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Cited by 6 publications
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References 17 publications
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“…Extensive research programs led by NASA have focused on designing and validating specific approaches for the design of a number of fault tolerant flight control schemes 1,2 , primarily focused on malfunctions of the actuators of the control surfaces or failures of the propulsion system. However, issues related to sensor failures have been considered of lower priority, mainly due to the fact that triple or quadruple physical redundancy on the sensor suite, along with the implementation of Built-In Testing (BIT) and/or voting schemes, have historically shown to be a reliable approach to cope with failures for the majority of the sensors of the flight control system 3,4 . On the other side, physical redundancy has clear limitations for light and inexpensive aircraft such as small UAVs which are being increasingly used in various civilian, military, and research applications.…”
Section: Introductionmentioning
confidence: 99%
See 1 more Smart Citation
“…Extensive research programs led by NASA have focused on designing and validating specific approaches for the design of a number of fault tolerant flight control schemes 1,2 , primarily focused on malfunctions of the actuators of the control surfaces or failures of the propulsion system. However, issues related to sensor failures have been considered of lower priority, mainly due to the fact that triple or quadruple physical redundancy on the sensor suite, along with the implementation of Built-In Testing (BIT) and/or voting schemes, have historically shown to be a reliable approach to cope with failures for the majority of the sensors of the flight control system 3,4 . On the other side, physical redundancy has clear limitations for light and inexpensive aircraft such as small UAVs which are being increasingly used in various civilian, military, and research applications.…”
Section: Introductionmentioning
confidence: 99%
“…2), if the windowed estimation error exceeds a threshold 2 E (see Eq. 3), and if the distance from the input to the nearest center is larger than a threshold3 E (see Eq.…”
mentioning
confidence: 99%
“…To alleviate the effect of sensor failures, multiple sensors can be installed to produce a physically redundant measurement. Through the use of these redundant measurements and voting schemes, failures for most types of sensors in the flight control system can be accommodated [1,2]. These physical redundancy approaches, however, are vulnerable to failures on pitot tube sensors, since redundant sensors are all subject to the same environmental conditions in flight.…”
mentioning
confidence: 99%
“…These physical redundancy approaches, however, are vulnerable to failures on pitot tube sensors, since redundant sensors are all subject to the same environmental conditions in flight. Therefore, failure on any individual pitot tube is also likely to occur on the other pitot tubes under certain weather conditions, resulting in a "common mode" failure [1][2][3][4]. Since flight control gains are typically scheduled as a function of the airspeed, incorrect airspeed measurements from a failed set of pitot tubes can result in catastrophic conditions, such as the crash of Air France Flight 447 [3], the X-31 research aircraft [4], and the Aero Peru 757 [5].…”
mentioning
confidence: 99%