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  • AIRCRAFT  (118)
  • 2020-2024
  • 2010-2014
  • 1970-1974  (118)
  • 1955-1959
  • 1945-1949
  • 1973  (118)
Collection
Keywords
Years
  • 2020-2024
  • 2010-2014
  • 1970-1974  (118)
  • 1955-1959
  • 1945-1949
Year
  • 1
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    Qualification flight tests of the Viking decelerator system. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Balloon Launched Decelerator Test (BLDT) series conducted at White Sands Missile Range (WSMR) during July and August of 1972 flight qualified the NASA Viking '75 decelerator system at conditions bracketing those expected for Mars. This paper discusses the decelerator system design requiremnts, compares the test results with prior work, and discusses significant considerations leading to successful qualification in earth's atmosphere. The Viking decelerator system consists of a single-stage mortar-deployed 53-foot nominal diameter disk-gap-band parachute. Full-scale parachutes were deployed behind a full-scale simulated Viking vehicle at Mach numbers from 0.47 to 2.18 and dynamic pressures from 6.9 to 14.6 psf. Analyses show that the system is qualified with sufficient margin to perform successfully for the Viking mission.
    Keywords: AIRCRAFT
    Type: AIAA PAPER 73-457 , Aerodynamic Deceleration Systems Conference; May 21, 1973 - May 23, 1973; Palm Springs, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Performance of a ballute decelerator towed behind a jet airplane (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An F-104B airplane was modified to investigate the drag and stability characteristics of a ballute decelerator in the wake of an asymmetrical airplane. Decelerator deployments were initiated at a Mach number of 1.3 and an altitude of 15,240 meters (50,000 feet) and terminated when the airplane had decelerated to a Mach number of 0.5. The flight tests indicated that the decelerator had a short inflation time with relatively small opening forces. The drag levels attained with the subject decelerator were less than those obtained with other high-speed decelerators behind a symmetrical tow vehicle. The ballute demonstrated good stability characteristics behind the testbed airplane.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-56019 , H-815
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Design and fabrication of an aeroelastic flap element for a Short TakeOff and Landing (STOL) aircraft model (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flap element typifying a third element in the flap system of a short takeoff and landing aircraft was designed, fabricated, and instrumented. It was delivered to NASA for flight-simulated testing. The flap element was aluminum skin-stringer-rib construction with adhesive laminated skins. The tests conducted were as follows: (1) sonic check, (2) thermal expansion, (3) end fitting stiffness, (4) material properties, (5) maximum bending stress in the skin, and (6) effective skin width and stringer spacing.
    Keywords: AIRCRAFT
    Type: NASA-CR-132339 , D6-41253
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Results of the flight noise measurement program using a standard and modified SH-3A helicopter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A field noise measurement program has been conducted using both a standard SH-3A helicopter and an SH-3A helicopter modified to reduce external noise levels. Modifications included reducing rotor speed, increasing the number of rotor blades, modifying the blade-tip shapes, and acoustically treating the engine air intakes and exhaust. The purpose of this study was to document the noise characteristics recorded on the ground of each helicopter during flyby, hover, landing, and take-off operations. Based on an analysis of the measured results, the average of the overhead, overall, ontrack noise levels was approximately 4 db lower for the modified helicopter than for the standard helicopter. The improved in-flight noise characteristics, and associated small footprint areas and time durations, were judged to be mainly due to tail-rotor noise reductions. The noise reductions were obtained at the expense of required power increases at airspeeds greater than 70 knots for the modified helicopter.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7330 , L-8950
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Results of the noise measurement program on a standard and modified OH-6A helicopter (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A field noise measurement program has been conducted on a standard OH-6A helicopter and one that had been modified by reducing the rotor speed, altering rotor tip shape, and treating the engine exhaust and inlet to reduce the external noise levels. The modifications consisted of extensive aircraft design changes resulting in substantial noise reductions following state-of-art noise reduction techniques. The purpose of this study was to document the ground noise characteristics of each helicopter during flyover, hover, landing, and take-off operations. Based on an analysis of the measured results, the average of the overall on-track noise levels of the final modified helicopter was approximately 14 db lower than that for the standard helicopter. Narrow-band-spectra data of the hovering helicopter show a reduction in the overall noise due to the reductions achieved for the lifting main and antitorque tail rotor, engine exhaust, and gear box noise for the modified helicopter. The noise results of the test program are found to correlate generally with noise measurements made previously on this type of aircraft.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7216 , L-8129
