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Results for “temperature sensing”

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 19 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1991

Sensing Temperatures Via Prostheses And Manipulators

Proposed temperature-sensing system applies heat to (or removes heat from) human user's skin according to temperature of remote object. Used in artificial limbs and in telerobotic manipulators. In prosthetic arm and hand, sensors on tips of artificial fingers send signals to electronic control network that drives small, lightweight thermoelectric heat pump worn on back of user's shoulder. Heat pump heats or cools skin according to signals from sensors. Heat pump and control network worn like article of clothing. In manual control of remote robot, sensors placed in fingers of remote manipulator. Sensors drive, via similar electronic control network, thermoelectric heat pumps in fingers of glove worn by operator, who then has benefit of information about temperatures on manipulated object.

Zerkus, Mike↗
NASA NTRSDate not supplied

Environmental Barrier Coating Surface Temperature Mapping Using a Compatible Er-Doped Sc 2 SiO 5 Temperature-Sensing Layer

Accurate surface temperature-mapping capabilities in the 1300 to 1500 °C range are needed for SiC/SiC ceramic matrix composites protected by environmental barrier coatings (EBCs) under testing in turbine engine environment facilities. The strong background thermal radiation at these higher temperatures is a challenging issue. Er-doped Y 2 SiO 5 was previously shown to be capable of achieving luminescence lifetime-based temperature mapping up to 1560 °C as a standalone material. However, compatibility issues between an Er-doped Y 2 SiO 5 surface temperature sensing layer and an underlying Sc 2 Si 2 O 7 -based EBC topcoat limited temperature mapping of the EBC surface to a maximum of 1380 °C. Therefore, an Er-doped Sc 2 SiO 5 temperature sensing layer has been subsequently developed with better compatibility with the Sc2Si2O7-based EBC topcoat. Localized spot temperature measurements as well as luminescence lifetime imaging-based temperature mapping were demonstrated up to 1535 °C from a 15 µm thick Er-doped Sc 2 SiO 5 layer at the surface of a Sc2Si2O7-based EBC topcoat, a significant improvement over the Er-doped Y2SiO5 layer 1380 °C temperature sensing limit. No degradation of the Er-doped Sc 2 SiO 5 temperature sensing surface layer was observed.

temperature measurement↗
NASA NTRS2002

Remote magneto-elastic analyte, viscosity and temperature sensing apparatus and associated methods of sensing

An analyte, viscosity, or temperature sensing apparatus for operative arrangement within a time-varying magnetic field, including a sensor with an outer surface that is chemically, frictionally, or thermally responsive and adhered to a base magnetostrictive element, and a receiver to measure a first and second value for magneto-elastic emission intensity of the sensor taken at, respectively, a first and second interrogation frequency. A change in mass or a change in material stiffness of the sensor due to the responsiveness, the viscosity and mass density of a fluid therearound, or the temperature, can be identified. The receiver, alternatively, measures a plurality of successive values for magneto-elastic emission intensity of the sensor taken over an operating range of successive interrogation frequencies to identify a value for the sensor's magneto-elastic resonant frequency (a fundamental frequency or harmonic thereof). Several sensors in an ordered array will provide a package of information.

Grimes, Craig A.↗
NASA NTRS2000

Scan mirror remote temperature sensing system and method

A remote temperature sensing system (10) for a scanning mirror (7). The system (10) includes a sensor which detects heat radiated by the mirror and provides a signal in response thereto. In the illustrative implementation, the system (10) includes a thermistor mounted within a housing. The housing is contoured to maximize the receipt of thermal energy thereby. A mounting assembly maintains the thermistor a predetermined nonzero distance from the scanning mirror (7). The invention includes a shroud (12) mounted on the mirror (7) for shielding the thermistor and a support tube connected to the thermistor housing on a first end and to a base on the second end thereof. The support tube is adapted to remain stationary within the shroud as the scanning mirror and the shroud rotate due to the scanning of the mirror. Wires are connected to the thermistor on a first end thereof and are wrapped around the support tube. The wires include a length of electrically conductive material having a resistivity which has a low sensitivity to temperature variations. The sensor output is processed in a conventional manner to provide an output indicative of the temperature of the mirror.

VanDyk, Steven G.↗
NASA NTRS1985

The Shuttle Infrared Leeside Temperature Sensing (SILTS) experiment

The Shuttle Infrared Leeside Temperature Sensing (SILTS) experiment is described. The SILTS experiment will obtain high-spatial-resolution measurements of the temperatures of Shuttle orbiter leeside surfaces during atmospheric entry. The data will be obtained by means of an imaging, infrared radiometer, located atop the orbiter's vertical tail, which will view the orbiter fuselage and left wing. Implementation of the SILTS experiment required a significant change to the configuration of the orbiter's vertical tail fintip. The orbiter Columbia has been modified to carry the SILTS experiment which will be active on Columbia's next flight, currently scheduled for mid-1985.

