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The method planned for the surface figure error measurement of the AMSDs at the XRCF will be discussed. Alignment, surface figure measurement, gravity effects, vibration & temperature environment effects, total error analysis, and data output will be discussed.
Radiosonde measurement errors occur for various reasons: calibration, mishandling of sensors, poor software, radiation, etc. It is important that these errors be found and corrected, or at the least, corrections determined that might be sensibly applied. Radiation errors apparently are the most serious since the lack of radiative equilibrium between the thermistor and its surrounding environment can not be corrected for just a single thermistor without serious intervention. However, errors may be determined using the Accurate Temperature Measuring (ATM) radiosonde. The ATM radiosonde development was initiated in the mid-1980's using three thermistors; five thermistors are presently incorporated in the ATM radiosonde. Test flights at different locations indicated that the radiative effect on the thermistor varies because of the different environment of each location and, can be corrected. When comparisons between different thermistors (radiosondes) are required the ATM is a valuable tool. Investigation of relative humidity measurements is an ongoing issue because of large discrepancies in observed data. The first chilled mirror (SNOW WHITE) radiosonde was flown from Wallops Flight Facility in 1997. Tests and analyses show the chilled mirror radiosonde present very acceptable data up to the altitude of the tropopause and in some measurements, to 100 hPA. Improvement and better interpretation of the measurements are important. Discussion concentrates on new aspects of the ATM radiosonde application and the utility of the chilled mirror radiosonde.
A technique using small, enriched uranium-aluminum alloy monitors to measure fission rates in fuel plate assembly reactors was developed at the Idaho National Laboratory Radiation Measurements Laboratory in support of Advanced Test Reactor Critical (ATR-C) Facility irradiations. Previous measurements were performed to determine the correlation between the beta-particle activity and the fission rate in the U-Al monitors following irradiation. The American Society for Testing and Materials (ASTM) has established a standard practice E704 for determining neutron fluence rate by radioactivation of depleted uranium by measuring the concentration of fission-products in irradiated uranium monitors. Rather than measuring the beta-particle decay from fission-products, the decay rate of fission-products is determined by gamma-ray spectroscopy. The feasibility of using a method adapted from the ASTM standard practice E704 was investigated for ATR-C irradiations and compared to the present method by analyzing a subset of 21 monitor wires using both methods. The resulting calculated fission rates agreed with an average standard deviation of 7.45%, within the average combined measurement error of 9.05%. Practical considerations such as expected fluence-rates, sample activity, and counting-time were compared between the two methods and the sources of error for each method were investigated. Quality assurance measurements utilizing the modified ASTM standard method are recommended for future test irradiation, but gross-beta-particle counting remains the most practical solution for ATR-C fluence-rate determination.
A ground-based astronomical telescope with a segmented primary mirror will suffer image-degrading wavefront aberrations from at least two sources: (1) atmospheric turbulence and (2) segment misalignment or figure errors of the mirror itself. This paper describes the derivation of a mirror control feedback matrix that assumes the presence of both types of aberration and is optimum in the sense that it minimizes the mean-squared residual wavefront error. Assumptions of the statistical nature of the wavefront measurement errors, atmospheric phase aberrations, and segment misalignment errors are made in the process of derivation. Examples of the degree of correlation are presented for three different types of wavefront measurement data and compared to results of simple corrections.
Hydrological parameters are scale dependent. Efficient monitoring techniques capable of measuring hydrological parameters, such as soil moisture content (θ), over a wide range of spatial scales are essential for understanding the complexity of water and energy movement across the landscape. Techniques to measure θ over spatial scales in the range from centimeters to thousands of meters, however, are sorely lacking. Recent improvements in the distributed temperature sensing (DTS) technology supported the development of novel techniques to fill that gap. However, improvements in the accuracy and applicability of DTS techniques are still needed. This study investigates the possibility of improving the accuracy of the fiber optics dual-probe heat-pulse (FO-DPHP) DTS technique by using a new design to maintain the spacing between the FO-DPHP probes and by introducing a novel data interpretation approach. The accuracy of the novel FO-DPHP design was tested at different θ in a sand column experiment. The FO-DPHP measurements obtained using traditional and novel data interpretation approaches were compared against independent measurements from several calibrated soil water content (EC5) sensors. Monte-Carlo analyses were also performed to assess the impact of DTS measurement errors on the accuracy achieved using the data interpretation approaches. The novel design and data interpretation approach allowed for accurate measurements of soil thermal properties and θ without the need to perform a hard-to-achieve soil-specific calibration. Measured θ had mean errors and standard deviations <0.03 and <0.01 m 3 m -3 , respectively, for moisture conditions ranging from dry to near saturation. The standard deviation in the measured heat capacity was <0.01 MJ m -3 K -1 .
