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Journal articles on the topic 'Aerospace measurements'

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Author: Grafiati

Published: 10 December 2022

Last updated: 28 January 2023

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1

Kingsley-Rowe, J. R., G. D. Lock, and A. G. Davies. "Aerospace applications of luminescent paint." Aeronautical Journal 107, no. 1077 (November 2003): 637–48. http://dx.doi.org/10.1017/s0001924000013518.

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Abstract Luminescent paints allow non-intrusive measurement of pressure and temperature at high spatial resolution without prior knowledge of the flow-field. Experiments have demonstrated that a ‘standard’ luminescent paint technique, developed by BAE Systems, can simultaneously measure steady pressure and temperature. This is achieved through knowledge of the paint phosphorescence lifetime rather than the absolute intensity, which increases the measurement accuracy. In addition, a new ‘fast’ paint has been calibrated at the University of Bath for the measurement of unsteady pressure using a variable frequency pulsing air jet. Pressure measurements were made with both paints in the wake of various excrescences, sized to produce vortex shedding in the frequency range 500–4,200Hz, in a transonic tunnel. The extent of the wakes was determined from a flow visualisation technique. Time-averaged measurements, using both luminescent paints, and transient measurements of the unsteady pressure field, made with the fast paint, were compared with transducer data. For all cases the luminescent paint data compared well with the conventional measurements and the Strouhal number agreed well with data from the literature. The use of luminescent paint for the simultaneous measurement of pressure and temperature over a NACA 0012 aerofoil, as well as the quantification of convective heat transfer is examined in Part 2.

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Kingsley-Rowe, J. R., G. D. Lock, and A. G. Davies. "Aerospace applications of luminescent paint." Aeronautical Journal 107, no. 1077 (November 2003): 649–56. http://dx.doi.org/10.1017/s000192400001352x.

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Abstract A heat transfer measurement technique has been developed, which utilised a laser to heat a spot of the ‘standard’ luminescent paint on an insulated metal wind tunnel model. The convective heat transfer coefficient was determined from the experimental quasi steady-state surface temperature, and solutions obtained from radial and axial conduction in a numerical heat transfer model. The convective heat transfer coefficient variation over both a flat plate and a NACA 0012 aerofoil have been measured in transonic flow. Measurements obtained from the flat plate were seen to agree well with correlation data from the literature. Measurements on the NACA 0012 aerofoil indicated the point of transition from laminar to turbulent boundary layer as well as the location of shock boundary layer interaction. The luminescent paint provided simultaneous measurements of pressure and temperature (see Part 1). The distribution of pressure over the NACA 0012 aerofoil was shown to be in excellent agreement with conventional transducer data, although the luminescent paint data provided greater spatial resolution. The position of the shock determined from the heat transfer measurements was shown to be in excellent agreement with the pressure measurements.

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3

Kondratyev, K. Ya, V. V. Kozoderov, and P. P. Fedchenko. "Studies of vegetation and soils from aerospace measurements." Advances in Space Research 5, no. 6 (January 1985): 355–57. http://dx.doi.org/10.1016/0273-1177(85)90341-2.

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4

Pongsakornsathien, Nichakorn, Alessandro Gardi, Yixiang Lim, Roberto Sabatini, and Trevor Kistan. "Wearable Cardiorespiratory Sensors for Aerospace Applications." Sensors 22, no. 13 (June 21, 2022): 4673. http://dx.doi.org/10.3390/s22134673.

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Emerging Air Traffic Management (ATM) and avionics human–machine system concepts require the real-time monitoring of the human operator to support novel task assessment and system adaptation features. To realise these advanced concepts, it is essential to resort to a suite of sensors recording neurophysiological data reliably and accurately. This article presents the experimental verification and performance characterisation of a cardiorespiratory sensor for ATM and avionics applications. In particular, the processed physiological measurements from the designated commercial device are verified against clinical-grade equipment. Compared to other studies which only addressed physical workload, this characterisation was performed also looking at cognitive workload, which poses certain additional challenges to cardiorespiratory monitors. The article also addresses the quantification of uncertainty in the cognitive state estimation process as a function of the uncertainty in the input cardiorespiratory measurements. The results of the sensor verification and of the uncertainty propagation corroborate the basic suitability of the commercial cardiorespiratory sensor for the intended aerospace application but highlight the relatively poor performance in respiratory measurements during a purely mental activity.

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Ornat, Artur, Marek Uliasz, Grzegorz Bomba, Andrzej Burghardt, Krzysztof Kurc, and Dariusz Szybicki. "Robotised Geometric Inspection of Thin-Walled Aerospace Casings." Sensors 22, no. 9 (May 1, 2022): 3457. http://dx.doi.org/10.3390/s22093457.

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This paper deals with the development of dimensional control technology for the production of ADT (accessory drive train) gearbox housing. The project included the development of a robotic geometry inspection station for thin-walled aerospace casings. Laser profilometers from two brands, Cognex and Keyence, were used to measure. A proprietary software solution for arc measurements is presented. The obtained solutions were compared and verified in accordance with the requirements of the manufacturer Pratt and Whitney Rzeszów S.A. The results of the work indicated that correct solutions were obtained with a very large reduction in control time. In addition, the measurement is fully automated and transferable to the company’s electronic systems.

