Rectification of a whole-sky photograph as a tool for determining spatial positioning of cumulus clouds
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Stucky, B. E.↗
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Results for “Position Determination”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Nondynamic Tracking Using The Global Positioning System
Report describes technique for using Global Positioning System (GPS) to determine position of low Earth orbiter without need for dynamic models. Differential observing strategy requires GPS receiver on user vehicle and network of six ground receivers. Computationally efficient technique delivers decimeter accuracy on orbits down to lowest altitudes. New technique nondynamic long-arc strategy having potential for accuracy of best dynamic techniques while retaining much of computational simplicity of geometric techniques.
Yunck, T. P.↗
Synthetic Estimation Filters For Determination Of Position
Concept of synthetic estimation filter (SEF) proposed to extend concept of matched filter from mere recognition of object to recognition of position and orientation relative to observing apparatus. Optical filter of this general type correlated with input image to obtain signal indicative of match between input and filter images.
Juday, Richard D.↗
Discovery of X-ray and Optical/Infrared Counterpart of XTE J1906+09
We present the Chandra localization of the transient X-ray source XTE J1906+09 and the discovery of optical and infrared counterparts. We analysed the archival Chandra ACIS-I observations of the region and determined the precise source position, that is 8$\arcmin$ away from position determined with the RXTE/PCA. We performed optical observations of the I field around the new location and identified a coincident ~ optical source (R=18.7). There exists an infrared point source in the Two Micron All Sky Survey catalogue with J=15.2, H=14.2 and K=13.5 whose location is also coincident with our Chandra and optical astrometry solutions. We additionally comment on the likely Be/X-ray binary nature of the system.
Gogus, Ersin↗
Determination of Position of Jupiter from VLBI Observations of
Very-Long Baseline Interferometry (VLBI) observations of the.
very-long baseline interferometry Jupiter Ulysses ↗
Experimental determination of position-estimate accuracy using back-azimuth signals from a microwave landing system
Flight tests using the Boeing 737 airplane to obtain position estimates with back azimuth signals from a microwave landing system (MLS) are discussed. The equations and logic used to generate a navigation position estimate in the MLS back azimuth signal environment are described. The error in the navigation position estimate is determined. A summary of the Boeing 737 position estimate update process is described. The navigation position estimate error calculated flight data and radar tracking information is analyzed. The position estimate error data using the MLS inputs are compared with error data obtained during dual distance measuring equipment updates.
Knox, C. E.↗
Aeroelastic stability of trimmed helicopter blades in forward flight
Equations for moderately large amplitude coupled flap-lag motion of a torsionally rigid hingeless elastic helicopter blade in forward flight are derived. Quasi-steady aerodynamic loads are considered and the effects of reversed flow are included. By using Galerkin's method the spatial dependence of the problem is eliminated and the equations are linearized about a time dependent equilibrium position determined from the trimmed equilibrium position of the rotor in forward flight. In the first trim procedure the rotor is maintained at a fixed value of thrust coefficient with forward flight and horizontal and vertical force equilibrium is satisfied in addition to maintaining zero pitch and roll moments. The second trim procedure maintains only zero pitch and roll moment simulating conditions under which a rotor would be tested in the wind tunnel.
Friedmann, P.↗
High energy cosmic ray iron spectrum experiment
An instrument containing a gas Cerenkov counter and an iron ionization spectrometer was constructed in order to measure the cosmic-ray iron spectrum to 300 GeV/nucleon. Trajectories of particles were determined by entopistic or position-determining scintillator systems. The geometric factors with and without the gas Cerenkov counter were 0.3 and 0.6 sq m-ster, respectively. The instrument was successfully flown in June 1976 without the spectrometer and in October 1976 with the spectrometer from Palestine, Texas. The June flight yielded 14.5 h of data; the October flight, 25 h.
Arens, J. F.↗
Improved geometric calibration of the SIR-C data
Errors in the determination of the platform state vector (position and velocity) limit the accuracy with which individual pixels in a SAR (synthetic aperture radar) image can be located. A method of updating the state vector based on the SAR data is described. The algorithm combines reference targets at known locations with the estimates available from the mission control center, utilizing a maximum likelihood estimator. The targets can be located at calibration sites or be easily recognizable targets of opportunity. The accuracy of the update depends on the number of targets, their geometry, and the accuracy of their position determination. The algorithm is tested using Seasat SAR data. High-accuracy state vectors were perturbed by Gaussian distributed errors with standard deviations and cross-correlations based on worst-case expectations for SIR-C (Shuttle Imaging Radar). Tests using ground targets located in topographic maps (1:24,000) showed that state vector position errors on the order of 300-400 m and velocity accuracies of 2-3 m/s are readily achievable.
Madsen, S. N.↗
Application of global positioning system to determination of tectonic plate movements and crustal deformations
It is shown that pseudo-range measurements to four GPS satellites based on correlation of the pseudo random code transmissions from the satellites can be used to determine the relative position of ground stations which are separated by several hundred kilometers to a precision at the centimeter level. Carrier signal measurements during the course of passage of satellites over a pair of stations also yield centimeter precision in the relative position, but oscillator instabilities limit the accuracy. The accuracy of solutions based on either type of data is limited by unmodeled tropospheric refraction effects which would reach 5 centimeters at low elevation angles for widely separated stations.
