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  • AERODYNAMICS  (415)
  • INSTRUMENTATION AND PHOTOGRAPHY  (313)
  • 1985-1989
  • 1975-1979  (728)
  • 1975  (728)
  • 1
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    A high-temperature wideband pressure transducer (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Progress in the development of a pressure transducer for measurement of the pressure fluctuations in the high temperature environment of a jet exhaust is reported. A condenser microphone carrier system was adapted to meet the specifications. A theoretical analysis is presented which describes the operation of the condenser microphone in terms of geometry, materials, and other physical properties. The analysis was used as the basis for design of a prototype high temperature microphone. The feasibility of connecting the microphone to a converter over a high temperature cable operating as a half-wavelength transmission line was also examined.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-CR-145710 , PGS-TR-PH-75-16
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Instrumentation for measurement of aircraft noise and sonic boom (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A jet aircraft noise and sonic boom measuring device which converts sound pressure into electric current is described. An electric current proportional to the sound pressure level at a condenser microphone is produced and transmitted over a cable, amplified by a zero drive amplifier and recorded on magnetic tape. The converter is comprised of a local oscillator, a dual-gate field-effect transistor (FET) mixer and a voltage regulator/impedance translator. A carrier voltage that is applied to one of the gates of the FET mixer is generated by the local oscillator. The microphone signal is mixed with the carrier to produce an electrical current at the frequency of vibration of the microphone diaphragm by the FET mixer. The voltage of the local oscillator and mixer stages is regulated, the carrier at the output is eliminated, and a low output impedance at the cable terminals is provided by the voltage regulator/impedance translator.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Lee surface flow phenomena over Space Shuttle at large angles of attack at M infinity = 6 (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An investigation was conducted regarding the surface heat transfer on the leeward side of the Space Shuttle, taking into account different free stream Reynolds numbers and angles of attack. Another investigation was concerned with the peak heating due to boundary layer transition and flow separation in the case of different Space Shuttle configurations. Criteria for vortex generation on the leeward flow were also examined along with the effect of transition on vortex generation. Attention was given to the leeward flowfield in the vortex flow region and the method of constructing an equivalent model for leeward flowfield analysis.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-148 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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  • 4
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    The effects of out-of-field radiation on earth-observing telescopes (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The stray radiation rejection requirements for the Synchronous Earth Observation Satellite telescope were determined and compared with estimated stray radiation rejection performance. It was found that normal baffle design practice and 0.05 wavelength rms surface roughness on the mirrors is adequate to prevent stray light from limiting the telescope measurements as long as the sun is 10 deg or more from the edge of the field of view for a baffle tube length-to-aperture diameter ratio of 6.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Engineering; 14; July-Aug
    Format: text
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  • 5
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    Scanning system tradeoffs for remote optical sensing from geosynchronous orbit (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The scanning and telescope field of view requirements for making Earth Resources (ER) and Meteorological (MET) phenomena observations from a Synchronous Earth Observation Satellite (SEOS) have been defined. The equations relating spacecraft scan capability to user scan field of view requirements are given and evaluated using four different telescope fields of view. The tradeoffs between telescope field-of-view and user scan fields of view requirements are shown, and it was determined that a 0.6 degree by 1.2 degree telescope FOV is optimum for the SEOS telescope. It was shown that an internal scan as well as external scan is required to satisfy both ER and MET users.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Optical Engineering; 14; July-Aug
    Format: text
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  • 6
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    A steering law for three double-gimbal control moment gyro systems (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A steering law for three double-gimbal control moment gyro (CMG) systems is proposed. This steering law is applicable to systems with almost any configuration of CMGs and the CMG-out operation needs no special modification. Examples of three double gimbal CMG systems in an orthogonal configuration and in a parallel configuration are shown along with the results of digital simulations. Simulation results show that any command torque can always be met except when the system is in a singular state and that, whenever the system is in, or close to, a singularity, the steering law drives the system state out of the vicinity of the singularity.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-X-64926
    Format: application/pdf
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  • 7
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    Methods Studies on System Identification from Transient Rotor Tests (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: Some of the more important methods are discussed that have been used or proposed for aircraft parameter identification. The methods are classified into two groups: Equation error or regression estimates and Bayesian estimates and their derivatives that are based on probabilistic concepts. In both of these two groups the cost function can be optimized either globally over the entire time span of the transient, or sequentially, leading to the formulation of optimum filters. Identifiability problems and the validation of the estimates are briefly outlined, and applications to lifting rotors are discussed.
    Keywords: AERODYNAMICS
    Type: NASA-CR-137965 , AR-2-PT-1
    Format: application/pdf
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  • 8
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    Plastic scintillation counters with an area of 2 sq m (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Two designs of plastic scintillation counters with an area of 2 sq m scanned in each case by a single photomultiplier of the FEU-49 type are described. The radial dependence of their light collection at the place of the path of the detected particle does not exceed 10% while the half width of the differential distribution of the pulse amplitudes from nonfiltered cosmic radiation at sea level is 90 to 95%, and 65%, the plastic thickness being 5 cm and 10 cm, respectively. The temperature coefficient of the counter is 0.32% per 1 C.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Cosmic Rays (NASA-TT-F-807); p 389-393
    Format: text
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  • 9
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    Estimating maximum instantaneous distortion from inlet total pressure rms and PSD measurements (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: An inexpensive method is developed to determine the extreme values of instantaneous inlet distortion. This method also provides insight into the basic mechanics of unsteady inlet flow and the associated engine reaction. The analysis is based on fundamental fluid dynamics and statistical methods to provide an understanding of the turbulent inlet flow and quantitatively relate the rms level and power spectral density (PSD) function of the measured time variant total pressure fluctuations to the strength and size of the low pressure regions. The most probable extreme value of the instantaneous distortion is then synthesized from this information in conjunction with the steady state distortion. Results of the analysis show the extreme values to be dependent upon the steady state distortion, the measured turbulence rms level and PSD function, the time on point, and the engine response characteristics. Analytical projections of instantaneous distortion are presented and compared with data obtained by a conventional, highly time correlated, 40 probe instantaneous pressure measurement system.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 75-1213
    Format: text
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  • 10
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    Forward marching procedure for separated boundary-layer flows (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A forward-marching procedure for separated boundary-layer flows which permits the rapid and accurate solution of flows of limited extent is presented. The streamwise convection of vorticity in the reversed flow region is neglected, and this approximation is incorporated into a previously developed (Carter, 1974) inverse boundary-layer procedure. The equations are solved by the Crank-Nicolson finite-difference scheme in which column iteration is carried out at each streamwise station. Instabilities encountered in the column iterations are removed by introducing timelike terms in the finite-difference equations. This provides both unconditional diagonal dominance and a column iterative scheme, found to be stable using the von Neumann stability analysis.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Aug. 197
    Format: text
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