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At least 523 records · Page 29
All sourcesNASA NTRSDOE OSTI
NASA NTRS1981

An error budget for the JPL hydrogen maser receiver

The hydrogen maser receiver is a synthesizer that converts the maser signal, at about 1420 MHz, to a set of output signals at 100, 20, 10, 5, 1, and 0.1 MHz. The contribution of the receiver and its component modules to the frequency instability and phase noise of each of its outputs is estimated, and these results are compared to published measurements of the 100-MHz output of the frequency standard, which consists of a maser plus its receiver. One can then assess how much the receiver degrades the performance of the frequency standard.

Greenhall, C. A.↗
NASA NTRS1982

The JPL millimeter, submillimeter and microwave line catalog

The catalog includes molecules of interest in the interstellar medium, in planetary atmospheres and in the Earth's atmosphere. Different units than those on the AFGL tape are used. For citing line frequencies in the microwave region. Either the experimental errors or the propagation of errors from the fit are included on the tape. This gives an estimate of how accurate the frequencies are. The intensity units are defined as follows: the logarithm of the intensity unit is the cross section times the frequency in MHz. This is essentially the same unit as on the AFGL tape, but contains fewer factors of the speed of light. The catalog is available to the scientific community either as a tape or on microfiche (filmed in frequency sorted and molecule sorted format).

Pickett, H.↗
NASA NTRS1982

Optical characterization of solar concentrator mirrors using the solar beam of the JPL 25-foot space simulator

The Jet Propulsion Laboratory 25-foot space simulator with its 5.8-m (19-ft) diameter simulated solar beam provides an excellent facility for measuring the optical characteristics of parabolic solar concentrator panels and gores. The virtual source position and size were determined by using a single lamp of the 37 xenon 30-kW source array with only the center lens in the 19-channel optical mixer. This data was used to define the optical test geometry, and it allowed accurate measurement of focal length and surface deviations of the mirror under test. A flux distribution of a typical solar concentrator placed directly on the solar beam gives measurements of performance at the focal point of the parabolic surface.

Argoud, M. J.↗
NASA NTRS1981

JPL pulsar timing observations. I - The Vela pulsar

It is found through an analysis of 12 years of arrival time data for PSR 0833-45, by fitting a model of the pulse period to the data in a least-squares sense, that there exist regions of exceptionally stable behavior in which rms residuals are typically about 40 microsec. In addition, each residual exhibits a significant period parameter second derivative which is found to change little within a given interjump era. Parameter changes in the period P, and the derivatives introduced by each of the four large observed jumps in period, are recomputed to demonstrate that the post-jump decay is nearly exponential in form. It is found that random fluctuations in P are an order of magnitude less than the systematic variations caused by the seond derivative period parameter, whose component associated with the general slowdown of the pulsar can be reliably measured when the observations span 55 years or more.

Downs, G. S.↗
NASA NTRS1982

JPL pulsar timing observations - Spinups in PSR 0525+21

Observations of the very slow objects PSR 0525+21, in which two small spin-ups occur, are presented. Twelve years of observation at 2.4 GHz reveal that the ratio of small jumps to the period is about one billionth, where the period is about 3.745 s; the analysis that arrived at these results is shown. The short-term behavior following the larger jump suggests an exponential decay, and long-term changes in the period derivative of about 0.03 percent clearly persist after each jump. It is argued that the spin-ups are not due to starquakes, but may be caused by uncoupling of a lighter crust from the core.

Downs, G. S.↗
NASA NTRS1982

The fabrication and surface tolerance measurements of the JPL clear aperture microwave antenna

Present ground station microwave antennas of the Deep Space Network are of the symmetric dual reflector (cassegrainian) type. An investigation is being made of alternative high-performance offset antenna designs which have a clear aperture (no reflector or structural blockage) with shaped reflector surfaces. A 1.5-m, 32-GHz clear aperture model was built for experimental studies. The unique processes of fabrication, surface measurement, and alignment are described.

Carpenter, J.↗
NASA NTRS1983

Performance simulation of the JPL solar-powered distiller. Part 1: Quasi-steady-state conditions

A 37.85 cu m (10,000 gallons) per year (nominal) passive solar powered water distillation system was installed and is operational in the Venus Deep Space Station. The system replaced an old, electrically powered water distiller. The distilled water produced with its high electrical resistivity is used to cool the sensitive microwave equipment. A detailed thermal model was developed to simulate the performance of the distiller and study its sensitivity under varying environment and load conditions. The quasi-steady state portion of the model is presented together with the formulas for heat and mass transfer coefficients used. Initial results indicated that a daily water evaporation efficiency of 30% can be achieved. A comparison made between a full day performance simulation and the actual field measurements gave good agreement between theory and experiment, which verified the model.

Yung, C. S.↗
NASA NTRS1983

The JPL 1.5-meter Clear Aperture Antenna with 84.5 Percent Efficiency

The theoretical and experimental study of a 1.5-meter offset dual shaped reflector at 31.4 GHz is detailed. An efficiency of 84.5 percent, a likely new record for reflector antennas, was ascertained through careful measurements. For larger low noise reflector systems, a 2- to 3-dB improvement in G/T performance over the state of the art ultra low noise ground stations and 90 percent or better aperture efficiency now appear feasible.