Anderle, R. J.↗
Locations of solar radio bursts
Measurements of the positions of the sources of solar radio bursts at decameter wavelengths, 20- to 60-MHz range, provide information about physical conditions in a region of the corona extending from about one-half to several solar radii from the surface of the sun. Position measurements in the 20- to 60-MHz range were made with the Clark Lake sweep-frequency grating interferometer. Although the resolution of the instrument is sufficient to measure source position accurately, the highly variable effect of refraction in the earth's ionosphere severely limits the observations, distorting position determinations to such an extent as to make much of the position data useless unless ionospheric refraction can be taken into account. A method was developed for the removal of the refractive effect from the data to permit determination of true source position. With this technique it is considered possible to measure spatial extent of radio sources that will provide information about emission processes and physical parameters in the corona.
Fitzenreiter, R.↗
Light position locating system Patent
Electro-optical detector for determining position of light source
Mclauchlan, J. M.↗
Orbit determination from two position vectors and periapsis radius
Orbit determination from two position vectors and periapsis radius, introducing polar equation for conic to obtain solution
Estes, R. H.↗
TAOS Orbit Determination Results Using Global Positioning Satellites
Orbit determination results for the Air Force Phillips Laboratory's Technology for Autonomous Operational Survivability (TAOS) satellite using a Rockwell AST V Global Positioning System (GPS) receiver are presented in this paper. Under a cooperative effort, GPS orbit determination technology developed at Jet Propulsion Laboratory (JPL) has been transferred to the U.S. Air Force. JPL's post processing differential GPS software MIRAGE [1] was modified to perform precise orbit determination for the TAOS satellite. Reconstructed TAOS position accuracies of 10 meters (3 sigma) are the objective. With four days of data, three-dimensional positions of less than 3 meters (1 sigma) have been achieved with overlapping orbit determination spans. Orbit determination results are also compared with those of the on-board GPS receiver's navigation solutions and with the Air Force's Satellite Control Network SGLS processing.
TAOS↗
A method to determine the kinematics of the lower limbs of a subject pedaling a bicycle using encoders and accelerometers
The goal of this research was to determine kinematic parameters of the lower limbs of a subject pedaling a bicycle. An existing measurement system was used as the basis to develop the model to determine position and acceleration of the limbs. The system consists of an ergometer instrumented to provide position of the pedal (foot), accelerometers to be attached to the lower limbs to measure accelerations, a recorder used for filtering, and a computer instrumented with an A/D board and a decoder board. The system is designed to read and record data from accelerometers and encoders. Software has been developed for data collection, analysis and presentation. Based on the measurement system, a two dimensional analytical model has been developed to determine configuration (position, orientation) and kinematics (velocities, accelerations). The model has been implemented in software and verified by simulation. An error analysis to determine the system's accuracy shows that the expected error is well within the specifications of practical applications. When the physical hardware is completed, NASA researchers hope to use the system developed to determine forces exerted by muscles and forces at articulations. This data will be useful in the development of countermeasures to minimize bone loss experienced by astronauts in microgravity conditions.
Liu, Shih-Ching↗
Method and device for detection of condition of brushless motors and generators
A method and device for determining the position of a rotor in a brushless motor is provided. The method generally includes: injecting electrical signals into a stator of the brushless motor; measuring scattering parameters reflected back from the stator, wherein the scattering parameters are influenced by the near-field dynamics impaired by the motor; and comparing the measured scattering parameters to a predetermined data set of scattering parameters for known rotor positions to determine the position of the rotor. The method and device is also suitable for determining a condition of a motor or a generator.
Haupt, Justine Elaine↗
Viking lander tracking contributions to Mars mapping
The paper shows how analyses of Doppler and ranging tracking data from the Viking landers are contributing to the photogrammetric inputs in three specific areas: improved determination of the spin axis of Mars, improved determination of the spin rate, and accurate position determination of the landers with respect to the equator and the vernal equinox. The latest results for these parameters are presented along with applications of these and other recent results for improved mapping of Mars. The improvements obtained provide a new level of precision for Mars mapping.
Michael, W. H., Jr.↗
The definition and stability of local inertial reference frames
VLBI measurements of extragalactic radio sources are utilized to develop a definition system for local inertial reference frames. Significant astrometric errors are identified and minimized by means of a parameter-estimation technique. A reference frame is measured for 30 min to observe the radio emission of the object to be located in the frame as well as the emission from about five additional sources which define the frame. Because the structures of the objects are unknown and tropospheric fluctuations exist, limiting errors exist for both single-epoch position determination and epoch-to-epoch differential position measurements. Data are presented regarding relativistic gravitational deflection by Jupiter which show that the local reference frame is stable at 240 microarcseconds over 12 days.
Treuhaft, R. N.↗