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Experimental and analytical determination of stability parameters for a balloon tethered in a wind (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental and analytical techniques for determining stability parameters for a balloon tethered in a steady wind are described. These techniques are applied to a particular 7.64-meter-long balloon, and the results are presented. The stability parameters of interest appear as coefficients in linearized stability equations and are derived from the various forces and moments acting on the balloon. In several cases the results from the experimental and analytical techniques are compared and suggestions are given as to which techniques are the most practical means of determining values for the stability parameters.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7222 , L-8524
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Effectiveness evaluation of STOL transport operations (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A short-takeoff and landing (STOL) systems simulation model has been developed and implemented in a computer code (known as STOL OPS) which permits evaluation of the operation of a STOL aircraft and its avionics in a commercial airline operating environment. STOL OPS concentrated on the avionics functions of navigation, guidance, control, communication, hazard aviodance, and systems management. External world factors influencing the operation of the STOL aircraft include each airport and its geometry, air traffic at each airport, air traffic control equipment and procedures, weather (including winds and visibility), and the flight path between each airport served by the route. The development of the STOL OPS program provides NASA a set of computer programs which can be used for detailed analysis of a STOL aircraft and its avionics and permit establishment of system requirements as a function of airline mission performance goals.
    Keywords: AIRCRAFT
    Type: NASA-CR-114631
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    The Influence of Wing Loading on Turbofan Powered STOL Transports with and Without Externally Blown Flaps (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of wing loading on the design of short takeoff and landing (STOL) transports using (1) mechanical flap systems, and (2) externally blown flap systems are determined. Aircraft incorporating each high-lift method are sized for field lengths of 2,000 feet, 2,500 feet, and 3,500 feet, and for payloads of 40, 150, and 300 passengers, for a total of 18 point-design aircraft. An assumed 1975 level of technology is applied to both concepts in terms of propulsion, weights, active controls, supercritical wing methodology, and acoustics. Low-wing-loading STOL configurations with mechanical flaps are found to be competitive with externally blown flap STOL configurations over wide ranges of payload and field length for the airworthiness rules and technology improvements assumed. Because the results of design studies like this one are sensitive to the ground rules assumed, careful attention is paid to describing the assumptions. These assumptions must be understood before the results are compared with other STOL airplane studies.
    Keywords: AIRCRAFT
    Type: NASA-CR-2320 , D3-8514-7
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Flight director design for a STOL aircraft. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The study described here was intended to explore some ways of giving the pilot the information necessary to perform as well as an autopilot. A fixed-base flight simulator was built to study pilot/director/aircraft performance. Instrument rated pilots used the different director-displays in an approach down to touchdown, including a flare and decrab maneuver. Two well established areas of control theory are combined in the design of the cockpit display. Optimal control theory and the theory of manual control are used to find the feedback gains required to drive the display symbols. Conclusions based on the simulator are presented. The results show that the director display developed in the work provides more than adequate information for simulated landing in highly turbulent conditions.
    Keywords: AIRCRAFT
    Type: Journal of Aircraft; 10; Aug. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    V/STOL tilt rotor aircraft study. Volume 7: Tilt rotor flight control program feedback studies (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An exploratory study has been made of the use of feedback control in tilt rotor aircraft. This has included the use of swashplate cyclic and collective controls and direct lift control. Various sensor and feedback systems are evaluated in relation to blade loads alleviation, improvement in flying qualities, and modal suppression. Recommendations are made regarding additional analytical and wind tunnel investigations and development of feedback systems in the full scale flight vehicle. Estimated costs and schedules are given.
    Keywords: AIRCRAFT
    Type: NASA-CR-114600 , D222-10060-3-VOL-7
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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