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  • 1
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    Rapid scanning magnet power supply for a high resolution mass spectrometer (1980)
    American Institute of Physics
    Details
    Publication Date: 1980-01-01
    Print ISSN: 0034-6748
    Electronic ISSN: 1089-7623
    Topics: Electrical Engineering, Measurement and Control Technology , Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 2
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    VIII. On the Discovery of Whale Remains in the Clays of the Carse of Stirling (1879)
    Geological Society of London
    Details
    Publication Date: 1879-01-01
    Print ISSN: 0371-7224
    Electronic ISSN: 2052-9422
    Topics: Geosciences
    Published by Geological Society of London
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    PAPER CURRENT
  • 3
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    Development of the HIDEC inlet integration mode (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The Highly Integrated Digital Electronic Control (HIDEC) development program conducted at NASA-Ames/Dryden will use an F-15 test aircraft for flight demonstration. An account is presently given of the HIDEC Inlet Integration mode's design concept, control law, and test aircraft implementation, with a view to its performance benefits. The enhancement of performance is a function of the use of Digital Electronic Engine Control corrected engine airflow computations to improve the scheduling of inlet ramp positions in real time; excess thrust can thereby be increased by 13 percent at Mach 2.3 and 40,000 ft. Aircraft supportability is also improved through the obviation of inlet controllers.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME, Transactions, Journal of Engineering for Gas Turbines and Power (ISSN 0022-0825); 112; 565-572
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    NASA/RAE collaboration on nonlinear control using the F-8C digital fly-by-wire aircraft (1983)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A cooperative advanced digital research experiment (CADRE) was established by the National Aeronautics and Space Administration (NASA) and the Royal Aircraft Establishment (RAE), in which nonlinear control algorithms developed by the RAE were tested on the F-8C digital fly-by-wire (DFBW) aircraft based at the Dryden Flight Research Facility. In the initial phase of the collaboration, some variable-gain algorithms, referred to collectively as variable integral control to optimize response (VICTOR) algorithms, were fight tested. With VICTOR, various measures available within the control system are used to vary gains and time-constants within the closed loop and thereby enhance the control capability of the system, while reducing the adverse effects of sensor noise on the control surfaces. A review of design procedures for VICTOR and results of preliminary flight tests are presented. the F-8C aircraft is operated in the remotely augmented vehicle (RAV) mode, with the control laws implemented as FORTRAN programs on a ground-based computer. Pilot commands and sensor information are telemetered to the ground, where the data are processed to form surface commands which are then telemetered to the ground, where the data are processed to form surface commands which are then telemetered back to the aircraft. The RAV mode represents a single-string (simplex) system and is therefore vulnerable to a hardover since comparison monitoring is not possible. Hence, extensive error checking is conducted on both the ground and airborne computers to prevent the development of potentially hazardous situations. Experience with the RAV monitoring and validation procedures is described.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AGARD Advan. in Guidance and Control Systems; 17 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Development of HIDEC adaptive engine control systems (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The purpose of NASA's Highly Integrated Digital Electronic Control (HIDEC) flight research program is the development of integrated flight propulsion control modes, and the evaluation of their benefits aboard an F-15 test aircraft. HIDEC program phases are discussed, with attention to the Adaptive Engine Control System (ADECS I); this involves the upgrading of PW1128 engines for operation at higher engine pressure ratios and the production of greater thrust. ADECS II will involve the development of a constant thrust mode which will significantly reduce turbine operating temperatures.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 86-GT-252
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    HIDEC adaptive engine control system flight evaluation results (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An integrated flight propulsion control mode, the Adaptive Engine Control System (ADECS), has been developed and flight tested on an F-15 aircraft as part of the NASA Highly Integrated Digital Electronic Control program. The ADECS system realizes additional engine thrust by increasing the engine pressure ratio (EPR) at intermediate and afterburning power, with the amount of EPR uptrim modulated using a predictor scheme for angle-of-attack and sideslip angle. Substantial improvement in aircraft and engine performance was demonstrated, with a 16 percent rate of climb increase, a 14 percent reduction in time to climb, and a 15 percent reduction in time to accelerate. Significant EPR uptrim capability was found with angles-of-attack up to 20 degrees.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 87-GT-257
