Relevant bibliographies by topics / Aerospace measurements

Academic literature on the topic 'Aerospace measurements'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Aerospace measurements"

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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): 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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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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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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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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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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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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Dissertations / Theses on the topic "Aerospace measurements"

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Husen, Nicholas M. "Skin Friction Measurements Using Luminescent Oil Films." Thesis, Purdue University, 2017. http://pqdtopen.proquest.com/#viewpdf?dispub=10277794.

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As aircraft are designed to a greater extent on computers, the need for accurate and fast CFD algorithms has never been greater. The development of CFD algorithms requires experimental data against which CFD output can be validated and from which insight about flow physics can be acquired. Skin friction, in particular, is an important quantity to predict with CFD, and experimental skin friction data sets aid not only with the validation of the CFD predictions, but also in tuning the CFD models to predict specific flow fields. However, a practical experimental technique for collecting spatially and temporally resolved skin friction data on complex models does not yet exist. This dissertation develops and demonstrates a new luminescent oil film skin friction meter which can produce spatially-resolved quantitative steady and unsteady skin friction data on models with complex curvature.

The skin friction acting on the surface of a thin film of oil can be approximated by the expression τw =μ ouh/h, where μ o is the dynamic viscosity of the oil, uh is the velocity of the surface of the oil film, and h is the thickness of the oil film. The new skin friction meter determines skin friction by measuring h and uh. The oil film thickness h is determined by ratioing the intensity of the fluorescent emissions from the oil film with the intensity of the incident light which is scattered from the surface of the model. When properly calibrated, that ratio provides an absolute oil film thickness value. This oil film thickness meter is therefore referred as the Ratioed-Image Film-Thickness (RIFT) Meter. The oil film velocity uh is determined by monitoring the evolution of tagged molecules within the oil film: Photochromic molecules are dissolved into the fluorescent oil and a pattern is written into the oil film using an ultraviolet laser. The evolution of the pattern is recorded, and standard cross-correlation techniques are applied to the resulting sequence of images. This newly developed skin friction meter is therefore called the Luminescent Oil Film Flow-Tagging skin friction meter, or the LOFFT skin friction meter. The LOFFT skin friction meter is demonstrated by collecting time-averaged skin friction measurements on NASA's FAITH model and by collecting unsteady skin friction measurements with a frequency response of 600Hz. Higher frequency response is possible and is dependent on the experimental setup.

This dissertation also contributes to the work done on the Global Luminescent Oil Film Skin Friction Meter (GLOFSFM) by noting that the technique could be influenced by ripples at the oil-air interface. An experiment studying the evolution of ripples at the oil-air interface was conducted to determine under what oil film conditions the GLOFSFM can be appropriately applied. The RIFT meter was crucial for this experiment, as it facilitated quantitative distributed oil film thickness measurements during the wind-tunnel run. The resulting data set is rich in content, permitting the computation of mean wavelengths, peak-to-trough ripple heights, wave speeds, and mean thicknesses. In addition to determining under what oil film conditions the GLOFSFM may be applied, this experiment directly determined the oil film conditions under which the velocity of the ripples may be used to proxy the velocity of the oil film surface. The RIFT meter and the ability to determine oil film surface velocity by monitoring ripple velocities admit yet another time-averaged skin friction meter, the Fluorescent-Oil Ripple-Velocity (FORV) skin friction meter. The FORV skin friction meter recovers skin friction as τ w = μovrip/H, where vrip is the velocity of the ripples, and H is the oil film thickness averaged over the thickness fluctuations due to the ripples. The FORV skin friction meter is demonstrated on NASA's FAITH model.

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Levedahl, Blaine Alexander. "Vehicle Control in Full Unsteady Flow Using Surface Measurements." NCSU, 2010. http://www.lib.ncsu.edu/theses/available/etd-02272010-190048/.

