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Aerospace and Electronic Systems Magazine, IEEE

Issue 7 • Date July 1992

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Displaying Results 1 - 10 of 10
  • Design of Boeing 777 electric system

    Publication Year: 1992 , Page(s): 4 - 11
    Cited by:  Papers (4)
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (739 KB)  

    The electric power system for the Boeing 777 is comprised of two independent electrical systems, the main and the backup. The main electric system includes two engine-driven integrated drive generators, a generator driven by the auxiliary power unit, three generator control units, and a bus power control unit. The backup electric system includes two engine-drive generators and one integrated converter/control unit to provide the redundancy of electrical sources equivalent to a three-engine airplane. Automation of the system is achieved by the use of state-of-the-art, microprocessor-based control units that perform system control, protection, and built-in-test functions. Each control unit has redundant two-way communication through an ARINC 629 communication bus that requires significantly fewer discrete wires than similar systems, allowing considerable reduction of the interface circuits and reduction in weight.<> View full abstract»

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  • RF optical links

    Publication Year: 1992 , Page(s): 12 - 15
    Cited by:  Papers (1)
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (395 KB)  

    RF photonic links that can be used to supplement gigahertz RF electrical transmission lines without the characteristic attenuation, induced noise, and distortion associated with long cable lengths are discussed. Wavelength division multiplexing (WDM) capabilites are examined in terms of available wavelengths, hardware, and spacing. Typical RF fiber-optic links at 6-18 GHz are addressed with respect to architecture and electrical and optical characteristics. A global Positioning System (GPS) fiber-optic link is presented.<> View full abstract»

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  • The future of military standards. A focus on electronics

    Publication Year: 1992 , Page(s): 16 - 19
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (471 KB)  

    The growing perception that with cutbacks in the military and the changing international economic environment, the military must rely on commercial industries in order to afford the next generation of high-performance and high-reliability military systems is discussed. One issue associated with the question of whether an industrial base for the military can be provided and maintained without major changes in the operation of both the government and commercial industry is examined, namely, whether commercial standards can effectively supplant military standards and still provide high performance and reliability for military missions.<> View full abstract»

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  • A full color AMLCD with NVG class B compatibility

    Publication Year: 1992 , Page(s): 20 - 23
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (256 KB)  

    A full color active-matrix liquid crystal display (AMLCD) with night-vision-goggle (NVG) compatibility is reported. The display is a 5-in-diagonal high-resolution triad (RGB) color pixel with 80*108 color groups per inch (H/V). It has a specially designed high-brightness backlight with low profile and the above-mentioned NVG characteristics. The color coordinates of the unit are almost identical to those of the display without NVG filter, preserving the red color coordinates. This display has full avionic characteristics, such as high contrast at high ambient light and extended temperature range.<> View full abstract»

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  • C-17 flight control system overview

    Publication Year: 1992 , Page(s): 24 - 31
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (671 KB)  

    The basic requirements that drove the design of the McDonnell Douglas C-17 airlifter are examined. The background behind the deep stall avoidance, probability of loss of control, all-engine-out control, and safe go-around requirements is explained, and the overall flight control system (FCS) design is presented, focusing on features that satisfy the above-mentioned requires. Specific failure modes and their design safeguards are reviewed. The early flight test results are presented. Minor anomalies encountered and their effect on the final flight control design are discussed.<> View full abstract»

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  • The C-17 multifunction display: a building block for avionic systems

    Publication Year: 1992 , Page(s): 32 - 39
    Cited by:  Patents (1)
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (596 KB)  

    The multifunction display (MFD) developed for use as the primary cockpit display system on the US Air Force C-17A military air transport is described. The 6-in by 6-in color cathode ray tube (CRT) display features a self-contained 1750 processor and vector generator capable of processing MIL-STD-1553B aircraft data and raster video into any of 10 formats as selected by the pilot or copilot. The MFD can display stroke, raster, or hybrid formats in 16 colors. Raster images are driven by sensor inputs with an RS-170 or RS-343 interface. The CRT uses a taut mask delta gun design and provides the best available brightness and line-width performance. The display features small size, low weight, low power, standard interface, and adaptable software. Reconfigurability in the aircraft is enhanced by using four identical cockpit displays.<> View full abstract»

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  • TALONS 95 GHz radar sensor for autonomous landing guidance

    Publication Year: 1992 , Page(s): 40 - 44
    Cited by:  Papers (1)
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (423 KB)  

    Ground tests of the TALONS (tactical avionics for low-level navigation and strike) 95-GHz radar sensor are reported. Radar backscatter data were taken for a runway/taxiway system at realistic depression angles in various weather conditions to determine the effects of precipitation and fog. The data were analyzed and utilized to produce radar imagery. Radar cross-sections of several tactical targets were also measured. It was found that the conditions encountered during the test program were virtually transparent to 95-GHz energy at the detection ranges required for landing guidance.<> View full abstract»

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  • Resonant sensor for high accuracy pressure measurement using silicon technology

    Publication Year: 1992 , Page(s): 45 - 48
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (343 KB)  

    A resonant-element transducer developed for aerospace applications using micromachined silicon technology is described. The sensor is a beam supported over a square diaphragm. The resonant frequency of the beam is proportional to the applied pressure on the diaphragm. Results presented show that the prototype's performance rivals that of current high-accuracy pressure transducers.<> View full abstract»

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  • Flight management system of the F-117A

    Publication Year: 1992 , Page(s): 49 - 55
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (558 KB)  

    The F-117A night attack aircraft flight management system (FMS) is described. The need for and purpose of the system are described, and the design goals are identified. The various modes and their important features are presented. The pitch and speed control laws are shown.<> View full abstract»

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  • Online identification and control of linearized aircraft dynamics

    Publication Year: 1992 , Page(s): 56 - 60
    Cited by:  Papers (7)
    Save to Project icon | Request Permissions | Click to expandQuick Abstract | PDF file iconPDF (478 KB)  

    An approach for online identification and control that requires weaker excitation than the existing approaches based on least-squares schemes and closed-loop systems is examined. It uses multiple-objective optimization theory to resolve the conflict between identification and controller performance as they compete for the only available resource, the inputs to the aircraft. The approach is applied to a longitudinal model of a representative linearized high-performance aircraft model. Simulation results compare the final controller with a conventional gain-scheduled pitch command augmentation system. It is demonstrated that by allowing some control input to be given to the identification process, the controller's overall performance is improved.<> View full abstract»

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The IEEE Aerospace and Electronic Systems Magazine publishes articles and tutorials concerned with the various aspects of systems for space, air, ocean, or ground environments.

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