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Hajiyev, Chingiz, and Ahmet Sofyali. "Spacecraft localization by indirect linear measurements from a single antenna." Aircraft Engineering and Aerospace Technology 90, no. 5 (July 2, 2018): 734–42. http://dx.doi.org/10.1108/aeat-12-2015-0245.

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Purpose The purpose of this paper is to present a two-stage approach for estimation of spacecraft’s position and velocity by indirect linear measurements from a single antenna. Design/methodology/approach In the first stage, direct nonlinear antenna measurements are transformed to linear x-y-z coordinate measurements of spacecraft’s position, and statistical characteristics of orbit determination errors are analyzed. Variances of orbit parameters’ errors are chosen as the accuracy criteria. In the second stage, the outputs of the first stage are improved by the designed Extended Kalman Filter for estimation of the spacecraft’s position and velocity on indirect linear x-y-z measurements. Findings The complex content of the measurement matrix in the conventional method causes periodic singularities in simulation results. In addition, the convergence of the filter using direct measurements is highly dependent on the initialization parameters’ values due to the nonlinear partial derivatives in the Jacobian measurement matrix. The comparison of the accuracy of both methods shows that the estimation by using indirect measurements reduces the absolute estimation errors. The simulation results show that the proposed two-stage procedure performs both with better estimation accuracy and better convergence characteristics. The method based on indirect measurements provides an unnoticeably short transient duration. Practical implications The proposed method can be recommended for satellite orbit estimation regarding its presented superiorities. Originality/value Inputting the single antenna measurements to the filter indirectly results in a quite simpler measurement matrix. As a result, the convergence of the filter is faster and estimation errors are lower.

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7

Berri, Pier Carlo, Matteo D. L. Dalla Vedova, and Paolo Maggiore. "Experimental comparison of Fiber Bragg Grating installation techniques for aerospace systems." MATEC Web of Conferences 304 (2019): 04012. http://dx.doi.org/10.1051/matecconf/201930404012.

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Aircraft systems are becoming more and more complex, as they are required to perform multiple functions. For example, smart systems need to be able to self-monitor their working parameters, in order to infer their health status. All these additional functions require the system to acquire a multitude of measurements; albeit sometimes it is possible to implement virtual sensor techniques, dedicate sensing hardware is usually needed. As a main drawback, the installation of the needed sensors adds up to the total complexity, weight, cost and failure rate of the system. In this context, minimally invasive sensors can be used to measure the system parameters with high spatial resolution and minimal added complexity. One key technology in this field is the Fiber Bragg Gratings (FBG) optical sensors, used to perform strain and temperature measurements. This work describes an experimental campaign intended to assess and validate several installation techniques for FBGs as strain sensors. Two test benches were developed for different measurement setups. One is intended for creep and repeatability tests of a FBG sensor glued at both ends; the other was used to compare point gluing and continuous gluing techniques on an aluminium beam subject to a bending load. Results are compared with numerical simulations of the structure and measurements performed with traditional strain gages.

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8

Magdziak, Marek. "The influence of a number of points on results of measurements of a turbine blade." Aircraft Engineering and Aerospace Technology 89, no. 6 (October 2, 2017): 953–59. http://dx.doi.org/10.1108/aeat-03-2016-0044.

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Purpose The purpose of this paper was to determine the influence of a number of measured points on results of measurements of turbine blades, which are the parts of aircraft engines. The selection of a number of points is the part of a measurement strategy in the coordinate measuring technique and determines the accuracy of measurements. Design/methodology/approach Numerical and experimental investigations were conducted. The measurements were simulated using different numbers of measured points. The simulated measurements were performed for the selected dispersion of measured points. The dispersion reflected the inaccuracy of a manufacturing process of the considered product and the uncertainty of measurements of curvilinear surfaces. To verify the accuracy of the numerical studies, experimental research was conducted. The real measurements were conducted using the selected coordinate measuring machine. Findings The gained results following the simulations can be very useful when selecting the appropriate number of measured points. The chosen number of points may be used during real measurements of turbine blades conducted on coordinate measuring machines. The results of numerical research indicate that there should be used the average radii of leading and trailing edges to increase the accuracy of measurements. The results of real coordinate measurements confirmed the results of simulation studies. Originality/value The main novelty of the paper is the presented methodology for determining the influence of measured points on results of measurements. The presented methodology helps the user of a coordinate measuring system select the appropriate measurement strategy of free-form surfaces applied in the aerospace industry.

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Jansson, N., and G. Stenfelt. "Steady and unsteady pressure measurements on a swept-wing aircraft." Aeronautical Journal 118, no. 1200 (February 2014): 109–22. http://dx.doi.org/10.1017/s0001924000009015.