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This dissertation is the first comprehensive attempt to address a new engineering problem: control of a vehicle maneuvering in a full unsteady flow field. The approach to the solution is focused in three main areas: modeling of a vehicle in full unsteady flow, control of a vehicle in full unsteady flow, and synthesizing the fluid loads for use in control of a vehicle maneuvering in a full unsteady flow field. To model a vehicle maneuvering in a full unsteady flow field this dissertation develops the Coupled Fluid Vehicle (CFV) model in which the fluid, which is a sum of a finite number of spatially dependent velocity fields whose contributions vary with time, is coupled to the vehicle rigid-body equations of motion. To control a vehicle maneuvering in a full unsteady flow field this dissertation develops the Fluid Compensation Control (FCC) strategy which gives the designer an opportunity to include the fluid states, in addition to the vehicle states, in the control law and an opportunity to balance reducing the fluid dynamic load through compensation and reducing the state error through regulation. To synthesize the fluid loads this dissertation has attempted to forward current work on the prediction of fluid loads from stagnation and separation point measurements using the Kutta principle, which says that the velocity around a vehicle is a smoothly varying function and that it is determined up to a multiplicative constant by its nodes (stagnation, separation, and reattachment points/lines), and by conducting an experiment to attempt to determine the correlation of the fluidic loads from the orientation and separation lines on a 3-dimensional bluff body.
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Johnson, Peder. "Dua-beam digital speckle photography : strain field measurements in aerospace applications." Licentiate thesis, Luleå tekniska universitet, 1998. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-26085.

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Price, Jennifer Lou. "Unsteady Measurements and Computations on an Oscillating Airfoil with Gurney Flaps." NCSU, 2001. http://www.lib.ncsu.edu/theses/available/etd-20010713-170959.

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Price, Jennifer Lou. Unsteady Measurements and Computations on an Oscillating Airfoil with Gurney Flaps. (Under the direction of Dr. Ndaona Chokani)The effect of a Gurney flap on an unsteady airfoil flow is experimentally and computationally examined. In the experiment, the details of the unsteady boundary layer events on the forward portion of the airfoil are measured. In the computation, the features of the global unsteady flow are documented and correlated with the experimental observations.The experiments were conducted in the North Carolina State University subsonic wind tunnel on an oscillating airfoil at pitch rates of 65.45 degrees/sec and 130.9 degrees/sec. The airfoil has a NACA0012 cross-section and is equipped with a 1.5% or 2.5% chord Gurney flap. The airfoil is tested at Reynolds numbers of 96,000, 169,000 and 192,000 for attached and light dynamic stall conditions. An array of surface-mounted hot-film sensors on the forward 25% chord of the airfoil is used to measure the unsteady laminar boundary layer separation, transition-to-turbulence, and turbulent reattachment. In parallel with the experiments incompressible Navier-Stokes computations are conducted for the light dynamic stall conditions on the airfoil with a 2.5%c Gurney flap at a Reynolds number of 169,000.The experimental measurements show that the effect of the Gurney flap is to move the separation, transition and reattachment forward on the airfoil. This effect is more marked during the airfoil's pitch-down than during pitch-up. The computational results verify these observations, and also show that the shedding of the dynamic stall vortex is delayed. Thus the adverse effects of dynamic stall are mitigated by the Gurney flap.

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Jones, Warren Anthony. "CONTROL OF DIFFUSING DUCT FLOWUSING ACTIVE VORTEX GENERATORSWITH HOT-FILM SENSOR MEASUREMENTS." NCSU, 2001. http://www.lib.ncsu.edu/theses/available/etd-20010528-224402.