Cha, A. G.↗
NASA NTRS1982

JPL airborne instruments activities

Two instruments intended for flight aboard aircraft for research in advanced remote sensing of the earth are under development: the airborne imaging spectrometer (AIS) and the airborne visible-infrared imaging spectrometer (AVIRIS). The AIS utilizes a 32 x 32 element HgCdTe CCD array to gather 10nm spectral data, initially in the 1.2 to 2.4 micron range, with 32 pixels of cross-track spatial data. The instrument acquires 128 channels of spectral data by using a grating spectrometer whose grating is stepped through four positions during a fraction of an IFOV time on the ground. With an IFOV of 2 mrad, the GIFOV at the design altitude of 3 km is 6m. The instrument has several on-board processing capabilities including ax+b corrections for detector calibration, cross-track and down-track pixel summing, spectral band summing, and variable integration time to allow flight at various altitudes and velocities. The AVIRIS uses a proven scanning mechanism to acquire the spatial data in a whisk broom mode. The spectral coverage is from 0.35 to 2.5 microns at bandwidths ranging from 10 to 20 nm.

Vane, G.↗
NASA NTRS1983

JPL pulsar timing observations. II - Geocentric arrival times

Monitoring of the behavior of naturally pulsating galactic radio sources, or pulsars, through regularly spaced measurements of pulse arrival times, has been conducted by several laboratories. A tabular presentation is here made of pulse arrival time measurements from the NASA Deep Space Network between late 1968 and early 1981. By expressing the measurements in ephemeris time, and referring them to the geocenter, usable tables of results have been generated for each pulsar listed in the first of the tables given. The considerations addressed by the tables are: (1) a necessary step in the study of pulsar dynamics is the reduction of topocentric arrival times to the barycenter of the solar system; (2) the tabulated data are accessible to all opinions as to the procedures to be used in interpreting arrival time data; and (3) different observing programs can usually be combined to produce an improvement in the total data set.

Downs, G. S.↗
NASA NTRS1983

Remote measurement of trace gases with the JPL laser absorption spectrometer

Extensive data from large regions are needed as a basis for the study of anthropogenic trace gases in the troposphere. The need arises, therefore, for an instrument which is capable to monitor rapidly the atmosphere in a region. The present investigation is concerned with the results of efforts to develop an instrument which is capable of remotely measuring gases in the troposphere. The Laser Absorption Spectrometer (LAS) was designed for use in aircraft, and was employed to measure tropospheric ozone distribution since 1977. Attention is given to a description of the LAS instrument, the theoretical basis of instrument operation, LAS measurement programs, the results of the LAS development program, and future work.

Shumate, M. S.↗
NASA NTRS1981

JPL highlights, 1981

Deep space exploration, energy and energy conversion technology, Earth orbital applications, information systems and space technology development, and technology applications are discussed.

Source record↗
NASA NTRS1983

JPL Closeup

Voyager, Infrared Astronomical Satellite, Galileo, Viking, Solar Mesosphere Explorer, Wide-field/Planetary Camera, Venus Mapper, International Solar Polar Mission - Solar Interplanetary Satellite, Extreme Ultraviolet Explores, Starprobe, International Halley Watch, Marine Mark II, Samex, Shuttle Imaging Radar-A, Deep Space Network, Biomedical Technology, Ocean Studies and Robotics are summarized.

Source record↗
NASA NTRS1983

Performance evaluation of the JPL interim digital SAR processor

The performance of the Interim Digital SAR Processor (IDP) was evaluated. The IDP processor was originally developed for experimental processing of digital SEASAT SAR data. One phase of the system upgrade which features parallel processing in three peripheral array processors, automated estimation for Doppler parameters, and unsupervised image pixel location determination and registration was executed. The method to compensate for the target range curvature effect was improved. A four point interpolation scheme is implemented to replace the nearest neighbor scheme used in the original IDP. The processor still maintains its fast throughput speed. The current performance and capability of the processing modes now available on the IDP system are updated.

Wu, C.↗
NASA NTRS1983

JPL tests of a LaJet concentrator facet

A LaJet Energy Company (LEC) concentrator facet, 60 in. in diameter, was tested for imaging quality. The following two methods were used: (1) autofocus tests with a point source of light at the facet's radius of curvature; and (2) tests with the Sun close to the horizon as a distant source. The tests of the LaJet facet indicate that all of the solar image reflected by an LEC 460 solar concentrator made of like facets should fall within a 9-in. aperture if the outer facets are carefully adjusted. Such a concentrator would have acceptable performance, but complete evaluation must be made with an assembled concentrator.

Dennison, E. W.↗
NASA NTRS1983

Single event upset (SEU) of semiconductor devices - A summary of JPL test data

The data summarized describe single event upset (bit-flips) for 60 device types having data storage elements. The data are from 15 acceleration tests with both protons and heavier ions. Tables are included summarizing the upset threshold data and listing the devices tested for heavy ion induced bit-flip and the devices tested with protons. With regard to the proton data, it is noted that the data are often limited to one proton energy, since the tests were usually motivated by the engineering requirement of comparing similar candidate devices for a system. It is noted that many of the devices exhibited no upset for the given test conditions (the maximum fluence and the maximum proton energy Ep are given for these cases). It is believed, however, that some possibility of upset usually exists because there is a slight chance that the recoil atom may receive up to 10 to 20 MeV of recoil energy (with more energy at higher Ep).

Nichols, D. K.↗