A system design that can provide extraordinary avionics reliability for the LHX aircraft has been devised, This system includes self-healing components, funclional and conventional redundancies, and reconfigurable features, There is liHle weight and cost increase over a conventional avionics Installation since some components were eliminated and conventional redundancy was used only in selected situations. Supporting analyses show that LHX needs hig~ reliability if it is to be affordable. New approaches are required since LHX must be more capable than present aircraft. More sensors, target~acquisition aids, and better navigation and communications systems arc required. These systems must be eHectivc in reducing crew workload. These systems must also be unusually reliable; with today's technology, they would cause an unacceptable failure rate and an impossible maintenance burden. The avionics architecture suggested for LHX has the potential for avoiding these drawbacks and, in fact, can provide increased utilization. When combined wilh the functional improvements furnished by the new sensors, the reliability of the LHX will provide high productivity.

LHX system design for improved performance and affordability

The process used in the synthesis of an integrated cockpit management system was discussed. Areas covered included flight displays, subsystem management, checklists, and procedures (both normal and emergency). The process of evolving from the unintegrated conventional system to the integrated system is examined and a brief description of the results presented.

/pdf/synthesis-of-an-integrated-cockpit-management-system-zbx4gq8ag7.pdf

Synthesis of an integrated cockpit management system

Presented is an advanced, fault-tolerant multiprocessor avionics architecture as could be employed in an advanced rotorcraft such as LHX. The processor structure is designed to interface with existing digital avionics systems and concepts including the Army Digital Avionics System (ADAS) cockpit/display system, navaid and communications suites, integrated sensing suite, and the Advanced Digital Optical Control System (ADOCS). The report defines mission, maintenance and safety-of-flight reliability goals as might be expected for an operational LHX aircraft. Based on use of a modular, compact (16-bit) microprocessor card family, results of a preliminary study examining simplex, dual and standby-sparing architectures is presented. Given the stated constraints, it is shown that the dual architecture is best suited to meet reliability goals with minimum hardware and software overhead. The report presents hardware and software design considerations for realizing the architecture including redundancy management requirements and techniques as well as verification and validation needs and methods.

/pdf/investigation-of-an-advanced-fault-tolerant-integrated-10texhho9l.pdf

Investigation of an advanced fault tolerant integrated avionics system

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Investigation of an advanced fault tolerant integrated avionics system