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Experiments have been conducted using vane-type vortex generators to control flow separation and exit flow distortion in a diffusing duct. The primary purpose is to examine the feasibility of using surface-mounted hot-film sensors to determine the extent of exit flow distortion. The experimental set-up consists of a two-dimensional blow down type wind tunnel with a variable diffuser exit. One diffuser wall is curved to produce a Stratford-like pressure gradient. The wall's placement is adjustable such that the adverse pressure gradient can be adjusted to promote separation. An active vortex generator array that can be placed at three streamwise locations is used to reduce the extent of flow separation and exit distortion.Diffuser surface pressure and exit total pressure measurements are obtained and compared to the hot-film data. The time-averaged mean and rms voltages from the hot-film data are used as indicators of flow separation and exit flow distortion.Results show that, with the use of the vortex generators, high mean voltages and low levels of rms voltage correlate well with improved pressure recovery. Conversely, poorer pressure recovery is associated with lower mean voltages and higher rms values compared to the baseline cases. Increased total pressures at the diffuser exit are accompanied by increases in hot-film mean voltages. These indicate higher shear stresses, which also correspond to increased flow uniformity. Lower variations in the rms voltages compared to the baseline cases also correlated well with improved total pressures at the diffuser exit.

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Tedder, Sarah Augusta. "Advancements in dual-pump broadband CARS for supersonic combustion measurements." W&M ScholarWorks, 2010. https://scholarworks.wm.edu/etd/1539623572.

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Space- and time-resolved measurements of temperature and species mole fractions of nitrogen, oxygen, and hydrogen were obtained with a dual-pump coherent anti-Stokes Raman spectroscopy (CARS) system in hydrogen-fueled supersonic combustion free jet flows. These measurements were taken to provide time-resolved fluid properties of turbulent supersonic combustion for use in the creation and verification of computational fluid dynamic (CFD) models. CFD models of turbulent supersonic combustion flow currently facilitate the design of air- breathing supersonic combustion ramjet (scramjet) engines. Measurements were made in supersonic axi-symmetric free jets of two scales. First, the measurement system was tested in a laboratory environment using a laboratory-scale burner (∼10 mm at nozzle exit). The flow structures of the laboratory-burner were too small to be resolved with the CARS measurements volume, but the composition and temperature of the jet allowed the performance of the system to be evaluated. Subsequently, the system was tested in a burner that was approximately 6 times larger, whose length scales are better resolved by the CARS measurement volume. During both these measurements, weaknesses of the CARS system, such as sensitivity to vibrations and beam steering and inability to measure temperature or species concentrations in hydrogen fuel injection regions were identified. Solutions were then implemented in improved CARS systems. One of these improved systems is a dual-pump broadband CARS technique called, Width Increased Dual-pump Enhanced CARS (WIDECARS). The two lowest rotational energy levels of hydrogen detectable by WIDECARS are H2 S(3) and H2 S(4). The detection of these lines gives the system the capability to measure temperature and species concentrations in regions of the flow containing pure hydrogen fuel at room temperature. WIDECARS is also designed for measurements of all the major species (except water) in supersonic combustion flows fueled with hydrogen and hydrogen/ethylene mixtures (N2, O 2, H2, C2H4, CO, and CO2). This instrument can characterize supersonic combustion fueled with surrogate fuel mixtures of hydrogen and ethylene. This information can lead to a better understanding of the chemistry and performance of supersonic combustion fueled with cracked jet propulsion (JP)-type fuel.
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Pool, Kirby Vinton. "Product/process improvement through performance measurements and modeling : a case study in aerospace welding." Thesis, Massachusetts Institute of Technology, 1991. http://hdl.handle.net/1721.1/13376.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Materials Science and Engineering, and Sloan School of Management, 1991.
Includes bibliographical references (leaves 135-136).
by Kirby Vinton Pool.
M.S.
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Bifano, Michael F. P. "Theory and Measurements of Thermal Properties in Nanowires and Carbon Nanotubes." Case Western Reserve University School of Graduate Studies / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=case1339998535.

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Brewer, David A. "Plume Contamination Measurements of an Additively-Printed GOX/ABS Hybrid Thruster." DigitalCommons@USU, 2018. https://digitalcommons.usu.edu/etd/7072.

