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Results for “cryogenic cooling”

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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At least 217 records · Page 12
All sourcesNASA NTRSDOE OSTI
NASA NTRS1979

A reflected-wave ruby maser with K-band tuning range and large instantaneous bandwidth

A novel maser concept is outlined and a unique design described which permits wide bandwidth and waveguide tuning range by employing four stages cascaded via cryogenically cooled circulators. Theoretical considerations for gain, bandwidth, gain ripple, and noise temperature are included. Operated on a closed-cycle helium refrigerator with a superconducting persistence-mode magnet, the four-stage amplifier is tunable from 18.3 to 26.6 GHz with 30 dB of net gain and achieves 240 MHz of 3-dB bandwidth near the center of this band. The measured noise temperature is 13 + or - 2 K referred to the room-temperature input flange. Applications are foreseen utilizing cooled parametric downconverters and upconverters with this amplifier at IF to extend the low-noise performance up to millimeter frequencies and down to L-band for radio astronomy and planetary spacecraft communications.

Moore, C. R.↗
NASA NTRS1979

Tests of low background photo conductors

In support of two infrared astronomy space projects, the IRAS satellite and the IRT on Spacelab 2, low-background tests were carried out on the performance and characterization of Si:Ga, Si:As, Si:Sb and Ge:Ga photoconductive detectors. These test results represent a useful appraisal of this family of detectors when operated at 1.8-4.2 K and at background power levels of 10 to the -14th to 10 to the -13th W. In addition to detector performance data, results are also presented on cryogenically cooled MOSFET amplifiers operated in the source follower and in the balanced-dc-TIA configurations.

Young, E. T.↗
NASA NTRS1979

Pulsed plasma thruster backflow characteristics

The exhaust plume of a millipound pulsed plasma thruster has been investigated using a unique vacuum facility with cryogenically cooled low back-scatter chamber walls. The mass flux distribution of the plume was determined, with emphasis on the region upstream of the thruster. Measurements of the plume material scattered from the chamber walls were used with articulated collimator-quartz crystal microbalance measurements of the total flux to estimate the upstream flux originating in the plume. This flux was found to be of order 10 to the minus 10 g/sq cm/ pulse and to vary approximately with the inverse square of the radius. Measurements indicate the directed plume is essentially axisymmetric with a slight elongation in the direction parallel to the interelectrode gap. This downstream flux decreases with radius along a Gaussian profile with 90% of the plume confined to a 40 deg half-angle cone.

Rudolph, L. K.↗
NASA NTRS1980

Support assembly for cryogenically coolable low-noise choke waveguide

A compact cryogenically coolable choked waveguide for low-noise input coupling into a cryogenically cooled device, such as a maser or parametric amplifier, utilizes coaxial stainless steel support tubes surrounding the waveguide and connected in cascade to provide a folded low thermal conduction path. The edges of the tubes connected are welded.

Mccrea, F. E.↗
NASA NTRS1979

Infrared telescope on Spacelab 2

The infrared telescope (IRT) on Spacelab 2 which will be the first cryogenically cooled telescope operated from the Orbiter is discussed. Its objectives are to measure the induced environment about the Orbiter and to demonstrate the ability to manage a large volume of superfluid helium in space. The prime astrophysical objectives are to map extended sources of low surface brightness infrared emission, including the zodiacal light, the galactic plane, and extragalactic regions. The IRT design is described, including the f/4 15.2 cm highly baffled Herschelian telescope cooled to 8 K which may scan to within 35 deg of the sun. The focal plane cooled to 3 K consists of nine discrete photoconductors covering the wavelength of 4.5-120 microns in five bands, with a single stellar detector used for aspect determination. Overlapping scans, contiguous orbits, and a six degree per second scan rate permit rapid redundant coverage of 60 % of the sky.

Koch, D.↗
NASA NTRS1979

Review of design and operational characteristics of the 0.3-meter transonic cryogenic tunnel

The fundamentals of cryogenic testing are validated both analytically and experimentally employing the 0.3-m transonic cryogenic tunnel. The tunnel with its unique Reynolds number capability has been used for a wide variety of aerodynamic tests. Techniques regarding real-gas effects have been developed and cryogenic tunnel conditions are set and maintained accurately. It is shown that cryogenic cooling, by injecting nitrogen directly into the tunnel circuit, imposes no problems with temperature distribution or dynamic response characteristics.

