Analytical Sensor Redundancy Assessment

Mulcare, D. B.; Downing, L. E.; Smith, M. K.

i

Analytical Sensor Redundancy Assessment

1988-04-01
By Mulcare, D. B. ; Downing, L. E. ; Smith, M. K.

File Language:

English

Details

Creators:

Mulcare, D. B. ; Downing, L. E. ; Smith, M. K.
Corporate Creators:

Lockheed-California Company
Corporate Contributors:

United States. Department of Transportation. Federal Aviation Administration. Technical Center
Subject/TRT Terms:

Aerodynamic Stability Airplanes Control Systems Fault Tolerant Computing
Publication/ Report Number:

DOT/FAA/CT-86/32
Resource Type:

Tech Report
Geographical Coverage:

United States
Corporate Publisher:

United States. Department of Transportation. Federal Aviation Administration. William J. Hughes Technical Center
Abstract:

The rationale and mechanization of sensor fault tolerance based on analytical redundancy principles are described. The concept involves the substitution of software procedures, such as an observer algorithm, to supplant additional hardware components. The observer synthesizes values of sensor states in lieu of their direct measurement. Such information can then be used, for example, to determine which of two disagreeing sensors is more correct, thus enhancing sensor fault survivability. Here a stability augmentation system is used as an example application, with required modifications being made to a quadruplex digital flight control system. The impact on software structure and the resultant revalidation effort are illustrated as well. Also, the use of an observer algorithm for wind gust filtering of the angle-of-attack sensor signal is presented.
Format:

PDF
Collection(s):

FAA William J. Hughes Technical Center for Advanced Aerospace
Main Document Checksum:

urn:sha-512:9744c1089fa1bec0d9797ef425c6faf3d19ea1e41666b060ad8503d21122ec63f38356592ce4098587ee0add1f850b4e11ac34f4deba5d4df6d339c2159cd708
Download URL:

https://rosap.ntl.bts.gov/view/dot/92812/dot_92812_DS1.pdf
File Type:

[PDF - 1.02 MB ]

File Language:

English

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