A new fault-tolerant system software concept employing the primary digital computers as host for the backup software portion has been implemented and flight tested in the F-8 digital fly-by-wire airplane. The system was implemented in such a way that essentially no transients occurred in transferring from primary to backup software. This was accomplished without a significant increase in the complexity of the backup software. The primary digital system was frame synchronized, which provided several advantages in implementing the resident backup software system. Since the time of the flight tests, two other flight vehicle programs have made a commitment to incorporate resident backup software similar in nature to the system described in this...
Flight tests conducted with the self-repairing flight control system (SRFCS) installed on the NASA F...
The capabilities and performance of various fault detection and accommodation (FDA) schemes in exist...
The requirements for fault-tolerant computers for flight control of commercial aircraft are examined...
The development and verification of the Backup Flight System software (BFS) is discussed. The approa...
Concepts for software to implement real time aircraft control systems on a centralized digital compu...
A redundant three axis analog control system was designed and developed to back up a digital fly by ...
To assess the feasibility of a digital fly-by-wire system, the mechanical flight control system of a...
The design, implementation, and verification of the flight control software used in the F-8 DFBW pro...
A generic software error in the quadruply redundant primary flight system could result in the catast...
A highly-reliable, fault-tolerant reconfigurable computer system for aircraft applications was devel...
The software for the Backup Flight Control System Functional Evaluator (BFCSFE) on a Data General Co...
The wing on the NASA F-111 transonic aircraft technology airplane was modified to provide flexible l...
The major aim of this study is to investigate the feasibility of using systems-based failure detecti...
A triplex digital fly by wire flight control system was developed and installed in an F-8C aircraft ...
The feasibility of using digital fly-by-wire systems to control aircraft was demonstrated by develop...
Flight tests conducted with the self-repairing flight control system (SRFCS) installed on the NASA F...
The capabilities and performance of various fault detection and accommodation (FDA) schemes in exist...
The requirements for fault-tolerant computers for flight control of commercial aircraft are examined...
The development and verification of the Backup Flight System software (BFS) is discussed. The approa...
Concepts for software to implement real time aircraft control systems on a centralized digital compu...
A redundant three axis analog control system was designed and developed to back up a digital fly by ...
To assess the feasibility of a digital fly-by-wire system, the mechanical flight control system of a...
The design, implementation, and verification of the flight control software used in the F-8 DFBW pro...
A generic software error in the quadruply redundant primary flight system could result in the catast...
A highly-reliable, fault-tolerant reconfigurable computer system for aircraft applications was devel...
The software for the Backup Flight Control System Functional Evaluator (BFCSFE) on a Data General Co...
The wing on the NASA F-111 transonic aircraft technology airplane was modified to provide flexible l...
The major aim of this study is to investigate the feasibility of using systems-based failure detecti...
A triplex digital fly by wire flight control system was developed and installed in an F-8C aircraft ...
The feasibility of using digital fly-by-wire systems to control aircraft was demonstrated by develop...
Flight tests conducted with the self-repairing flight control system (SRFCS) installed on the NASA F...
The capabilities and performance of various fault detection and accommodation (FDA) schemes in exist...
The requirements for fault-tolerant computers for flight control of commercial aircraft are examined...