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Abstract Steady and unsteady pressure measurements are conducted for a tailless aircraft model. The main aim with the presented experimental work is to investigate the difficulties and possibilities involved in using an available pressure sensing system for accurate unsteady pressure measurement. The experimental procedure which is utilised for unsteady pressure measurements is described in detail. In particular, the importance of synchronised timing is recognised. For a harmonically varying pressure a small time delay in the measurement chain can result in a significant phase shift. Also, difficulties and uncertainties that are still present are pointed out. The results from these experiments are compared to numerical results based on unsteady potential flow theory. In general, the experimental and computational results show similar trends. Especially good agreement is found for the steady pressure measurements. For the unsteady pressure measurements a possible Reynolds number dependency is found for the considered test conditions.

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10

King, Andrew, A. D. Evans, Philip J. Withers, and C. Woodward. "The Effect of Fatigue on Residual Peening Stresses in Aerospace Components." Materials Science Forum 490-491 (July 2005): 340–45. http://dx.doi.org/10.4028/www.scientific.net/msf.490-491.340.

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The Rolls-Royce Wide Chord Fan Blade (WCFB) is an innovative aerospace component, manufactured from Ti-6Al-4V alloy. The blade roots experience fatigue loading during flight, and are subject to fretting fatigue where they contact the fan disc. Shot peening (SP) and laser shock peening (LSP) are mechanical surface treatments which have been applied to the blade root to improve fatigue strength and damage tolerance. Both techniques cause local plastic deformation of the material, resulting in a layer of compressive residual stress. The compressive stress from LSP may reach a depth of 2mm in titanium, compared with only 0.25mm for conventional SP. These compressive stresses are balanced by subsurface tensile stress. LSP is reported to cause less work hardening than shot peening. It is important to understand the stability of the residual stresses during service conditions so that accurate fatigue life assessments can be made. Fatigue testing has been carried out on blade root section test pieces and on notched three point bend samples. Residual strain and stress measurements have been made on both types of sample. Residual strain measurements have been made using monochromatic and pulsed time-of-flight neutron diffraction techniques. The large penetration lengths of these types of radiation allow accurate residual strain measurements to be made non-destructively, deep inside a component. Because no material removal is required, no stress relaxation occurs, allowing the measurement of balancing tensile stresses. LSP and SP samples have been studied, both in the as-received condition and after fatigue.

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11

Huang, Xun. "Compressive Sensing and Reconstruction in Measurements with an Aerospace Application." AIAA Journal 51, no. 4 (April 2013): 1011–16. http://dx.doi.org/10.2514/1.j052227.

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12

Tobiska, W. Kent, D. Bouwer, D. Smart, M. Shea, J. Bailey, L. Didkovsky, K. Judge, et al. "Global real-time dose measurements using the Automated Radiation Measurements for Aerospace Safety (ARMAS) system." Space Weather 14, no. 11 (November 2016): 1053–80. http://dx.doi.org/10.1002/2016sw001419.

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13

Gopinath, K., K. Raghavendra, M. K. Behera, E. V. Subba Rao, M. Umakanth, and S. Gopinath. "Product Design Aspects for Design of Accurate Mass Properties Measurement System for Aerospace Vehicles." Applied Mechanics and Materials 110-116 (October 2011): 4712–18. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.4712.

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Mass properties of aerospace vehicle viz Weight, Center of Gravity (Xcg, Ycg, Zcg) & Mass Moment of Inertia (Ixx, Iyy & Izz) are critical inertial parameters which are vital to meet the intended mission objectives. Accurate mass properties measurement is needed for fast maneuvering aerospace vehicles to meet the Control and Guidance requirements within the tolerable limits generated by the System Designer. Mass properties estimation is vital during the configuration design phase of an aerospace vehicle. Assumptions and Constraints during the configuration design, limits the accuracy of estimations making the mass properties measurement mandatory. The mass properties of the aerospace vehicle can be measured by numerous methods, but for achieving high accuracies within the tolerable limits, the measurement system should have advanced technologies and measurement methodologies. Based on the experience, mass properties measurement systems were designed using Load Cells and Cross-Flexural Pivots in two different systems (Weight and CG in System-1, MOI in System-2), which have limited accuracy and also involves tedious external measurements. Adopting Air-Bearing (T / H / Spherical shape) supported with accurate sensors using Inverted Torsion Pendulum method, Multiple Point Weighing method and a proper measurement methodology, enhances the accuracy of the measurement system. Usage of spherical bearing yields a better accurate system but has the difficulty in realization of the system indigenously, whereas use of T or H-shape bearing is a feasible solution for achieving the desired accurate mass properties specifications. This paper gives an insight into to the product design aspects to be considered for realization of accurate mass properties measurement system.

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Stevenson, J. C., and K. V. Alexander. "Circular flight kite tests: converting to standard results." Aeronautical Journal 110, no. 1111 (September 2006): 605–14. http://dx.doi.org/10.1017/s0001924000001469.

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Abstract Kite testing by flying in a horizontal circle, was developed in order to address the inevitable accuracy problems inherent in pre-existing kite measurement techniques. However the raw results from this circular flight method are not directly comparable with traditional kite performance measurements. To enable direct comparisons to be made, modifying equations have been developed to convert the raw circular flight results into the traditional measurements of lift to drag ratio, and lift coefficient. This paper derives the modifying equations, and presents experimental results comparing traditional measurements with both the raw and modified circular flight results. The modifying equations are applied to an example set of results to assess the sensitivity of the test environment parameters. It is concluded that for many cases, the discrepancy between the raw circular flight test results and traditional measurement techniques is small enough to ignore. Alternatively, the modifying equations given in the paper may readily be encoded so that traditional results may be quickly obtained from this novel test method.