Precision measurement of synchronization error in tracking station clocks, to obtain selenodetic data on Lunar Orbiter mission
Objective: GeoCarb validation •Purpose: •Do the four TCCON sites in the GeoCarb domain characterize satellite validation? •Method: •Assess the error estimates globally vs. in the GeoCarb domain •Assess the use of GML/DOE aircraft for CH4 validation •Systematic error estimate (from Kulawik, 2016): •+ regional bias (stdevof average bias versus validation at each station) •+ correlated error (stdev of daily average versus validation) •-co-location error (above quantities for model@satelliteminus model@valid) •-validation error (systematic error of validation estimates, e.g. model extension) Aircraft validation error •CH4 profile extension error estimate: 7 ppb •Extend aircraft observations to the top of the atmosphere with different model configurations •CAMS, scaling to stratosphere, then taking stratosphere •Extend by repeating top aircraft value to the troposphere, then taking CAMS •Extend with GEOS-Chem run (from 2010). •Difference CAMS-Scale vs. CAMS-Tropo: •3.6 +-5.5 ppb •Systematic error: 6.6 ppb •Extending aircraft to tropopause is blatantly wrong, but these two have the same stratosphere. •Difference CAMS-Scale vs. GEOS-Scale: •6.2 +-8.7 ppb •Do not consider bias since model is 10 years off. Systematic error ~8.7 ppb. •Estimate of systematic error from profile extension (possibly underestimated, resulting in possibly higher TROPOMI error estimate) •7 ppb •Would likely vary some by season, site, other conditions •Aircraft measurement error: 1 ppb •1 ppb from measurement error3
SUMMARY An underground nuclear explosion (UNE) couples mechanical energy into crustal rock, which propagates as seismic and acoustic waves. These different physical phenomena transport, by different pathways, to standoff detectors at varying distances. The transport pathways attenuate the original signal but in different ways. Enabled by correct statistical weighting, signal attenuation models can be used to combine these disparate sensor data to estimate the yield of an UNE. Contemporaneous statistical models, used in yield estimation, can be improved with an advanced partition of error for these physical signal propagation models. We present an advanced multivariate approach to error modelling of multiphenomenology physical signatures. In addition to measurement error, our error model represents physical model biases as random with a physics-based covariance structure. To illustrate this proposed framework, we demonstrate the estimation of explosion yield using openly available seismic and acoustic data from chemical single-point explosions.
An investigation of the Shuttle Reaction Control System (RCS) propellant gaging module has revealed that the gaging errors due to the combined effects of random instrumentation measurement errors and propellant loading uncertainties are non-linear over the range of the propellant quantity gage (0-100%), with the largest error occurring at the zero point. When the RCS propellant tanks are filled to contain 100% of the maximum usable propellant, the largest gaging error was determined to be 3.9% for the fuel and 5.4% for the oxidizer. When the RCS propellant tanks initially contain 50% of the maximum usable propellant, the largest gaging error increases to 4.0% for the fuel and 5.6% for the oxidizer.
An investigation of the shuttle orbital maneuvering system (OMS) pressure-volume-temperature (P-V-T) propellant gaging module has revealed that the gaging errors due to the combined effects of random instrumentation measurement errors, propellant loading uncertainties, and simplifying assumptions in the software are non-linear over the range of the usable propellant quantity gage (0-100%), with the largest error being at the zero point. When the OMS propellant tanks in the orbiter vehicle pods are filled to contain 100% of the maximum usable propellant, the gaging error at the zero point was determined to be 9.5% for the fuel and 9.5% for the oxidizer. When the OMS propellant tanks initially contain 50% of the maximum usable propellant, the largest gaging error is still 9.5% for the fuel and 9.5% for the oxidizer.
A more accurate algorithm was developed to compute thermal inertia from temperature difference and albedo information. The error of this algorithm is about 1/3 of the measurement error in HCMM as opposed to the current algorithm which can have an error 5 times larger. A northeast trending lineament was discovered in southwestern Arizona on enhanced thermal inertia images.
Windowing of design space is considered in order to reduce the bias errors due to low-order polynomial response surfaces (RS). Standard design space windowing (DSW) uses a region of interest by setting a requirement on response level and checks it by a global RS predictions over the design space. This approach, however, is vulnerable since RS modeling errors may lead to the wrong region to zoom on. The approach is modified by introducing an eigenvalue error measure based on point-to-point mean squared error criterion. Two examples are presented to demonstrate the benefit of the error-based DSW.
The Orion Crew Exploration Vehicle (CEV) will replace the Space Shuttle and serve as the next-generation spaceship to carry humans back to the Moon for the first time since the Apollo program. For nominal lunar mission operations, the Mission Control Navigation team will utilize radiometric measurements to determine the position and velocity of Orion and uplink state information to support Lunar return. However, in the loss of communications contingency return scenario, Orion must safely return the crew to the Earth's surface. The navigation design solution for this loss of communications scenario is optical navigation consisting of lunar landmark tracking in low lunar orbit and star- horizon angular measurements coupled with apparent planetary diameter for Earth return trajectories. This paper describes the optical measurement errors and the navigation filter that will process those measurements to support navigation for safe crew return.
General-case equations for application to mismatch errors in Y-factor measurements for calibration of receiver - radio frequency technique for noise temperature measurement errors
Regression analysis of tracking system measurement errors on Apollo/Saturn 1B flight tests
Measurement errors in ionospheric local electron concentration determination from Doppler dispersion measurements by satellite radio beacons
Technique for measuring instantaneous angular deflection of object requires no physical contact. Technique utilizes two flat refractors, converging lens, and different photocell. Distinction of method is its combination of optical and electromechanical components into feedback system in which measurement error is made to approach zero. Application is foreseen in measurement of torsional strain.