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  • 1
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    Description and test results of a digital supersonic propulsion system integrated control (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A digitally implemented integrated inlet/engine control system was developed and tested on a mixed compression, Mach 2.5, supersonic inlet and augmented turbofan engine. The control matched engine airflow to available inlet airflow so that in steady state, the shock would be at the desired location, and the overboard bypass doors would be closed. During engine induced transients, such as augmentor lights and cutoffs, the inlet operating point was momentarily changed to a more supercritical point to minimize unstarts. The digital control also provided automatic inlet restart.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Advanced Control Technol. and its Potential for Future Transport Aircraft; p 503-524
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Role of optical computers in aeronautical control applications (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The role that optical computers play in aircraft control is determined. The optical computer has the potential high speed capability required, especially for matrix/matrix operations. The optical computer also has the potential for handling nonlinear simulations in real time. They are also more compatible with fiber optic signal transmission. Optics also permit the use of passive sensors to measure process variables. No electrical energy need be supplied to the sensor. Complex interfacing between optical sensors and the optical computer is avoided if the optical sensor outputs can be directly processed by the optical computer.
    Keywords: OPTICS
    Type: NASA. Langley Research Center Opt. Inform. Process. for Aerospace Appl.; p 33-43
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Investigation of the starting characteristics of the M-1 rocket engine using the analog computer (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Starting characteristics of M- I liquid propellant rocket engine using analog computer simulation
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-3136
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Optical sensors for aeronautics and space (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A review of some NASA and DOD programs to develop optical sensors with fiberoptics for instrumentation and control is presented. Fiberoptic systems offer some distinct advantages. Noise immunity is one important asset. Fiberoptic systems do not conduct electricity and therefore can be used in and near areas that contain explosive or flammable materials. One objective of these programs is to produce more reliable sensors and to improve the safety and operating economy of future aircraft and space vehicles.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-81407 , E-321
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Fiber optic sensors for measuring angular position and rotational speed (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two optical sensors, a 360 deg rotary encoder and a tachometer, were built for operation with the light source and detectors located remotely from the sensors. The source and detectors were coupled to the passive sensing heads through 3.65 meter fiber optic cables. The rotary encoder and tachometer were subjected to limited environmental testing. They were installed on an air breathing engine during recent altitude tests. Over 100 hours of engine operation were accumulated without any failure of either device.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-81454 , E-381
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Conceptual design of an optic based engine control system (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Use of optics in the aircraft engine control systems would provide immunity to electromagnetic effects (such as lightning, radar, and nuclear pulses) for flight and propulsion control systems located throughout the aircraft and in need of communication and would result in weight reduction. This paper discusses a conceptual design of an optic engine control system that is being developed by the Fiber Optic Control System Integration (FOCSI) program. The features inherent in each of the optic-based components of the optic system, which includes the on-engine full authority digital electonic control, optic sensors, optic-based actuators, and an optic data bus for communication with the aircraft flight control system are described in detail. The diagrams of the FOCSI control system and its components are included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 87-GT-168
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Dynamic response of Mach 2.5 axisymmetric inlet with 40 percent supersonic internal area contraction (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of experimental tests conducted on a supersonic, mixed compression, axisymmetric inlet are presented. The inlet is designed for operation at Mach 2.5 with a turbofan engine (TF-30). The inlet was terminated with either a choked-orifice plate or a long pipe with variable area choked exit plug. Frequency responses were obtained for selected static pressures in the diffuser. These pressures were selected as potential control signals for terminal shock control. Frequency responses were obtained for the Mach 2 and 2.5 conditions for different terminations. Responses also were obtained with and without cowl bleed. Internal disturbances were produced by sinusoidally varying the inlet overboard bypass doors at frequencies out to 100 hertz.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2833 , E-7426
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Experimental dynamic response of a two-dimensional, Mach 2.7, mixed compression inlet (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A test program was conducted on a two-dimensional supersonic inlet. Internal disturbances in diffuser exit mass flow were produced by oscillating overboard bypass doors. Open-loop dynamic responses of shock position, throat exit and diffuser exit static pressures are presented. The steady-state and dynamic coupling between ducts were also obtained. The experimental results from the two-dimensional inlet are compared to results from a similar size axisymmetric inlet and also to a transfer function synthesis program.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-6957 , E-7002
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Terminal-shock and restart control of a Mach 2.5, mixed compression inlet coupled to a turbofan engine (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Results of an experimental program conducted on a mixed-compression inlet coupled to a turbofan engine are presented. Open-loop frequency response data are presented that show the response of shock position (as measured by an average inlet static pressure) to sinusoidal airflow disturbances produced at the compressor face station. Also presented are results showing the effect of different passive terminations (a choke plate or a long duct) on the characteristics of the inlet. Transfer functions obtained by using experimental data are presented and compared to the experimental data. Closed-loop frequency response of shock position (with a proportional-plus-integral controller) is presented. In addition, transient data are presented that show the unstart-restart characteristics of the inlet.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3104 , E-7924
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Digital integrated control of a Mach 2.5 mixed-compression supersonic inlet and an augmented mixed-flow turbofan engine (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A digitally implemented integrated inlet-engine control system was designed and tested on a mixed-compression, axisymmetric, Mach 2.5, supersonic inlet with 45 percent internal supersonic area contraction and a TF30-P-3 augmented turbofan engine. The control matched engine airflow to available inlet airflow. By monitoring inlet terminal shock position and over-board bypass door command, the control adjusted engine speed so that in steady state, the shock would be at the desired location and the overboard bypass doors would be closed. During engine-induced transients, such as augmentor light-off and cutoff, the inlet operating point was momentarily changed to a more supercritical point to minimize unstarts. The digital control also provided automatic inlet restart. A variable inlet throat bleed control, based on throat Mach number, provided additional inlet stability margin.
    Keywords: ELECTRONICS
    Type: NASA-TM-X-3075 , E-7965
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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