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SINGH, YADUNATH. "ELECTRICAL RESISTIVITY MEASUREMENTS: A REVIEW." International Journal of Modern Physics: Conference Series 22 (January 2013): 745–56. http://dx.doi.org/10.1142/s2010194513010970.

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World-wide interest on the use of ceramic materials for aerospace and other advanced engineering applications, has led to the need for inspection techniques capable of detecting unusually electrical and thermal anomalies in these compounds. Modern ceramic materials offer many attractive physical, electrical and mechanical properties for a wide and rapidly growing range of industrial applications; moreover specific use may be made of their electrical resistance, chemical resistance, and thermal barrier properties. In this review, we report the development and various techniques for the resistivity measurement of solid kind of samples.

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16

Shortis, Mark R., Stuart Robson, Thomas W. Jones, William K. Goad, and Charles B. Lunsford. "PHOTOGRAMMETRIC TRACKING OF AERODYNAMIC SURFACES AND AEROSPACE MODELS AT NASA LANGLEY RESEARCH CENTER." ISPRS Annals of Photogrammetry, Remote Sensing and Spatial Information Sciences III-5 (June 6, 2016): 27–34. http://dx.doi.org/10.5194/isprsannals-iii-5-27-2016.

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Aerospace engineers require measurements of the shape of aerodynamic surfaces and the six degree of freedom (6DoF) position and orientation of aerospace models to analyse structural dynamics and aerodynamic forces. The measurement technique must be non-contact, accurate, reliable, have a high sample rate and preferably be non-intrusive. Close range photogrammetry based on multiple, synchronised, commercial-off-the-shelf digital cameras can supply surface shape and 6DoF data at 5-15Hz with customisable accuracies. This paper describes data acquisition systems designed and implemented at NASA Langley Research Center to capture surface shapes and 6DoF data. System calibration and data processing techniques are discussed. Examples of experiments and data outputs are described.

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Shortis, Mark R., Stuart Robson, Thomas W. Jones, William K. Goad, and Charles B. Lunsford. "PHOTOGRAMMETRIC TRACKING OF AERODYNAMIC SURFACES AND AEROSPACE MODELS AT NASA LANGLEY RESEARCH CENTER." ISPRS Annals of Photogrammetry, Remote Sensing and Spatial Information Sciences III-5 (June 6, 2016): 27–34. http://dx.doi.org/10.5194/isprs-annals-iii-5-27-2016.

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Aerospace engineers require measurements of the shape of aerodynamic surfaces and the six degree of freedom (6DoF) position and orientation of aerospace models to analyse structural dynamics and aerodynamic forces. The measurement technique must be non-contact, accurate, reliable, have a high sample rate and preferably be non-intrusive. Close range photogrammetry based on multiple, synchronised, commercial-off-the-shelf digital cameras can supply surface shape and 6DoF data at 5-15Hz with customisable accuracies. This paper describes data acquisition systems designed and implemented at NASA Langley Research Center to capture surface shapes and 6DoF data. System calibration and data processing techniques are discussed. Examples of experiments and data outputs are described.

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Grunefeld, G., V. Beushausen, A. Brockhinke, and P. Andresen. "Laser-Based Multiparameter Measurements." AIAA Journal 35, no. 3 (March 1997): 500–508. http://dx.doi.org/10.2514/2.123.

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Porter, C. O., J. W. Baughn, T. E. McLaughlin, C. L. Enloe, and G. I. Font. "Plasma Actuator Force Measurements." AIAA Journal 45, no. 7 (July 2007): 1562–70. http://dx.doi.org/10.2514/1.24497.

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20

Wang, Xiaogang, Wutao Qin, Yuliang Bai, and Naigang Cui. "Cooperative target localization using multiple UAVs with out-of-sequence measurements." Aircraft Engineering and Aerospace Technology 89, no. 1 (January 3, 2017): 112–19. http://dx.doi.org/10.1108/aeat-06-2015-0160.

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Purpose The time delay would occurs when the measurements of multiple unmanned aerial vehicles (UAVs) are transmitted to the date processing center during cooperative target localization. This problem is often named as the out-of-sequence measurement (OOSM) problem. This paper aims to present a nonlinear filtering based on solving the Fokker–Planck equation to address the issue of OOSM. Design/methodology/approach According to the arrival time of measurement, the proposed nonlinear filtering can be divided into two parts. The non-delay measurement would be fused in the first part, in which the Fokker–Planck equation is utilized to propagate the conditional probability density function in the forward form. The time delay measurement is fused in the second part, in which the Fokker–Planck is used in the backward form approximately. The Bayes formula is applied in both parts during the measurement update. Findings Under the Bayesian filtering framework, this nonlinear filtering is not only suitable for the Gaussian noise assumption but also for the non-Gaussian noise assumption. The nonlinear filtering is applied to the cooperative target localization problem. Simulation results show that the proposed filtering algorithm is superior to the previous Y algorithm. Practical implications In this paper, the research shows that a better performance can be obtained by fusing multiple UAV measurements and treating time delay in measurement with the proposed algorithm. Originality/value In this paper, the OOSM problem is settled based on solving the Fokker–Planck equation. Generally, the Fokker–Planck equation can be used to predict the probability density forward in time. However, to associate the current state with the state related to OOSM, it would be used to propagate the probability density backward either.