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This thesis examines the impact of the physical contamination on optical surfaces of spacecraft by an ABS/GOX thruster. Plume contamination presents a significant operational hazard for spacecraft solar arrays and thermal control surfaces can lead to decreased power production and increased spacecraft temperatures. Historically, due to the lack of a reliable, on-demand, and multiple-use ignition methodology, hybrid rockets have never been previously considered for in-space propulsion. Recent advancements in hybrid rocket technologies, have made hybrid systems feasible for in space propulsion. However, prior to this study no research had ever been performed with regard to plume contamination effects due to hybrid rockets. This paper presents the results from a set of preliminary plume contamination measurements on a prototype small spacecraft hybrid rocket system, collected under both ambient and vacuum chamber conditions.
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Barone, Dominic L. "Investigation of TDLAS Measurements in a Scramjet Engine." University of Cincinnati / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1277130335.

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Books on the topic "Aerospace measurements"

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Ehernberger, L. J. Stratospheric turbulence measurements and models for aerospace plane design. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1992.

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Visentine, James T. Material interactions with the low earth orbital environment: Accurate reaction rate measurements. New York: AIAA, 1986.

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Visentine, James T. Atomic oxygen effects measurements for shuttle missions STS-8 and 41-G. Washington, D. C: Lyndon B. Johnson Space Center, 1988.

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Rogers, Melissa J. B. Summary report of mission acceleration measurements for STS-73, launched October 20, 1995. [Washington, DC]: National Aeronautics and Space Administration, 1996.

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Shen kong ce kong wu xian dian ce liang ji shu: Radiometric measuring techniques for deep space navigation. Beijing Shi: Guo fang gong ye chu ban she, 2012.

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Benton, E. V. Environmental radiation measurements on MIR station: Program 1--internal experiment, program 2--external experiment : year 2 progress report, contract no. NCC2-893. [Washington, DC: National Aeronautics and Space Administration, 1997.

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Rogers, Melissa J. B. Summary report of mission acceleration measurements for STS-60, SPACEHAB-2 launched February 11, 1994. Cleveland, Ohio: NASA Lewis Research Center, 1994.

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Noyes, Gerold. Performance measurements and energy balance of an SPS V160 Stirling motor at the German Aerospace Research Establishment. Köln: Deutsche Forschungsanstalt für Luft- und Raumfahrt, 1990.

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International Congress on Instrumentation in Aerospace Simulation Facilities (19th 2001 Cleveland, Ohio). ICIASF '01: 19th International Congress on Instrumentation in Aerospace Simulation Facilities, Leveraging resources through collaboration, 22800 Cedar Point Road, Cleveland, Ohio 44142, August 27-30, 2001. Piscataway, N.J: IEEE Service Center, 2001.

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Shen kong ce kong tong xin xi tong gong cheng yu ji shu: Engineering and Technology of Deep Space TT&C System. Beijing Shi: Ke xue chu ban she, 2013.

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Book chapters on the topic "Aerospace measurements"

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Boden, Fritz, Thomas Wolf, Claudio Lanari, and Anwar Torres. "IPCT Ground Vibration Measurements on a Small Aircraft." In Research Topics in Aerospace, 33–55. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-34738-2_4.

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Kindler, Kolja, Karen Mulleners, and Markus Raffel. "Towards In-Flight Measurements of Helicopter Blade Tip Vortices." In Research Topics in Aerospace, 171–85. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-34738-2_11.

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Boden, Fritz, Henk Jentink, and Christian Petit. "IPCT Wing Deformation Measurements on a Large Transport Aircraft." In Research Topics in Aerospace, 93–115. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-34738-2_7.

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Boden, Fritz, Claudio Lanari, Anwar Torres, and Thorsten Weikert. "In-Flight IPCT Wing Deformation Measurements on a Small Aircraft." In Research Topics in Aerospace, 57–72. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-34738-2_5.

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Ružička, Pavel, Jan Rýdel, Miroslav Josefik, and Fritz Boden. "Assessment of IPCT for Wing Deformation Measurements on Small Aircrafts." In Research Topics in Aerospace, 73–92. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-34738-2_6.

