A320-Regelungssystem

Brockhaus, Rudolf; Alles, Wolfgang; Luckner, Robert

doi:10.1007/978-3-642-01443-7_20

Cited by 1 publication

(2 citation statements)

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“…As soon as the integrator saturates, the rate feedforward is switched off and the attitude control loop augments the saturated integrated output directly. A C * control law has been implemented for longitudinal control [10,11]. When the angle of attack α exceeds the protection threshold α prot a , the commanded angle of attack becomes proportional to the inceptor deflection α comm ∝ δ c up to the maximum value α max .…”

Section: B Linear Controllersmentioning

confidence: 99%

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Design and Piloted Simulator Evaluation of Adaptive Safe Flight Envelope Protection Algorithm

Lombaerts

Looye²,

Ellerbroek³

et al. 2017

Journal of Guidance, Control, and Dynamics

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This paper discusses the design and evaluation of an efficient safe flight envelope protection method, for keeping an augmented aircraft with manual flight control laws within the safe envelope bounds. This flight envelope is estimated adaptively, so that configuration changes and possible failures can be taken into account. The updated information of the safe envelope is used in the flight control laws to prevent loss of control in flight. It has been found that a control architecture involving separate pilot command filtering is particularly well suited to incorporate these adaptive protections. Moreover, haptic feedback to the pilot controls can be included as well, based on the same adaptive bounds. This has the potential to further increase the flight crew awareness about the risk of losing control in flight. These algorithms have been evaluated in the Simona Research Simulator at Delft University of Technology, to investigate the impact on the awareness of the crew. Commercial airline crews flew multiple challenging approach and landing scenarios in a relevant simulated environment. Results show that the algorithms support the flight crew significantly. They contribute to 'care-free' flying and to avoiding loss of control in flight.

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Section: B Linear Controllersmentioning

confidence: 99%

“…The C * (t) control signal is a weighted combination of load factor at the pilot station n z pilot and pitch rateθ [10,11]:…”

Section: B Linear Controllersmentioning

confidence: 99%