Ray, E. J.↗
NASA NTRS1980

Internal image motion compensation system for the Shuttle Infrared Telescope Facility

The Shuttle Infrared Telescope Facility (SIRTF) is being designed as a 1-m, cryogenically cooled telescope capable of a thirty-fold improvement over currently available infrared instruments. The SIRTF, mounted in the Orbiter bay on the Instrument Pointing System (IPS), requires that the image at the focal plane be stabilized to better than 0.1 arcsec with an absolute accuracy of 1 arcsec in order to attain this goal. Current estimates of IPS performance for both stability and accuracy indicate that additional stabilization will be necessary to meet the SIRTF requirements. An Image Motion Compensation (IMC) system, utilizing a Charge Coupled Device (CCD) star tracker located at the focal plane and a steerable mirror in the SIRTF optical path, has been designed to work in conjunction with the IPS.

Lorell, K. R.↗
NASA NTRS1978

Simulation of the Infrared Astronomical Satellite /IRAS/ telescope system

The Infrared Astronomical Satellite (IRAS), a joint Dutch-British-U.S. project scheduled for launch in February 1981, will conduct the first all-sky infrared survey between 8 and 120 microns using a 60-cm aperture, cryogenically-cooled telescope. A computer simulation program has been developed at Ames Research Center to aid in the design of this complex telescope. The development and implementation of the IRAS Telescope Simulator (IRTS), its input data sources, and its output data products are described.

Henderson, E.↗
NASA NTRS1982

Dynamic Isolation for Cryogenic Refrigerators

Prototype pressure-compensated mounting isolates a Tunable Diode Laser (TDL) housing from mechanical vibration. Mounting is being tested as part of Langley Research Center program for development of highly sensitive instruments that remotely measure important chemical constituents of atmosphere. Instruments typically have requirement for cryogenic cooling of sensitive detectors and components that are necessary to detect presence of tenuous constituents of atmosphere. Key elements of mounting are two bellows, reaction plate, flexible straps and vibration isolators.

Averill, R. D.↗
NASA NTRS1981

Evaluation of moire techniques for wind tunnel metrology

The development of a moire technique suitable for the analysis of object deflections in a cryogenically cooled, transonic wind tunnel is described. The operating environment for the wind tunnel has a temperature range of 77 to 3390 k, pressure to 91390 Kgs/sq m, and noise to 150 dB SPL. Efforts were made to accomplish the following: to demonstrate projection moire as it would be used to study structural deflections; to use optical processing to multiply the sensitivity of the moire; and to investigate a system design based on the requirements of the wind tunnel geometry.

Harris, J. S.↗
NASA NTRS1981

Stray radiation and the Infrared Astronomical Satellite /IRAS/ telescope

Stray light control is a major consideration in the design of infrared cryogenically cooled telescopes such as the Infrared Astronomical Satellite (IRAS). The basic design of the baffle system, and the placement, shape, and coating of the secondary support struts for the telescope subsystem are described. The intent of this paper is to highlight the stray light problems encountered while designing the system, and to illustrate how computer analysis can be a useful design aid. Scattering measurements of the primary mirror, and a full system level scatter measurement are presented. Comparisons of predicted performance with the measured results are also presented.

Noll, R. J.↗
NASA NTRS1981

Orbital operations with the Shuttle Infrared Telescope Facility /SIRTF/

The Shuttle Infrared Telescope Facility (SIRTF) is a cryogenically-cooled, 1-m-class telescope that will be operated from the Space Shuttle as an observatory for infrared astronomy. This paper discusses the scientific constraints on and the requirements for pointing and controlling SIRTF as well as several aspects of SIRTF orbital operations. The basic pointing requirement is for an rms stability of 0.25 arcsec, which is necessary to realize the full angular resolution of the 5-micron diffraction-limited SIRTF. Achieving this stability requires the use of hardware and software integral to SIRTF working interactively with the gyrostabilized Shuttle pointing-mount. The higher sensitivity of SIRTF, together with orbital and time constraints, puts a premium on rapid target acquisition and on efficient operational and observational procedures. Several possible acquisition modes are discussed, and the importance of source acquisition by maximizing the output of an infrared detector is emphasized.