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Flight test experience with pilot-induced-oscillation suppressor filters (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Digital flight control systems are popular for their flexibility, reliability, and power; however, their use sometimes results in deficient handling qualities, including pilot-induced oscillation (PIO), which can require extensive redesign of the control system. When redesign is not immediately possible, temporary solutions, such as the PIO suppression (PIOS) filter developed for the Space Shuttle, have been proposed. To determine the effectiveness of such PIOS filters on more conventional, high-performance aircraft, three experiments were performed using the NASA F-8 digital fly-by-wire and USAF/Calspan NT-33 variable-stability aircraft. Two types of PIOS filters were evaluated, using high-gain, precision tasks (close formation, probe-and-drogue refueling, and precision touch-and-go landing) with a time delay or a first-order lag added to make the aircraft prone to PIO. Various configurations of the PIOS filter were evaluated in the flight programs, and most of the PIOS filter configurations reduced the occurrence of PIOs and improved the handling qualities of the PIO-prone aircraft. These experiments also confirmed the influence of high-gain tasks and excessive control system time delay in evoking pilot-induced oscillations.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 83-2107
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    NASA/RAE collaboration on nonlinear control using the F-8C digital fly-by-wire aircraft (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Design procedures are reviewed for variable integral control to optimize response (VICTOR) algorithms and results of preliminary flight tests are presented. The F-8C aircraft is operated in the remotely augmented vehicle (RAV) mode, with the control laws implemented as FORTRAN programs on a ground-based computer. Pilot commands and sensor information are telemetered to the ground, where the data are processed to form surface commands which are then telemetered back to the aircraft. The RAV mode represents a singlestring (simplex) system and is therefore vulnerable to a hardover since comparison monitoring is not possible. Hence, extensive error checking is conducted on both the ground and airborne computers to prevent the development of potentially hazardous situations. Experience with the RAV monitoring and validation procedures is described.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-84296 , A-9076 , NAS 1.15:84296
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    A project management system for the X-29A flight test program (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The project-management system developed for NASA's participation in the X-29A aircraft development program is characterized from a theoretical perspective, as an example of a system appropriate to advanced, highly integrated technology projects. System-control theory is applied to the analysis of classical project-management techniques and structures, which are found to be of closed-loop multivariable type; and the effects of increasing project complexity and integration are evaluated. The importance of information flow, sampling frequency, information holding, and delays is stressed. The X-29A system is developed in four stages: establishment of overall objectives and requirements, determination of information processes (block diagrams) definition of personnel functional roles and relationships, and development of a detailed work-breakdown structure. The resulting system is shown to require a greater information flow to management than conventional methods. Sample block diagrams are provided.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-2712
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Dual Engine application of the Performance Seeking Control algorithm (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Dual Engine Performance Seeking Control (PSC) flight/propulsion optimization program has been developed and will be flown during the second quarter of 1993. Previously, only single engine optimization was possible due to the limited capability of the on-board computer. The implementation of Dual Engine PSC has been made possible with the addition of a new state-of-the-art, higher throughput computer. As a result, the single engine PSC performance improvements already flown will be demonstrated on both engines, simultaneously. Dual Engine PSC will make it possible to directly compare aircraft performance with and without the improvements generated by PSC. With the additional thrust achieved with PSC, significant improvements in acceleration times and time to climb will be possible. PSC is also able to reduce deceleration time from supersonic speeds. This paper traces the history of the PSC program, describes the basic components of PSC, discusses the development and implementation of Dual Engine PSC including additions to the code, and presents predictions of the impact of Dual Engine PSC on aircraft performance.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 93-1822 , AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit; Jun 28, 1993 - Jun 30, 1993; Monterey, CA; United States|; 13 p.
    Format: text
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    NASA TECHNICAL REPORTS
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