Throckmorton, D. A.↗
NASA NTRSDate not supplied

Temperature Sensing to Above 1500 °C Using Y 2 SiO 5 :Er Phosphor Thermometry

A transition from metallic to ceramic turbine components that can operate at higher turbine engine temperatures will push component surface temperatures from below 1200 °C into a 1300 to 1500 °C temperature range that is much more challenging for phosphor thermometry measurements. To address this challenge, Y 2 SiO 5 :Er was selected for its high temperature sensing performance by both luminescence lifetime and luminescence intensity ratio (LIR) methods as well as its thermochemical compatibility with the current generation of rare earth silicate environmental barrier coatings (EBCs) that are required to protect SiC/SiC ceramic composite components. Lifetime measurements that monitor the Er3+ 4S3/2→4I15/2 emission decay at 542 nm exhibited a slow decrease in decay time with temperature up to 1300° C, above which the decay decreased steeply to provide good temperature sensitivity in the 1300 to 1500 °C range (Fig. 1). LIR images were obtained where each pixel represented the ratio I488/I561 (I488 and I561 are the detected 488 nm 4F7/2→4I15/2 and the 561 nm 4S3/2→4I15/2 emission band intensities, respectively). Good temperature sensitivity (Fig. 2) and signal-to-background ratios were observed to above 1500 °C. Contrary to conventional guidance on selecting phosphors for high temperature sensing, the detected emission band intensities and decay times exhibited remarkably slow decreases with temperature up into the 1300 to 1500 °C range despite high phonon energies (>900 cm-1) that allow the energy gap between the 4S3/2 emitting reservoir level and the 4F9/2 level below it to be bridged by as few as three phonons. The benefits of utilizing a thermographic phosphor at very high temperatures that exhibits strong nonradiative multiphonon relaxation even at room temperature is explained by a competition between spontaneous and stimulated multiphonon emission, and the more temperature-sensitive decay time above 1300 °C is explained by a transition from high to low effective phonon energies.

temperature measurement↗
NASA NTRS1988

Shuttle Infrared Leeside Temperature Sensing (SILTS) experiment - STS 61-C results

The operation of the Shuttle Infrared Leeside Temperature Sensing experiment on mission STS 61-C of the Space Shuttle Orbiter Columbia is described. False-color video images are shown of surface temperatures on the leeside wing and fuselage areas during entry. Features evident in the imagery are related to aerodynamic flow phenomena such as shock interactions, leeside vortices, and elevon gap effects. Significant anomalies in experiment hardware operation occurred on this flight. The anomalous hardware performance resulted in requirements for major modification to the postflight data reduction procedures. The data collected provide a qualitative, but not a fully quantitative, look at leeside surface heating.

Throckmorton, David A.↗
NASA NTRS1979

An experimental investigation to determine the effect of window cooling by mass injection for the Shuttle Infrared Leeside Temperature Sensing (SILTS) experiment

The effect of mass injection on the shuttle infrared leeside temperature sensing (SILTS) pod window surfaces in reducing window heating and minimizing window lens radiation during the reentry data taking period is investigated. Heat transfer coefficients on and around the simulated windows and window cavities are determined. Heat transfer rates and window coolant flow rates are reported for the SILTS configuration. A comparison of two windows' geometries and their effects on the heat transfer rate is discussed and oil flow photographs are presented to indicate how mass injection affects the flow field near the SILTS window.

Bradley, P. F.↗
NASA NTRS1990

Shuttle Infrared Leeside Temperature Sensing (SILTS) experiment - STS-28 preliminary results

Preliminary results from the STS-28 flight of the Shuttle Infrared Leeside Temperature Sensing (SILTS) experiment aboard the Shuttle Orbiter Columbia are presented. Infrared images are shown in false-color indicating the level and distribution of surface temperature on the leeside of the left wing during entry. Features evident in the imagery are related to their causative aerodynamic flow phenomena. Quantitative comparisons of the infrared image data with in situ temperature measurements obtained with thermocouples located at the aerodynamic surface of the thermal protection system materials are presented.

Throckmorton, David A.↗
NASA NTRS1990

Temperature sensing by primary roots of maize

Zea mays L. seedlings, grown on agar plates at 26 degrees C, reoriented the original vertical direction of their primary root when exposed to a thermal gradient applied perpendicular to the gravity vector. The magnitude and direction of curvature can not be explained simply by either a temperature or a humidity effect on root elongation. It is concluded that primary roots of maize sense temperature gradients in addition to sensing the gravitational force.

NASA Program Space Biology↗
NASA NTRS2008

Astable Oscillator Circuits using Silicon-on-Insulator Timer Chip for Wide Range Temperature Sensing

Two astable oscillator circuits were constructed using a new silicon-on-insulator (SOI) 555 timer chip for potential use as a temperature sensor in harsh environments encompassing jet engine and space mission applications. The two circuits, which differed slightly in configuration, were evaluated between -190 and 200 C. The output of each circuit was made to produce a stream of rectangular pulses whose frequency was proportional to the sensed temperature. The preliminary results indicated that both circuits performed relatively well over the entire test temperature range. In addition, after the circuits were subjected to limited thermal cycling over the temperature range of -190 to 200 C, the performance of either circuit did not experience any significant change.

Patterson, Richard L.↗
NASA NTRS1992

Shuttle Infrared Leeside Temperature Sensing (SILTS) experiment - STS-35 and STS-40 preliminary results

Preliminary results from the STS-35 and STS-40 flight of the Shuttle Infrared Leeside Temperature Sensing (SILTS) experiment aboard the Shuttle Orbiter Columbia are presented. Infrared images are shown in false-color indicating the level and distribution of surface temperature over the vehicle's leeside fuselage during entry. Features evident in the imagery are related to their causative aerodynamic flow phenomena. Quantitative comparisons of the infrared image data with in situ temperature measurements obtained with thermocouples located at the aerodynamic surface of the thermal protection materials are presented.

Throckmorton, David A.↗