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Li, Xiaohua, Bo Lu, Wasiq Ali, Jun Su, and Haiyan Jin. "Passive Sonar Multiple-Target Tracking with Nonlinear Doppler and Bearing Measurements Using Multiple Sensors." International Journal of Aerospace Engineering 2021 (October 11, 2021): 1–11. http://dx.doi.org/10.1155/2021/4163766.

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The major advantage of the passive multiple-target tracking is that the sonars do not emit signals and thus they can remain covert, which will reduce the risk of being attacked. However, the nonlinearity of the passive Doppler and bearing measurements, the range unobservability problem, and the measurement to target data association uncertainty make the passive multiple-target tracking problem challenging. To deal with the target to measurement data association uncertainty problem from multiple sensors, this paper proposed a batch recursive extended Rauch-Tung-Striebel smoother- (RTSS-) based probabilistic multiple hypothesis tracker (PMHT) algorithm, which can effectively handle a large number of passive measurements including clutters. The recursive extended RTSS which consists of a forward filter and a backward smoothing is used to deal with the nonlinear Doppler and bearing measurements. The target range unobservability problem is avoided due to using multiple passive sensors. The simulation results show that the proposed algorithm works well in a passive multiple-target tracking system under dense clutter environment, and its computing cost is low.

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22

Traub, L. W. "Estimating aerofoil lift from flow angle." Aeronautical Journal 119, no. 1219 (September 2015): 1167–73. http://dx.doi.org/10.1017/s0001924000011180.

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Estimation of the lift of an aerofoil is one of the fundamental measurements of fluid mechanics. Lift is commonly measured using a load cell or a force balance. Non-intrusive methods to measure lift are usually pressure based. Aerofoils may be pressure tapped where small surface orifices are connected via tubing to a pressure measurement system, either a multi-tube manometre or an electronic system. Both measurement options add cost and complication, especially in an educational setting. Pressure tapping small aerofoils can also be difficult, especially if the models are rapid prototyped (RP). Low model surface resolution (from RP manufacture) and confined geometry complicate model assembly and finishing. Boundary-layer transition caused by poorly implemented tappings (too large a diametre or poorly aligned, i.e. straight aft) can also alter results. Wall pressure tappings may also be used and have the benefit of being non-intrusive. To implement, the test section roof and floor is tapped with a streamwise row of ports that facilitate measurement of the wall pressure signature. Integration of the pressure differential then relates to the lift produced. This measurement methodology still requires a multi-channel pressure acquisition system and modification of the wind tunnel. In Refs 4,5 methods are presented that facilitate calculation of the instantaneous forces acting on a body through flow field measurements determined using particle image velocimetry. However, the required flow field measurements encompass those surrounding the body, and are not a simple point measurement. In Ref. 6 a method is presented to estimate the lift of an aerofoil using two Pitot-static tubes that are used to measure the velocity above and below the aerofoil’s quarter chord. Wall corrections are required to yield an accurate lift estimate.

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23

Lowson, Martin V. "Visualization measurements of vortex flows." Journal of Aircraft 28, no. 5 (May 1991): 320–27. http://dx.doi.org/10.2514/3.46030.

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Brooks, Thomas F., Michael A. Marcolini, and Dennis S. Pope. "Airfoil trailing-edge flow measurements." AIAA Journal 24, no. 8 (August 1986): 1245–51. http://dx.doi.org/10.2514/3.9426.

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Alahyari, Abbas A., and Ellen K. Longmire. "Concentration Measurements in Experimental Microbursts." AIAA Journal 35, no. 3 (March 1997): 569–71. http://dx.doi.org/10.2514/2.136.

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Dianat, M., and I. P. Castro. "Measurements in separating boundary layers." AIAA Journal 27, no. 6 (June 1989): 719–24. http://dx.doi.org/10.2514/3.10171.

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Zimmerman, D. C., S. W. Smith, H. M. Kim, and T. J. Bartkowicz. "An Experimental Study of Structural Health Monitoring Using Incomplete Measurements." Journal of Vibration and Acoustics 118, no. 4 (October 1, 1996): 543–50. http://dx.doi.org/10.1115/1.2888333.

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In this paper, algorithmic approaches to enhance structural health monitoring capability when faced with incomplete measurements are addressed. The incomplete measurement problem has two aspects: (i) experimental measurement of a lesser number of modes of vibration than that of the analytical model and (ii) experimental measurement of a lesser number of degrees of freedom than that of the analytical model. Studies comparing model reduction, eigenvector expansion, and a hybrid model reduction/eigenvector expansion to address the second contribution are performed using experimental data. These approaches to the incomplete measurement problem are evaluated within the frameworks of multiple-constraint matrix adjustment (both sparsity and nonsparsity preserving algorithms) and minimum rank perturbation theory, which are both applicable for model refinement as well as damage location. Experimental evaluation of the proposed approaches utilize data from the NASA Langley Research Center 8-bay truss and McDonnell Douglas Aerospace 10-bay truss facilities.