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Lanari, Claudio, Boleslaw Stasicki, Fritz Boden, and Anwar Torres. "Image Based Propeller Deformation Measurements on the Piaggio P 180." In Research Topics in Aerospace, 133–53. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-34738-2_9.

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Maucher, Christoph, and Fritz Boden. "Blade Deformation Measurements with IPCT on an EC 135 Helicopter Rotor." In Research Topics in Aerospace, 195–213. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-34738-2_13.

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Veerman, H. P. J., H. Kannemans, and H. W. Jentink. "Highly Accurate Aircraft In-Flight Wing Deformation Measurements Based on Image Correlation." In Research Topics in Aerospace, 15–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-34738-2_3.

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Beswick, John M. "Chapter 17 | Super-Precision Aerospace Bearing Steel Technologies." In Rolling Bearing Steel: Design, Technology, Testing and Measurements, 313–50. 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959: ASTM International, 2022. http://dx.doi.org/10.1520/mnl8320200019.

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Sanfedino, Francesco, Marco Scardino, Jérémie Chaix, and Stéphanie Lizy-Destrez. "CubeSat Attitude Estimation via AUKF Using Magnetometer Measurements and MRPs." In Advances in Aerospace Guidance, Navigation and Control, 343–61. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-17518-8_20.

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Conference papers on the topic "Aerospace measurements"

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Mercer, Carolyn R. "Optical measurements for intelligent aerospace propulsion." In Optical Science and Technology, SPIE's 48th Annual Meeting, edited by Patrick V. Farrell, Fu-Pen Chiang, Carolyn R. Mercer, and Gongxin Shen. SPIE, 2003. http://dx.doi.org/10.1117/12.509732.

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TIGHE, THOMAS, and RALPH SHIMOVETZ. "SARL noise measurements." In 28th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-285.

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Smith, Robert W., and Ted Corbin. "LOWTRAN 7 comparisons with field measurements." In Aerospace Sensing, edited by Dieter Clement and Wendell R. Watkins. SPIE, 1992. http://dx.doi.org/10.1117/12.137849.

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Nomura, Satoshi, Gen Ito, Kazuhisa Fujita, and Kimiya Komurasaki. "Translational Temperature Measurements in Shock Layer by Point-measurement Laser Absorption Spectroscopy." In 52nd Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-1409.

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Seichepine, Nicolas, Jerome Lacaille, and J. Ricordeau. "Data mining of flight measurements." In Infotech@Aerospace 2011. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-1530.

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Eichelberger, H., G. Fremuth, G. Prattes, Ch Kurbisch, G. Laky, F. Giner, S. Neukirchner, et al. "BepiColombo-MPO-SERENA-PICAM EMC measurements." In 2016 ESA Workshop on Aerospace EMC (Aerospace EMC). IEEE, 2016. http://dx.doi.org/10.1109/aeroemc.2016.7504548.

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Goebel, John H., Theodore T. Weber, Arthur D. Van Rheenen, Leon L. Jostad, Joo-Young Kim, and Ben Gable. "Cryogenic measurements of Aerojet GaAs n-JFETs." In Aerospace Sensing, edited by Eric R. Fossum. SPIE, 1992. http://dx.doi.org/10.1117/12.60499.

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Grant, Michael, Stephen Katzberg, and Roland Lawrence. "GPS Remote Sensing Measurements Using Aerosonde UAV." In Infotech@Aerospace. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-7005.

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NORTON, OLIN, R. KUMAR, and D. SRIKANTAIAH. "A direct comparison of cross-correlation velocity measurements with laser Doppler measurements." In 29th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-213.

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EHERNBERGER, L. "Stratospheric turbulence measurements and models for aerospace planedesign." In AlAA 4th International Aerospace Planes Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-5072.

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Reports on the topic "Aerospace measurements"

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Liou, K. N. Interpretation of Radiation Measurements from UAV. Final Report [Unmanned Aerospace Vehicles]. Office of Scientific and Technical Information (OSTI), July 2000. http://dx.doi.org/10.2172/763424.

