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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 73 records · Page 4
All sourcesNASA NTRSDOE OSTI
DOE OSTI2022

Launch accelerometer for model rocket

Systems and methods of detecting launch of a model rocket are described herein. A mechanically implemented launch accelerometer may be disposed on a model rocket. The launch accelerometer may detect acceleration of the rocket by a mass of the launch accelerometer moving relative to the rocket and against a spring force based on the rocket acceleration. The mass may comprise a first electrical contact that may contact a second electrical contact when the mass is accelerated beyond a threshold, which is indicative of launch of the rocket. The contact between the first electrical contact and the second electrical contact may complete an electrical circuit. Furthermore, at least one pin may lock the mass in a position allowing the electrical circuit to remain complete.

Boyson, Jonathan M.↗
NASA NTRS1993

NASA Ultra-Sensitive Miniature Accelerometer

Using micro-machined silicon technology, an ultra-sensitive miniature accelerometer can be constructed which meets the requirements for microgravity experiments in the space environment. Such an accelerometer will have a full scale sensitivity of 10 -2 g, a resolution of 10 -8 g, low cross-axis sensitivity, and low temperature sensitivity. Mass of the device is approximately five grams and its footprint is 2 cm x 2 cm.

miniature↗
NASA NTRSDate not supplied

Improvements to Calibration Modeling of a Tri-Axial Accelerometer Using Response Surface Methods

Aerodynamic ground test facilities require precision attitude measurements to support fundamental research and aerodynamic vehicle characterization. Accelerometers are used as one solution for measuring test article attitude. Several wind-tunnel facilities experience elevated temperatures during sustained testing of approximately 38°C (100°F) and extremes up to 149°C (300°F). Accelerometer thermal corrections are required to maintain attitude measurement accuracy during elevated temperature tunnel conditions. This manuscript details characterization of non-linear and thermal effects of the Mini/MEMs Tri-Axis Sensor System (MTASS) developed at NASA. Non-linear effects are characterized using a two-axis index head, and temperature effects are characterized using a metallic cube in a thermal chamber. The results show a significant decrease in back-computed residuals for room temperature and elevated temperatures experiments.

Accelerometer↗
NASA NTRSDate not supplied

Improvements to Calibration Modeling of a Tri-Axial Accelerometer Using Response Surface Methods

Aerodynamic ground test facilities require precision attitude measurements to support fundamental research and aerodynamic vehicle characterization. Accelerometers are used as one solution for measuring test article attitude. Several wind-tunnel facilities experience elevated temperatures during sustained testing of approximately 38°C (100°F) and extremes up to 149°C (300°F). Accelerometer thermal corrections are required to maintain attitude measurement accuracy during elevated temperature tunnel conditions. This manuscript details characterization of non-linear and thermal effects of the Mini/MEMs Tri-Axis Sensor System (MTASS) developed at NASA. Non-linear effects are characterized using a two-axis index head, and temperature effects are characterized using a metallic cube in a thermal chamber. The results show a significant decrease in back-computed residuals for room temperature and elevated temperatures experiments.

Accelerometer↗
DOE OSTI2022

Unsupervised learning from three-component accelerometer data to monitor the spatiotemporal evolution of meso-scale hydraulic fractures

Enhanced geothermal systems can provide a substantial share of the global energy demand. There exist several hurdles in the engineering implementations of such geothermal systems. One such hurdle is the accurate monitoring of the fracture networks created in subsurface through hydraulic stimulation of these systems. Micro seismicity associated with the stimulation is the primary means to locate the event hypocenters for estimating the stimulated rock volume. Existing methods for location the hypocenters are restricted to only the highest amplitude impulsive signals that are simultaneously detected on several sensors. Consequently, a large portion (usually ~99%) of the measurements are left unused. In this paper, an unsupervised manifold-approximation followed by clustering of 3-component accelerometer data is used to analyze the seismicity recorded on a monitoring well. With this method, a larger portion of the measured signal is used for the monitoring of the hydraulic fracture network. We analyze the EGS Collab experiment 1 microseismic data, recorded at the Sanford Underground Research Facility, South Dakota. Using the data from a single three-component accelerometer, the polarization features viz. Azimuth, incidence, rectilinearity, and planarity are used as inputs for the unsupervised manifold approximation followed by clustering. Our study shows that density-based clusters in the projected 3D space correspond to distinct types of hydraulically fractured zones around the injection point. Finally, we show that the temporal evolution of these clusters can be used to track fracture creation and propagation.

58 GEOSCIENCES↗
NASA NTRS1965

Simple device produces accelerometer calibration pulse

Shock-impulse exciter produces a remote checkout of the amplitude calibration and frequency response of a piezoelectric vibration accelerometer. The exciter employs a bimetal spring to apply a mechanical acceleration pulse of a known amplitude and frequency to the accelerometer.

Source record↗
NASA NTRS1965

Miniature servo accelerometer is force- balanced

Miniature servo accelerometer measures unusually small forces of torques. The pendulous mass of the accelerometer is suspended by fused quartz torsion fibers in an electromagnetically force- balanced environment. It is used in gravity surveys for exploring mineral deposits.