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Pongsakornsathien, Nichakorn, Yixiang Lim, Alessandro Gardi, Samuel Hilton, Lars Planke, Roberto Sabatini, Trevor Kistan, and Neta Ezer. "Sensor Networks for Aerospace Human-Machine Systems." Sensors 19, no. 16 (August 8, 2019): 3465. http://dx.doi.org/10.3390/s19163465.

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Intelligent automation and trusted autonomy are being introduced in aerospace cyber-physical systems to support diverse tasks including data processing, decision-making, information sharing and mission execution. Due to the increasing level of integration/collaboration between humans and automation in these tasks, the operational performance of closed-loop human-machine systems can be enhanced when the machine monitors the operator’s cognitive states and adapts to them in order to maximise the effectiveness of the Human-Machine Interfaces and Interactions (HMI2). Technological developments have led to neurophysiological observations becoming a reliable methodology to evaluate the human operator’s states using a variety of wearable and remote sensors. The adoption of sensor networks can be seen as an evolution of this approach, as there are notable advantages if these sensors collect and exchange data in real-time, while their operation is controlled remotely and synchronised. This paper discusses recent advances in sensor networks for aerospace cyber-physical systems, focusing on Cognitive HMI2 (CHMI2) implementations. The key neurophysiological measurements used in this context and their relationship with the operator’s cognitive states are discussed. Suitable data analysis techniques based on machine learning and statistical inference are also presented, as these techniques allow processing both neurophysiological and operational data to obtain accurate cognitive state estimations. Lastly, to support the development of sensor networks for CHMI2 applications, the paper addresses the performance characterisation of various state-of-the-art sensors and the propagation of measurement uncertainties through a machine learning-based inference engine. Results show that a proper sensor selection and integration can support the implementation of effective human-machine systems for various challenging aerospace applications, including Air Traffic Management (ATM), commercial airliner Single-Pilot Operations (SIPO), one-to-many Unmanned Aircraft Systems (UAS), and space operations management.

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Meyers, J. F., and L. Scott Miller. "Assessing the Capability of Doppler Global Velocimetry to Measure Vortical Flow Fields." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 208, no. 2 (July 1994): 99–105. http://dx.doi.org/10.1243/pime_proc_1994_208_259_02.

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A new non-intrusive flow diagnostics instrumentation system, Doppler global velocimetry, is presented. The system is capable of making simultaneous three-component velocity measurements within a selected measurement plane at video camera rates. These velocity images can provide the researcher with spatial and temporal information about the flow field in a global sense. The investigation of a vortical flow above a 75° delta wing comparing standard three-component fringe-type laser velocimetry measurements with Doppler global velocimetry measurements is presented.

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Nisha, M. S., Dalbir Singh, J. Freesta Shiny, and B. Sasirekha. "Design and Manufacture of Nanofibers Using Electrospinning Technique for Aerospace Application." Applied Mechanics and Materials 852 (September 2016): 72–78. http://dx.doi.org/10.4028/www.scientific.net/amm.852.72.

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In this study, Polyvinylidene fluoride (PVDF) ultrafine fibers was fabricated by electro spinning equipment using rotating collector drum with different weight percentage of multi-walled carbon nanotube (MWCNT). The fabricated PVDF-MWCNT fiber has embedded to a glass fiber reinforced polymer (GFRP) for structural health monitoring of composite structures. GFRP is non-conductive material. However, by adding (or) embedding conductive PVDF-MWCNT nanocomposites, measuring its relative electrical resistance can be achieved. This study assesses the use of piezo resistive effect and conductivity of carbon nanotubes (CNT) for in-suit measurement of electrical resistance measurements and strain measurement of carbon fiber are correlated for sensing and damage monitoring purpose. The PVDF-MWCNT fiber and PVA-MWCNT fiber embedded in GFRP were evaluated and compared. Its first time PVDF-MWCNT fiber is used in composite material for sensing the damages; hence embedded sensor will downgrade the fatigue life of the composite structures usually, but in this investigation PVDF-MWCNT focus on not to downgrade the material’s mechanical properties. The manufactured specimens were subjected to various incremental loading and unloading tensile test. During mechanical loading and unloading processes the corresponding electrical resistance was monitored simultaneously, to assess the damage level in the structure.

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31

Pfeffer, P. E., M. Harrer, and J. Lin. "Vehicle dynamics measurements." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 222, no. 5 (May 2008): 801–13. http://dx.doi.org/10.1243/09544070jauto413.

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32

Cooper, Kevin R., Edzard Mercker, and Jürg Müller. "The necessity for boundary corrections in a standard practice for the open-jet wind tunnel testing of automobiles." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 231, no. 9 (April 26, 2017): 1245–73. http://dx.doi.org/10.1177/0954407017701287.

