed, enabling systems with a minuscle per-sensor mass, volume
and power share. To achieve this, several multiplexing techniques are jointly applied in the presented project to
form hybrid multiplexing. Furthermore, an interrogation technique which allows a dynamically adaptable tradeoff
between the number of sampled sensors and the sampling rate is employed to increase operational flexibility.
The design and the implementation of this unit are presented and a test result is summarized.
Chromatic confocal microscopy is a common way to interrogate topologies and is well understood. Thin film
reflectometry (TFR), on the other hand, is a way to monitor film thicknesses. Semiconductor and optics producing
industries, e.g., require information about topological, film thickness or optical constants. We developed
a spectrometric measuring system which is capable of determining high precision thin film thickness and topographic
information of a specimen at the same time. The spectral intensity distribution reflected by a transparent
thin film differs from a spectroscopic confocal observation by a chromatic measurement head, since the spectral
interference fringes appear in the spectra. The spectrometer-based system interrogates both confocal, as well as
thin film signals employing an analytical model of the chromatic shift of the measuring head, film composition
and a least-square estimator.
Hence, the advantage of this combined measuring system is the concurrent determination of film thickness and
distance to the measuring head. By scanning the surface of a specimen laterally, a both tomo- and topological
image can be acquired. Spacial measurements at test objects were carried out to demonstrate this measurement
principle and the results are discussed.
Fiber-Bragg-grating (FBG) sensors have become commercially available sensors for the measurement of temperature,
strain and many other quantities. The sensor information is encoded in the spectral reflection characteristic
of these devices. Their usage as strain sensors is one of the most prominent fields of application. Strains
from a structure which is to be monitored are transferred into the fiber-Bragg-grating, by surface bonding or
embedding. In general an arbitrary state of strain may thus occur within the FBG, represented by a full strain
tensor with normal strain components, as well as with shear strain components. The influence of normal strains
is well understood and has been treated theoretically by many authors. The influence of shear strains is however
not well understood. As we were recently able to theoretically demonstrate by a full tensor coupled mode
analysis, shear strains do influence the spectral response of fiber-Bragg-sensors and thus have to be considered.
In this work, an introduction to the modeling of shear strains within fiber-Bragg-gratings is given. We discuss
reasonable approximations for the simplification of the theoretical model. We compute, to our knowledge for
the first time, the direct influence of shear strains on the output of a FBG measurement system and show the
cases when shear strain effects are relevant. Furthermore, we compare the sensitivity of different interrogation
algorithms towards shear strain influences on the measurement system output.
Fiber Bragg grating (FBG) sensors have proven to be adaptable for monitoring various physical quantitites
like temperature, strain, or even vibrations and acoustic noise. Several interrogation methods, like spectroscopic
evaluation, interferometric interrogation, active scanning or active filtering systems or passive filtering systems are
capable of monitoring the wavelengths of the FBG sensors. Among the passive filtering systems, interrogators
based on arrayed waveguide gratings (AWG) have shown to be promising candidates for sensing with FBGs,
especially for high-frequency measurement tasks.
Whereas the resolution- and the accuracy-dependency on light intensity of direct wavelength determining systems
like spectrometers or scanning filter systems can be minimized by data processing algorithms, the performance
of passive filtering based interrogators is more sensitive regarding uncertainties induced by electrical amplifier
noise, FBG peak shape, light source intensity, etc.. The influence of different sources of uncertainties for AWGbased
interrogators on the accuracy of the wavelength determination are investigated by an analytical model.
The model is evaluated by a numerical simulation. It is shown how strongly the accuracy and the resolution of
such an interrogator depend on the mentioned sources of uncertainties. Considering the obtained results, one
can say that FBG interrogators based on arrayed waveguide gratings have, including the shown restrictions, the
potential for rugged, compact and cost effective high accuracy wavelength interrogators.
Within this work, we describe our newly developed interrogation scheme for fiber optic sensing applications.
This measurement system will be utilized in Ariane launchers for monitoring temperature and mechanical stress
distribution during flight. The acquired sensing data can be used to control propulsion unit an thrusters and
thereby adapt the flight path in a way that damage on the launcher is prevented.
In order to detect the peak wavelength of e.g. fiber Bragg grating (FBG) sensors, a tunable laser source based
on a modulated-grating laser diode is able to scan through a more than 40nm wide spectrum in the infrared
region. Several sensors with different spectral answers can be placed inside one sensor fiber and then interrogated
sequentially. The magnitudes of the reflected intensities depend on the actual sensor position that is determined
by the measurand (e.g. temperature). One single sensor is scanned by a variable number of spectral sampling
points and the spectral answer of the sensor is then calculated by centroid algorithms. Depending an the spectral
width of one sensor, the number of sensors that shall be interrogated and the required sampling points per sensor,
a maximum sampling frequency of 240kHz is achievable with our hardware.
Contrary to comparable systems, our interrogator is capable of switching to any available wavelength of its
spectrum within a couple of nanoseconds. Therefore standard continuous sweeping through the entire spectrum
is not necessary. This results in a new measurement scheme, wherein spectral gaps between consecutive sensors
do not need to be scanned and can be skipped. Since most of the spectrum consists of the gaps between the
sensors, overall measurement time is thereby reduced significantly. One problem arises from this measurement
scheme: Due to the fact that the sensor's spectral answers vary in time, a special algorithm for tracking the
spectral movement has to be implemented.
The scope of this work is the description, implementation and assessment of this new peak tracking procedure.
After describing the measurement setup, we will therefore explain the algorithm behind the peak tracking measurement.
Afterwards the simulation process is explained and results are shown. Performance obtained by peak
tracking compared to standard continuous wavelength scanning is evaluated in detail and further development
steps which are necessary to obtain a fully sophisticated interrogation systems are discussed.
Multi-axial force and torque sensing is of importance for robot control and many force-feedback applications.
Minimal invasive robotic surgery (MIRS) is a possible field of application of force and torque sensors with up
to six degrees of freedom. Although these sensors are not yet employed in current commercial MIRS systems,
extensive work has been carried out on the development of these sensors. Some of their issues are related to
their electric working principle: they are limited in performance by thermal noise, need electric power inside
the patient and are not usable under influence of strong magnet fields (e. g. in MRI machines). One possible
alternative is seen in fiber optic force torque sensors, since the signal demodulation may be located in some
distance to the actual sensor and they also do not have to include any magnetic material.
This article presents a fiber optic force and torque sensor with six degrees of freedom. The general setup
resembles a Stewart Platform, whereas its connecting beams are formed by the fiber itself, and the element
creating stiffness may be of arbitrary form. Only a single fiber is needed to extract all six parameters since they
are measured on six multiplexed fiber Bragg grating sensors. We demonstrate how the sensor is realized and
show results of torque measurements with variable load.
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