Self-testing digital flight control applications

Hendrick, R. C.; Hill, Charles W. L.

doi:10.2514/6.1975-568

Cited by 4 publications

(1 citation statement)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Systems have been imPresented as Paper 79-1704 at the AIAA Guidance and Control Conference, Boulder, Colo., Aug. [6][7][8]1979 plemented and flown, demonstrating and verifying the crucial self-monitoring issues. 2 " 4 Techniques used in these systems are largely accepted in the industry, and have been incorporated in various digital flight-control applications.…”

Section: Introductionmentioning

confidence: 99%

DC-9-80 Digital Flight Guidance System Monitoring Techniques

Osder¹

1981

Journal of Guidance and Control

View full text Add to dashboard Cite

The DC-9-80 aircraft is equipped with an integrated digital flight guidance system that provides autopilot, flight director, thrust management, speed control, autothrottle, and stability augmentation within a single computer complex. The system architecture is based on two essentially autonomous computer complexes, each able to provide all of these functions, with complete fail-passive monitoring for all flight-critical functions, including category III A autoland. This paper describes how the multiplicity of hardware and software monitors are implemented, and how their effectiveness has been analyzed and verified. The system monitors are designed so that fault detection and appropriate shutdown of the failed elements can meet the quantitative safety criteria required by the civil aviation certificating agencies.

show abstract

Section: Introductionmentioning

confidence: 99%

DC-9-80 Digital Flight Guidance System Monitoring Techniques

Osder¹

1981

Journal of Guidance and Control

View full text Add to dashboard Cite

show abstract

Specific failure identification algorithms for the F-8

Hartmann

Stein

1976

1976 IEEE Conference on Decision and Control Including the 15th Symposium on Adaptive Processes

View full text Add to dashboard Cite

Analytical redundancy is applied to the pitch axis of an aircraft to enhance sensor fault detection. Three different designs based on monitoring Kalman filter residuals or likelihood functions were developed. Sensor failures were simulated to evaluate the performance of the algorithms on a non-linear simulation of an F-8C aircraft. Based on requirements for sensor fault detection and preliminary simulator performance it is concluded that these algorithms have the potential for reducing the level of sensor redundancy in a digital flight control system without compromising performance.

show abstract

Architecture Considerations for Digital Automatic Flight Control Systems

Osder

1975

IEEE Trans. Aerosp. Electron. Syst.

View full text Add to dashboard Cite

Self-testing digital flight control applications

Cited by 4 publications

References 0 publications

DC-9-80 Digital Flight Guidance System Monitoring Techniques

DC-9-80 Digital Flight Guidance System Monitoring Techniques

Specific failure identification algorithms for the F-8

Architecture Considerations for Digital Automatic Flight Control Systems

Contact Info

Product

Resources

About