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  • Other Sources  (93)
  • MECHANICAL ENGINEERING  (55)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE
  • 2020-2023
  • 1980-1984  (93)
  • 1940-1944
  • 1983  (93)
  • 1
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    Operational military helicopter interior noise and vibration measurements with comparisons to ride quality criteria (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Balka (1981) has identified the attainment of a 'jet-smooth' ride as a primary goal of the helicopter industry for commercial and certain military helicopters. It was noted that criteria accounting for both multiple axis vibration and interior noise are needed. The present investigation has the objective to present a vibration and interior noise data base in a format suitable for direct evaluation of aircraft ride quality. The investigation is also concerned with an assessment of the measured environment against available criteria as an indication of the state-of-the-art for current machines. Interior noise and vibration measurements were obtained on eight military helicopters during routine operational flights. The data are presented in the form of a number of parameters.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-2526
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    AFTI/F-16 flight test results and lessons (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The AFTI/F-16 flight test program is summarized, and several design issues of general interest are addressed. A brief description is given of the test vehicle, its flight control modes, and the flight envelopes in which testing was performed. Flight test results are summarized by addressing benefits experienced in flight control task-tailoring, handling qualities in mission tasks, aircraft structure considerations, digital flight control system performance, and human factors. Finally, several design issues relevant to future fighter aircraft are examined, including degraded flight control, system complexity, simplex information in redundant systems, and single failure propagation in redundant systems.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Interior noise considerations for advanced high-speed turboprop aircraft (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 17, p. 2685, Accession no. A82-35018
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: (ISSN 0021-8669)
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Double arch mirror study (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The development of a method of mounting light weight glass mirrors for astronomical telescopes compatible with the goals of the Shuttle Infrared Telescope Facility (SIRTF) was investigated. A 20 in. diameter double arch lightweight mirror previously fabricated was modified to use a new mount configuration. This mount concept was developed and fabricated. The mounting concept of the double mounting mirror is outlined. The modifications made to the mirror, fabrication of the mirror mount, and room temperature testing of the mirror and mount and the extension of the mirror and mount concept to a full size (40 in. diameter) primary mirror for SIRTF are discussed.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-166589 , NAS 1.26:166589
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Double arch mirror study. Part 1: Preliminary engineering report (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In the proposed design, the NASA AMES 20-in double arch mirror is supported by three clamp and flexure assemblies. The mirror clamp consists of a T-shaped Invar-36 member that goes into a similarly shaped socket in the back of the mirror. The mirror socket is made oversize and contacts the clamp only along the conical surface. The clamp is preloaded by a spring washer and pulls the mirror into contact with the flexure. The clamp is then inserted into the mirror socket through a cutout, is rotated 90 deg, and is then pinned in place. Loading conditions considered in socket design are discussed as well as stress in the socket and clamp. Flexure geometry and stress are examined as well as the effects of flexure error and of mirror cell error.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-166589-PT-1 , NAS 1.26:166589-PT-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Space applications of Automation, Robotics And Machine Intelligence Systems (ARAMIS). Volume 3, phase 2: Executive summary (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The field of telepresence is defined, and overviews of those capabilities that are now available, and those that will be required to support a NASA telepresence effort are provided. Investigation of NASA's plans and goals with regard to telepresence, extensive literature search for materials relating to relevant technologies, a description of these technologies and their state of the art, and projections for advances in these technologies are included. Several space projects are examined in detail to determine what capabilities are required of a telepresence system in order to accomplish various tasks, such as servicing and assembly. The key operational and technological areas are identified, conclusions and recommendations are made for further research, and an example developmental program leading to an operational telepresence servicer is presented.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-3736 , NAS 1.26:3736 , SSL-32-83-VOL-3-PHASE-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Status review of a supersonically-biased fighter wing-design study (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Results from an ongoing supersonically-biased fighter wing-design study are summarized. The study has been conducted to explore the effects of supersonic aerodynamic performance, transonic maneuvering, low-speed/high angle-of-attack characteristics, and airframe system integration requirements on fighter aircraft wing design. The approach adopted involves the theoretical and experimental investigation of four advanced aircraft configurations which differ only in wing geometry. Supersonic and low-speed/high angle-of-attack wind tunnel results have been obtained for 20 deg trapezoidal, 65 deg delta, 70/30-deg advanced cranked, and 70/66-deg advanced cranked wing configurations. The supersonic data show that the advanced cranked wings outperform the trapezoidal and delta wings at cruise and moderate lift conditions. Low-speed/high angle-of-attack results show that all wings have significant stability problems above an angle of attack of 20 deg. Aircraft sizing analysis results show that the advanced cranked-wing configurations are significantly lighter, based upon take-off gross weight, than either the trapezoidal or the delta wings.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1857
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Space Applications of Automation, Robotics and Machine Intelligence Systems (ARAMIS), phase 2. Volume 2: Telepresence project applications (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The field of telepresence is defined and overviews of those capabilities that are now available, and those that will be required to support a NASA telepresence effort are provided. Investigation of NASA' plans and goals with regard to telepresence, extensive literature search for materials relating to relevant technologies, a description of these technologies and their state of the art, and projections for advances in these technologies over the next decade are included.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-3735 , NAS 1.26:3735 , SSL-31-83
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 9
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    Space Applications of Automation, Robotics and Machine Intelligence Systems (ARAMIS), phase 2. Volume 1: Telepresence technology base development (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The field of telepresence is defined, and overviews of those capabilities that are now available, and those that will be required to support a NASA telepresence effort are provided. Investigation of NASA's plans and goals with regard to telepresence, extensive literature search for materials relating to relevant technologies, a description of these technologies and their state of the art, and projections for advances in these technologies over the next decade are included. Several space projects are examined in detail to determine what capabilities are required of a telepresence system in order to accomplish various tasks, such as servicing and assembly. The key operational and technological areas are identified, conclusions and recommendations are made for further research, and an example developmental program is presented, leading to an operational telepresence servicer.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA-CR-3734 , NAS 1.26:3734 , SSL-30-83
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 10
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    Application of in-flight thrust determination uncertainty (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A numerical example is given of a previously proposed methodology for the evaluation of in-flight thrust measurement uncertainty, using data extracted from a performance report comparing two different missile prototypes under a variety of flight conditions. Attention is given to the data for the AGM-68B Air Launched Cruise Missile, which is powered by the F107 dual-spool, mixed flow turbofan engine. Assessments are made of the definition of the measurement process, instrumentation error estimation, the propagation of errors to thrust calculation, mathematical model errors, the in-flight thrust error component, and correction to standard conditions. It is concluded that in-flight thrust measurement uncertainty limits can be evaluated from measurement system error analysis results and test data for the missile evaluation process presently described.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 831439
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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