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This paper is intended to provide a summary of the necessary adjustments required for road-representative open-jet wind tunnel measurements on automobiles. The open-jet wind tunnel provides accurate measurements, but they are made in a finite-sized jet that differs from the unconfined open-road conditions. Furthermore, measurements on a given automobile made in different open-jet wind tunnels disagree with each other, and with measurements in closed-wall wind tunnels that were corrected for the influences of their solid boundaries. There appears to be reticence at some company levels to making ‘corrections’ to open-jet measurements. Perhaps non-specialist managers think that the need for a ‘correction’ means an erroneous measurement. It does not! Any high-quality wind tunnel measurement is accurate, but it needs to be ‘calibrated’ to on-road conditions through an appropriate set of procedures. Closed-wall wind tunnels measure higher drag coefficients, in comparison with those in an unconstrained on-road flow. Open-jet wind tunnels frequently measure a lower value. The closed-wall adjustments lower the drag coefficient to the unconstrained value. Open-jet adjustments should also adjust the drag coefficient to the same unconstrained value. This paper explores the range of effects from the finite jet and elucidates the effectiveness of a two-measurement correction procedure. It is shown that not every data point must be measured twice, only a small selected subset. Since approximately 20% of tunnel occupancy is in the fan-on condition, then the additional cost of correct accurate on-road-equivalent data is low.

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Sitompul, Peberlin Parulian, Timbul Manik, Mario Batubara, and Bambang Suhandi. "Radio Frequency Interference Measurements for a Radio Astronomy Observatory Site in Indonesia." Aerospace 8, no. 2 (February 17, 2021): 51. http://dx.doi.org/10.3390/aerospace8020051.

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We report on the measurements of radio frequency interference (RFI) at Mount Timau, Kupang, Indonesia, which is intended to host a future radio astronomy observatory. These measurements were taken twice in October 2020 and December 2020 to obtain the RFI environment, at frequencies between 70 and 7000 MHz. Due to the limitations of the measurement data, the results presented in this paper are based on peak detection rather than statistical analysis. Based on the measurement results, the frequency interval between 70–88 MHz and 120–150 MHz is relatively quiet, and the frequency range of 150–300 MHz is relatively clear. The frequency interval of 300 to 800 MHz is relatively quiet, except at the frequency of 600 MHz. The frequency range of 800–1400 MHz is also relatively quiet. The predominant terrestrial services in this band are at 840 MHz, with an amplitude around 32 dB, and 916 MHz, with an amplitude around 12 dB, and the global system for mobile (GSM) signals around 954 MHz have an amplitude around 20 dB above the noise floor. The frequency range of 1400–7000 MHz is also relatively quiet. In this band frequency, we can see RFI at 2145 and 2407 MHz, emitted by local Wi-Fi, and at 2683 MHz, with amplitudes of 18, 40 and 15 dB, respectively, from the noise level. We conclude that, for this period, the frequency band allocated for astronomy can possibly be used for radio telescope development.

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Send, Wolfgang. "Downstream vorticity measurements from ultrasonic pulses." Journal of Aircraft 25, no. 11 (November 1988): 993–94. http://dx.doi.org/10.2514/3.45693.

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Baumann, M. J., and R. J. Kind. "Aerodynamic Measurements of Regular Depression Roughness." AIAA Journal 39, no. 1 (January 2001): 37–40. http://dx.doi.org/10.2514/2.1299.

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Lima Filho, Geraldo Mulato de, Robert Cardoso Fernandes de Almeida, Ruy Morgado de Castro, and Alvaro José Damião. "Operational Measurements for Infrared Camera Characterization." Journal of Aerospace Technology and Management 9, no. 4 (October 19, 2017): 519–28. http://dx.doi.org/10.5028/jatm.v9i4.589.

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37

Kuttenkeuler, Jakob. "Optical Measurements of Flutter Mode Shapes." Journal of Aircraft 37, no. 5 (September 2000): 846–49. http://dx.doi.org/10.2514/2.2679.

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38

Storkmann, V., H. Olivier, and H. Gronig. "Force Measurements in Hypersonic Impulse Facilities." AIAA Journal 36, no. 3 (March 1998): 342–48. http://dx.doi.org/10.2514/2.402.

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39

Chua, L. P., Y. F. Li, and T. Zhou. "Measurements of a Heated Square Jet." AIAA Journal 42, no. 3 (March 2004): 578–88. http://dx.doi.org/10.2514/1.9111.

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40

Oshima, H., and B. R. Ramaprian. "Velocity Measurements over a Pitching Airfoil." AIAA Journal 35, no. 1 (January 1997): 119–26. http://dx.doi.org/10.2514/2.71.

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41

Gilbert, Barry. "Turbulence measurements in a radial upwash." AIAA Journal 27, no. 1 (January 1989): 44–51. http://dx.doi.org/10.2514/3.10092.

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42

Méheut, M., and D. Bailly. "Drag-Breakdown Methods from Wake Measurements." AIAA Journal 46, no. 4 (April 2008): 847–62. http://dx.doi.org/10.2514/1.29051.

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43

Büchner, S., A. Lieseberg, and J. Maul. "Density measurements in ballistic re-entry." Aerospace Science and Technology 1, no. 2 (February 1997): 137–49. http://dx.doi.org/10.1016/s1270-9638(97)90043-2.