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Calkins, Dale E., Richard S. Gaevert, Frederick J. Michel, and Karen J. Richter. Aerospace System Unified Life Cycle Engineering Producibility Measurement Issues. Fort Belvoir, VA: Defense Technical Information Center, May 1989. http://dx.doi.org/10.21236/ada210937.

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Catherine Gautier. Atmospheric radiation measurement - unmanned aerospace vehicle. Final technical report. Office of Scientific and Technical Information (OSTI), March 2000. http://dx.doi.org/10.2172/764576.

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Gautier, Catherine. Final Report: Atmospheric Radiation Measurement Unmanned Aerospace Vehicle, February 1, 1995 - January 31, 1999. Office of Scientific and Technical Information (OSTI), January 1999. http://dx.doi.org/10.2172/765148.

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Noguchi, R. Environmental effects on composite airframes: A study conducted for the ARM UAV Program (Atmospheric Radiation Measurement Unmanned Aerospace Vehicle). Office of Scientific and Technical Information (OSTI), June 1994. http://dx.doi.org/10.2172/10166660.

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Roye, Thorsten. Unsettled Technology Areas in Deterministic Assembly Approaches for Industry 4.0. SAE International, August 2021. http://dx.doi.org/10.4271/epr2021018.

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Increased production rates and cost reduction are affecting manufacturing in all sectors of the mobility industry. One enabling methodology that could achieve these goals in the burgeoning “Industry 4.0” environment is the deterministic assembly (DA) approach. The DA approach is defined as an optimized assembly process; it always forms the same final structure and has a strong link to design-for-assembly and design-for-automation methodologies. It also looks at the whole supply chain, enabling drastic savings at the original equipment manufacturer (OEM) level by reducing recurring costs and lead time. Within Industry 4.0, DA will be required mainly for the aerospace and the space industry, but serves as an interesting approach for other industries assembling large and/or complex components. In its entirety, the DA approach connects an entire supply chain—from part manufacturing at an elementary level to an OEM’s final assembly line level. Addressing the whole process of aircraft design and manufacturing is necessary to develop further collaboration models between OEMs and the supply chain, including addressing the most pressing technology challenges. Since all parts aggregate at the OEM level, the OEM—as an integrator of all these single parts—needs special end-to-end methodologies to drastically decrease cost and lead time. This holistic approach can be considered in part design as well (in the design-for-automation and design-for-assembly philosophy). This allows for quicker assembly at the OEM level, such as “part-to-part” or “hole-to-hole” approaches, versus traditional, classical assembly methods like manual measurement or measurement-assisted assembly. In addition, it can increase flexibility regarding rate changes in production (such as those due to pandemic- or climate-related environmental challenges). The standardization and harmonization of these areas would help all industries and designers to have a deterministic approach with an end-to-end concept. Simulations can easily compare possible production and assembly steps with different impacts on local and global tolerances. Global measurement feedback needs high-accuracy turnkey solutions, which are very costly and inflexible. The goal of standardization would be to use Industry 4.0 feedback and features, as well as to define several building blocks of the DA approach as a one-way assembly (also known as one-up assembly, or “OUA”), false one-way assembly, “Jig-as-Master,” etc., up to the hole-to-hole assembly approach. The evolution of these assembly principles and the link to simulation approaches are undefined and unsolved domains; they are discussed in this report. They must be discussed in greater depth with aims of (first) clarifying the scope of the industry-wide alignment needs and (second) prioritizing the issues requiring standardization. NOTE: SAE EDGE™ Research Reports are intended to identify and illuminate key issues in emerging, but still unsettled, technologies of interest to the mobility industry. The goal of SAE EDGE™ Research Reports is to stimulate discussion and work in the hope of promoting and speeding resolution of identified issues. SAE EDGE™ Research Reports are not intended to resolve the challenges they identify or close any topic to further scrutiny.
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