Johnston, A. R.↗
NASA NTRS1966

Damping technique gives accelerometer flat frequency response

Piezoelectric accelerometer uses a viscous damping technique to achieve a flat frequency response over a wide frequency range in high acoustic environments. This eliminates the electrical overload on associated electronics and loss of useful data caused by oscillations of the accelerometer.

Wing, T.↗
NASA NTRS1966

Rectilinear accelerometer possesses self- calibration feature

Rectilinear accelerometer operates from an ac source with a phase-sensitive ac voltage output proportional to the applied accelerations. The unit includes an independent circuit for self-test which provides a sensor output simulating an acceleration applied to the sensitive axis of the accelerometer.

Henderson, R. B.↗
NASA NTRS1966

Instrument automatically selects peak acceleration signal from several accelerometers

Solid state circuit selects the highest of several ac accelerometer signals and gates this signal to an output amplifier, preserving all the frequency information in the peak signal. If the amplitudes of the accelerometer signals change with time, the circuit will continually switch to the highest signal, rejecting the smaller signals.

Chapman, C. P.↗
NASA NTRS1966

Miniature capacitive accelerometer is especially applicable to telemetry

Capacitive accelerometer design enables the construction of highly miniaturized instruments having full-scale ranges from 1 g to several hundred g. This accelerometer is applicable to telemetry and can be tailored to cover any of a large number of acceleration ranges and frequency responses.

Coon, G. W.↗
NASA NTRS1966

Low level accelerometer test methods are investigated

Problems associated with testing accelerometers to an accuracy where the standard error is less than .0000001 g are centered around the elimination of uncertainties in the acceleration input to the accelerometer. By placing a test rig in free fall, the uncertainty in the earths gravity field can be eliminated.

Nelson, R. H., Jr.↗
NASA NTRS1972

Low G accelerometer testing

Eight different types of low-g accelerometer tests are covered on the Bell miniature electrostatically suspended accelerometer (MESA) which is known to be sensitive to less than 10 to the minus 7th power earth's gravity. These tests include a mass attracting scheme, Leitz dividing head, Wild theodolite, precision gage blocks, precision tiltmeters, Hilger Watts autocollimator, Razdow Mark 2 autocollimator, and laser interferometer measuring system. Each test is described and a comparison of the results is presented. The output of the MESA was as linear and consistent as any of the available devices were capable of measuring. Although the extent of agreement varied with the test equipment used, it can only be concluded that the indicated errors were attributable to the test equipment coupled with the environmental conditions.

Vaughan, M. S.↗
NASA NTRS1972

Gyro and accelerometer failure detection and identification in redundant sensor systems

Algorithms for failure detection and identification for redundant noncolinear arrays of single degree of freedom gyros and accelerometers are described. These algorithms are optimum in the sense that detection occurs as soon as it is no longer possible to account for the instrument outputs as the outputs of good instruments operating within their noise tolerances, and identification occurs as soon as it is true that only a particular instrument failure could account for the actual instrument outputs within the noise tolerance of good instruments. An estimation algorithm is described which minimizes the maximum possible estimation error magnitude for the given set of instrument outputs. Monte Carlo simulation results are presented for the application of the algorithms to an inertial reference unit consisting of six gyros and six accelerometers in two alternate configurations.

Potter, J. E.↗
NASA NTRS1972

Gyro and accelerometer failure detection and identification in redundant sensor systems.

An algorithm for failure detection and identification for redundant non-orthogonal arrays of single degree of freedom gyros and accelerometers is described which is optimum in the sense that detection occurs as soon as it is no longer possible to account for the instrument outputs as the outputs of good instruments operating within their noise tolerances, and identification occurs as soon as it is true that only a particular instrument failure could account for the actual instrument outputs within the noise tolerance of good instruments. An estimation algorithm is described which minimizes the maximum possible error magnitude for the given set of instrument outputs. Monte Carlo simulation results are presented for the application of the algorithms to an inertial reference unit consisting of six gyros and six accelerometers in two alternate configurations.

Potter, J. E.↗
NASA NTRS1973

Minimax failure detection and identification in redundant gyro and accelerometer systems.

Minimax algorithms for failure detection and identification for redundant noncolinear arrays of single-degree-of-freedom gyros and accelerometers are described. These algorithms are optimum in the sense that detection occurs as soon as it is no longer possible to account for the instrument outputs as the outputs of good instruments operating within their noise tolerances, and identification occurs as soon as it is true that only a particular instrument failure could account for the actual instrument outputs within the noise tolerance of good instruments. An estimation algorithm is described which minimizes the maximum possible estimation error magnitude for the given set of instrument outputs. Monte Carlo simulation results are presented for the application of the algorithms to an inertial reference unit consisting of six gyros and six accelerometers in two alternate configurations.

Potter, J. E.↗
NASA NTRS1974

Contributions to the problem of piezoelectric accelerometer calibration

After discussing the principal calibration methods for piezoelectric accelerometers, an experimental setup for accelerometer calibration by the reciprocity method is described It is shown how the use of a lock-in voltmeter eliminates errors due to viscous damping and electrical loading.

Jakab, I.↗