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  • Inorganic Chemistry  (7,503)
  • Aircraft Design, Testing and Performance
  • 1990-1994  (3,672)
  • 1930-1934  (3,900)
Collection
Keywords
Publisher
Years
Year
  • 1
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    Airplane takeoff and landing performance monitoring system (1991)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The invention is a real-time takeoff and landing performance monitoring system for an aircraft which provides a pilot with graphic and metric information to assist in decisions related to achieving rotation speed (V.sub.R) within the safe zone of a runway, or stopping the aircraft on the runway after landing or take-off abort. The system processes information in two segments: a pretakeoff segment and a real-time segment. One-time inputs of ambient conditions and airplane configuration information are used in the pretakeoff segment to generate scheduled performance data. The real-time segment uses the scheduled performance data, runway length data and transducer measured parameters to monitor the performance of the airplane throughout the takeoff roll. Airplane and engine performance deficiencies are detected and annunciated. A novel and important feature of this segment is that it updates the estimated runway rolling friction coefficient. Airplane performance predictions also reflect changes in head wind occurring as the takeoff roll progresses. The system provides a head-down display and a head-up display. The head-up display is projected onto a partially reflective transparent surface through which the pilot views the runway. By comparing the present performance of the airplane with a predicted nominal performance based upon given conditions, performance deficiencies are detected by the system.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Method and system for monitoring and displaying engine performance parameters (1991)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The invention is a method and system for monitoring and directly displaying the actual thrust produced by a jet aircraft engine under determined operating conditions and the available thrust and predicted (commanded) thrust of a functional model of an ideal engine under the same determined operating conditions. A first set of actual value output signals representative of a plurality of actual performance parameters of the engine under the determined operating conditions is generated and compared with a second set of predicted value output signals representative of the predicted value of corresponding performance parameters of a functional model of the engine under the determined operating conditions to produce a third set of difference value output signals within a range of normal, caution, or warning limit values. A thrust indicator displays when any one of the actual value output signals is in the warning range while shaping function means shape each of the respective difference output signals as each approaches the limit of the respective normal, caution, and warning range limits.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Inflow Meaurements Made with a Laser Velocimeter on a Helicopter Model in Forward Flight. Volume 10: Rectangular Planform Blades at an Advance Ratio of 0.30, 0.50 Chord above the Tip Path Plane. Data Files (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-08-24
    Description: These data files contain the inflow measurements made with a laser velocimeter on a helicopter model in forward flight, volume X, rectangular planform blades at an advance ratio of .30, .50 chord above the tip path plane.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TM-102644-SUPPL
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Flexible connector for use in aircraft (1992)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The invention concerns a connector, in an aircraft engine, for mounting a ring to a turbine rotor which the ring surrounds. The ring carries propeller blades, and the connector transmits both thrust and torque loads between the ring and the rotor, without significant deformation. However, the connector does deform in order to accommodate differential thermal growth between the ring and the rotor.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The Design of an Ultra High Capacity Long Range Transport Aircraft (1993)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: This paper examines the design of a 650 passenger aircraft with 8000 nautical mile range to reduce seat mile cost and to reduce airport and airway congestion. This design effort involves the usual issues that require trades between technologies, but must also include consideration of: airport terminal facilities; passenger loading and unloading; and, defeating the 'square-cube' law to design large structures. This paper will review the long range ultra high capacity or megatransport design problem and the variety of solutions developed by senior student design teams at Purdue University.
    Keywords: Aircraft Design, Testing and Performance
    Type: Proceedings of the Ninth Annual Summer Conference: NASA/USRA University Advanced Design Program; 101-111; EP-309
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    The Design of a Primary Flight Trainer using Concurrent Engineering Concepts (1993)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Concurrent Engineering (CE) concepts seek to coordinate the expertise of various disciplines from initial design configuration selection through product disposal so that cost efficient design solutions may be achieve. Integrating this methodology into an undergraduate design course sequence may provide a needed enhancement to engineering education. The Advanced Design Program (ADP) project at Embry-Riddle Aeronautical University (EMU) is focused on developing recommendations for the general aviation Primary Flight Trainer (PFT) of the twenty first century using methods of CE. This project, over the next two years, will continue synthesizing the collective knowledge of teams composed of engineering students along with students from other degree programs, their faculty, and key industry representatives. During the past year (Phase I). conventional trainer configurations that comply with current regulations and existing technologies have been evaluated. Phase I efforts have resulted in two baseline concepts, a high-wing, conventional design named Triton and a low-wing, mid-engine configuration called Viper. In the second and third years (Phases II and III). applications of advanced propulsion, advanced materials, and unconventional airplane configurations along with military and commercial technologies which are anticipated to be within the economic range of general aviation by the year 2000, will be considered.
    Keywords: Aircraft Design, Testing and Performance
    Type: Proceedings of the Ninth Annual Summer Conference: NASA/USRA University Advanced Design Program; 26-37; EP-309
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Corporate Jet (1991)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Gulfstream Aerospace Corporation, Savannah, GA, used a version of a NASA program called WIBCO to design a wing for the Gulfstream IV (G-IV) which will help to reduce transonic drag (created by shock waves that develop as an airplane approaches the speed of sound). The G-IV cruises at 88 percent of the speed of sound, and holds the international record in its class for round-the-world flight. They also used the STANS5 and Profile programs in the design. They will use the NASA program GASP to help determine the gross weight, range, speed, payload and optimum wing area of an intercontinental supersonic business jet being developed in cooperation with Sukhoi Design Bureau, a Soviet organization.
    Keywords: Aircraft Design, Testing and Performance
    Type: Spinoff 1991; 74-75; NASA-NP-147
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Propeller speed and phase sensor (1992)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A speed and phase sensor counterrotates aircraft propellers. A toothed wheel is attached to each propeller, and the teeth trigger a sensor as they pass, producing a sequence of signals. From the sequence of signals, rotational speed of each propeller is computer based on time intervals between successive signals. The speed can be computed several times during one revolution, thus giving speed information which is highly up-to-date. Given that spacing between teeth may not be uniform, the signals produced may be nonuniform in time. Error coefficients are derived to correct for nonuniformities in the resulting signals, thus allowing accurate speed to be computed despite the spacing nonuniformities. Phase can be viewed as the relative rotational position of one propeller with respect to the other, but measured at a fixed time. Phase is computed from the signals.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Counterrotating aircraft propulsor blades (1993)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A propulsor blade for an aircraft engine includes an airfoil section formed in the shape of a scimitar. A metallic blade spar is interposed between opposed surfaces of the blade and is bonded to the surfaces to establish structural integrity of the blade. The metallic blade spar includes a root end allowing attachment of the blade to the engine.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Power turbine ventilation system (1991)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Air control mechanism within a power turbine section of a gas turbine engine. The power turbine section includes a rotor and at least one variable pitch propulsor blade. The propulsor blade is coupled to and extends radially outwardly of the rotor. A first annular fairing is rotatable with the propulsor blade and interposed between the propulsor blade and the rotor. A second fairing is located longitudinally adjacent to the first fairing. The first fairing and the second fairing are differentially rotatable. The air control mechanism includes a platform fixedly coupled to a radially inner end of the propulsor blade. The platform is generally positioned in a first opening and a first fairing. The platform and the first fairing define an outer space. In a first position corresponding with a first propulsor blade pitch, the platform is substantially conformal with the first fairing. In a second position corresponding with the second propulsor blade pitch, an edge portion of the platform is displaced radially outwardly from the first fairing. When the blades are in the second position and rotating about the engine axis, the displacement of the edge portion with respect to the first fairing allows air to flow from the outer space to the annular cavity.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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