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44

Salyer, Terry Ray, and Steven H. Collicott. "Multiple-source schlieren noise reduction measurements." AIAA Journal 34, no. 11 (November 1996): 2444–46. http://dx.doi.org/10.2514/3.13420.

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45

Morio, Jérôme, and Florent Muller. "Spatial object classification by radar measurements." Aerospace Science and Technology 14, no. 4 (June 2010): 259–65. http://dx.doi.org/10.1016/j.ast.2010.01.008.

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46

Popowski, Stanisław, and Witold Dąbrowski. "MEASUREMENT AND ESTIMATION OF THE ANGLE OF ATTACK AND THE ANGLE OF SIDESLIP." Aviation 19, no. 1 (March 30, 2015): 19–24. http://dx.doi.org/10.3846/16487788.2015.1015293.

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The paper presents issues concerning the estimation of the angle of attack and the angle of sideslip on a flying object board. Angle of attack and sideslip estimation methods which are based on measurements of linear velocity components of an object with the Earth’s coordinates and on attitude angles of the object are presented. Both of these measurements originate from the inertial navigation system, and velocity measurement is obtained from the satellite navigation system. The idea of applying inertial and satellite navigation for the estimation of attack and sideslip angles is presented. Practical comparison of these estimation methods has been conducted based on logged parameters of a flight onboard a Mewa aircraft. Development proposals for these methods are presented as well.

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47

Aimasso, A., M. D. L. Dalla Vedova, P. Maggiore, and G. Quattrocchi. "Study of FBG-based optical sensors for thermal measurements in aerospace applications." Journal of Physics: Conference Series 2293, no. 1 (June 1, 2022): 012006. http://dx.doi.org/10.1088/1742-6596/2293/1/012006.

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Abstract Optical fibers have revolutionized several technological sectors in recent decades, above all that of communication, and have also found many applications in the medical, lighting engineering, and infrastructural fields. In the aerospace field, many studies investigated the adoption of fiber optics considering the planned transition from fly-by-wire to fly-by-light flight controls. A significant feature of optical fiber is its ability to be used not only as a transmission medium but also as a basis for fiber-embedded sensors; one of the most prominent types is based on Bragg gratings (FBGs). FBGs can replace several traditional sensors, providing measures of temperature, vibrations, and mechanical deformation. Optical sensors provide many advantages over traditional, electrical-based sensors, including EMI insensitivity, ease of multiplexing on a single line, resilience to harsh environments, very compact sizes and global weight saving. Furthermore, punctual knowledge of the temperature field is essential to perform the thermal compensation of the optical sensors used for strain measurements. In this work, the authors analyzed the performance of thermal sensors based on FBGs to verify their stability, accuracy, and sensitivity to operating conditions. Two different methods of FBGs surface application have been considered (gluing with pre-tensioning vs. non-tensioned bonding). The results were then compared to those acquired using typical temperature sensors to determine the relationship between the observed temperature and the Bragg wavelength variation (i.e. the proportionality coefficient Kt). The effects on the proportionality coefficient Kt, arising from fiber pre-tensioning and thermal expansion of the structural support, were then evaluated by comparing the results obtained with the two bonding approaches.

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Andrianopoulos, N. P., S. K. Kourkoulis, and S. Saragas. "COD measurements and optimum exploitation of metal matrix composites for aerospace applications." Engineering Fracture Mechanics 57, no. 5 (July 1997): 565–76. http://dx.doi.org/10.1016/s0013-7944(97)00049-0.

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Loutas, T. H., A. Panopoulou, D. Roulias, and V. Kostopoulos. "Intelligent health monitoring of aerospace composite structures based on dynamic strain measurements." Expert Systems with Applications 39, no. 9 (July 2012): 8412–22. http://dx.doi.org/10.1016/j.eswa.2012.01.179.

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50

Carl, M., T. Behrendt, C. Fleing, M. Frodermann, J. Heinze, C. Hassa, U. Meier, D. Wolff-Gassmann, S. Hohmann, and N. Zarzalis. "Experimental and Numerical Investigation of a Planar Combustor Sector at Realistic Operating Conditions." Journal of Engineering for Gas Turbines and Power 123, no. 4 (October 1, 2000): 810–16. http://dx.doi.org/10.1115/1.1378298.

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Results of an ongoing collaboration between the engine manufacturer MTU and the German aerospace research center DLR on the NOx reduction potential of conventional combustors are reported. A program comprising optical sector combustor measurements at 1, 6, and 15 bars and CFD calculations is carried out. The aims are to gather information in the combustor at realistic operating conditions, to understand the differences between the sector flow field and data from tubular combustors, to verify the used CFD, and to discover the benefits and limitations of the applied optical diagnostics. Selected results of measurements and calculations of the isothermal flow and of measurements at 6 bars and 700 K at a rich-lean and overall lean AFR are reported. The used measurement techniques were LDA, PDA, Mie scattering on kerosene, quantitative light scattering, OH* chemiluminescence, and LIF on OH. The measurements were able to confirm the intended quick and homogeneous mixing of the three staggered rows of secondary air jets.

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