Werner, M. W.↗
NASA NTRS1981

Shuttle infrared telescope facility pointing and control system

The Shuttle Infrared Telescope Facility (SIRTF) is being designed as a 0.85 m cryogenically cooled telescope capable of a three order of magnitude improvement over currently available infrared instruments. The SIRTF requires that the image at the focal plane be stabilized to better than 0.25 arcsec with an absolute accuracy of 1.0 arcsec. Current pointing-mount performance simulations indicate that neither of these requirements can be met without additional stabilization. The SIRTF pointing and control system will utilize gyro outputs, star field position measurements from a focal plane fine guidance sensor, and a steerable secondary mirror to provide the necessary stabilization and pointing control. The charge coupled device fine guidance sensor tracks multiple stars simultaneously and, through the use of multistar processing algorithms in a high performance microcomputer, generates three-axis attitude errors and gyro-drift estimates to correct the pointing-mount gyros. A high-bandwidth feedforward loop, driven directly from the pointing-mount gyro package, controls the steering mirror in order to correct disturbances not compensated for by the pointing-mount control system. A prototype design for the SIRTF pointing and control system is described in detail. Performance analyses made using a digital simulation of the pointing and control system as well as experimental data obtained in laboratory and field test measurements are presented.

Lorell, K. R.↗
NASA NTRS1982

The sixteen to forty micron spectroscopy from the NASA Lear jet

Two cryogenically cooled infrared grating spectrometers were designed, fabricated and used on the NASA Lear Jet Observatory. The first spectrometer was used to measure continuum sources such as dust in H II regions, the galactic center and the thermal emission from Mars, Jupiter, Saturn, and Venus over the 16 to 40 micron spectral range. The second spectrometer had higher resolution and was used to measure ionic spectral lines in H II regions (S III at 18.7 microns). It was later used extensively on NASA C-141 Observatory to make observations of numerous objects including H II regions, planetary nebulae, stars with circumstellar shells, the galactic center and extragalactic objects. The spectrometers are described including the major innovations and a list of the scientific contributions.

Houck, J. R.↗
NASA NTRS1981

Sunshade/radiative cooler for IRAS infrared astronomical satellite

The Infrared Astronomical Satellite (IRAS) is a joint project shared by the United States and the Netherlands with the United Kingdom providing tracking and ground support services. IRAS features a cryogenically cooled telescope designed to perform an unbiased all-sky survey of the far infrared spectrum from 8 to 120 microns and to observe objects of special interest. The sunshade is designed to protect the telescope aperture and sunshade radiators from: direct solar radiation; direct earth radiation; radiation exchange with satellite structures; excessive aperture heating caused by sunshade inner cone emission. The sunshade three-stage radiative cooler design meets the listed requirements and, in addition, provides some contamination protection for the telescope aperture and optical surfaces during pointing maneuvers when the telescope is tilted in the direction of the velocity vector. Unless protected by the sunshade, the ram effect can cause molecules to enter the aperture and deposit on the cooled optical surfaces. This paper describes the sunshade design, the thermal analyses, and the results of thermal balance testing of the flight hardware.

Anderson, R. R.↗
NASA NTRS1982

Closed-cycle cryogenic pump suitable for sounding rockets use

We have successfully used a closed-cycle cryogenic cooling system as a high-speed UHV pump for instruments carried into the upper atmosphere on board sounding rockets. The device utilizes a commercially available, Sterling-cycle refrigerator that has proven to be rugged and simple to use under field conditions.

Erdman, P. W.↗
NASA NTRS1981

Fourier spectroscopy on planetary missions including Voyager

For more than a decade, spaceborne Fourier transform spectrometers have been employed in investigations concerning the earth and other objects in the solar system. The wide spectral range at moderately high spectral resolution, the precise wavenumber and radiometric calibrations, and the reliability achieved by these instruments, have permitted scientific investigations which would otherwise have been impossible. Weight limitations and the long flight durations prohibited the use of highly sensitive, cryogenically cooled detectors on these missions. A brief review is presented of the evolution of the instruments known as IRIS (InfraRed Interferometric Spectrometer). The concept of remote sensing by infrared emission spectroscopy is discussed, and examples of results obtained with IRIS are presented. Attention is given to the most recent results from Voyager with emphasis on those from Titan.

Hanel, R. A.↗
NASA NTRS1982

The development and applications of charge-coupled devices for space astronomy

The developments in charge-coupled device technology over the past decade are reviewed, with emphasis on the relevance of these developments to astronomical applications. The characteristics and limitations of current commercial devices are described, and the future requirements on CCDs for space astronomy are summarized for the X-ray and near UV, optical, and infrared wavelength ranges. Emphasis is placed on the commonality of technological development which is called for, including the issues of quantum detection efficiency (photon entrance and depletion depth), charge transfer efficiency, modulation transfer function, output noise level, and array size. The system requirements on focal plane instrumentation for space astronomy are summarized, and shown to have much in common for the different wavelength bands. These requirements are discussed in terms of CCD mosaicing, cryogenic cooling, and electronics. The overlap in CCD developments in the defense, astronomical and commercial arenas is summarized.

Griffiths, R. E.↗