A review of avionics requirements for general aviation
Avionics requirements for general aviation aircraft to reduce pilot errors
Gee, S. W.↗
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Integrated supersonic transport avionics
Integrating avionic subsystems into advanced supersonic transport configurations
Head, R. M.↗
Research directed toward determination of advanced avionics technology for a V/STOL aircraft program Final report
Flight control system design data and helicopter simulation data for V/STOL aircraft advanced avionic technology
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The NASA-ERC V/STOL avionics systems technology program.
NASA program for developing avionics to provide V/STOL with reliable performance under instrument conditions
Bretoi, R. N.↗
A conceptual design of the space shuttle integrated avionics system
Conceptual design development of space shuttle integrated avionics system emphasizing necessary electronics systems
Digesu, F. E.↗
Integrated avionics architecture
Design considerations for integrated avionics system for aircraft and manned space vehicles
Petrie, D. M.↗
Standard interface definition for avionics data bus systems
Data bus for avionics system of space shuttle, noting functions of interface unit, error detection and recovery, redundancy, and bus control philosophy
Kosmala, A. L.↗
Advanced software techniques for data management systems. Volume 1: Study of software aspects of the phase B space shuttle avionics system
An overview of the executive system design task is presented. The flight software executive system, software verification, phase B baseline avionics system review, higher order languages and compilers, and computer hardware features are also discussed.
Martin, F. H.↗
Shuttle avionics and the goal language including the impact of error detection and redundancy management
The relationship is examined between the space shuttle onboard avionics and the ground test computer language GOAL when used in the onboard computers. The study is aimed at providing system analysis support to the feasibility analysis of a GOAL to HAL translator, where HAL is the language used to program the onboard computers for flight. The subject is dealt with in three aspects. First, the system configuration at checkout, the general checkout and launch sequences, and the inventory of subsystems are described. Secondly, the hierarchic organization of onboard software and different ways of introducing GOAL-derived software onboard are described. Also the flow of commands and test data during checkout is diagrammed. Finally, possible impact of error detection and redundancy management on the GOAL language is discussed.
Flanders, J. H.↗
Space tug point design study. Volume 3: Design definition. Part 1: Propulsion and mechanical, avionics, thermal control and electrical power subsystems
A study was conducted to determine the configuration and performance of a space tug. Details of the space tug systems are presented to include: (1) propulsion systems, (2) avionics, (3) thermal control, and (4) electric power subsystems. The data generated include engineering drawings, schematics, subsystem operation, and component description. Various options investigated and the rational for the point design selection are analyzed.
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Space shuttle program: Shuttle Avionics Integration Laboratory. Volume 7: Logistics management plan
The logistics management plan for the shuttle avionics integration laboratory defines the organization, disciplines, and methodology for managing and controlling logistics support. Those elements requiring management include maintainability and reliability, maintenance planning, support and test equipment, supply support, transportation and handling, technical data, facilities, personnel and training, funding, and management data.
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Analysis of technology requirements and potential demand for general aviation avionics systems for operation in the 1980's
Avionics systems are identified which promise to reduce economic constraints and provide significant improvements in performance, operational capability and utility for general aviation aircraft in the 1980's.
Cohn, D. M.↗
Shuttle avionics integration laboratory: Sail project plan, space shuttle program, volume 1
The establishment of the Shuttle Avionica Integration Laboratory (SAIL) for performing avionics system integrated testing is discussed. The specific functions of the SAIL are described, and the organization and management methods are detailed.
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Space Tug Avionics Definition Study. Volume 5: Cost and Programmatics
The baseline avionics system features a central digital computer that integrates the functions of all the space tug subsystems by means of a redundant digital data bus. The central computer consists of dual central processor units, dual input/output processors, and a fault tolerant memory, utilizing internal redundancy and error checking. Three electronically steerable phased arrays provide downlink transmission from any tug attitude directly to ground or via TDRS. Six laser gyros and six accelerometers in a dodecahedron configuration make up the inertial measurement unit. Both a scanning laser radar and a TV system, employing strobe lamps, are required as acquisition and docking sensors. Primary dc power at a nominal 28 volts is supplied from dual lightweight, thermally integrated fuel cells which operate from propellant grade reactants out of the main tanks.
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Space shuttle orbiter avionics software. Systems analysis flight software and SDL analysis reports
Results are presented of systems analyses of the avionics software of the space shuttle orbiter.
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Transcription of the Workshop on General Aviation Advanced Avionics Systems
Papers are presented dealing with the design of reliable, low cost, advanced avionics systems applicable to general aviation in the 1980's and beyond. Sensors, displays, integrated circuits, microprocessors, and minicomputers are among the topics discussed.
Tashker, M.↗
Shuttle avionics system
The avionics system of the Space Shuttle is designed in a fail operational/fail safe architecture. The guidance, navigation and control system is implemented, through the onboard Orbiter digital computers. Guidance, navigation and control sensors are triplex, while the flight control effectors are mechanized either in load sharing or quad structure. Two sets of basic flight instruments and controls are provided along with electronic interfaces to allow for multiple selection of input destination and display source selection. Communications, tracking and instrumentation subsystems are mechanized as a dual hardware design for key operational elements. The data processing system allows for quad, triplex, dual or single computer operation. The power distribution subsystem provides a triple bus system with appropriate tie elements. A functional description is given of the computer system, the data bus, the mass memory unit, the multiplexer/demultiplexer and the CRT display system.
Gardiner, R. A.↗