Effects of Structural Failure on the Safe Flight Envelope of Aircraft

Nabi, Hafiz Noor; Lombaerts, Thomas; Zhang, Y.; Kampen, E. van; Chu, Q.P.; Visser, Coen C. de

doi:10.2514/1.g003184

Cited by 47 publications

(31 citation statements)

References 32 publications

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“…First and foremost, the desired region of the state-space can be defined by limits on the aircraft states. Within such a strict envelope, one would have the largest control-invariant set (or safe set) [27,28], i.e., the largest set of initial conditions such that, given suitable control input, the aircraft is kept within the flight envelope.…”

Section: B Stable Set Analysismentioning

confidence: 99%

Piecewise Polynomial Modeling for Control and Analysis of Aircraft Dynamics Beyond Stall

Cunis

Burlion

Condomines

2019

Journal of Guidance, Control, and Dynamics

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Section: B Stable Set Analysismentioning

confidence: 99%

Piecewise Polynomial Modeling for Control and Analysis of Aircraft Dynamics Beyond Stall

Cunis

Burlion

Condomines

2019

Journal of Guidance, Control, and Dynamics

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“…where l(x) : R n → R represents a continuous cost function which is problem specific, see Ref. [7,11] for possible implementations. In Ref.…”

Section: B Reachability Analysis As An Optimal Control Problemmentioning

confidence: 99%

Probabilistic Flight Envelope Estimation with Application to Unstable Over-Actuated Aircraft

Yin

Chu

Zhang

et al. 2019

AIAA Scitech 2019 Forum

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This paper proposes a novel and practical framework for safe flight envelope estimation and protection, in order to prevent loss-of-control-related accidents. Conventional analytical envelope estimation methods fail to function efficiently for systems with high dimensionality and complex dynamics, which is often the case for high-fidelity aircraft models. In this way, this paper develops a probabilistic envelope estimation method based on Monte Carlo simulation. This method generates a probabilistic estimation of the flight envelope by simulating flight trajectories with extreme control effectiveness. It is shown that this method can significantly reduce the computational load compared with previous optimization-based methods and guarantee feasible and conservative envelope estimation of no less than seven dimensions. This method was applied to the Innovative Control Effectors aircraft, an over-actuated tailless fighter aircraft with complex aerodynamic coupling between control effectors. The estimated probabilistic flight envelope is used for online envelope protection by a database approach. Both conventional state-constraint-based and novel predictive probabilistic flight envelope protection systems were implemented on a multi-loop nonlinear dynamic inversion controller. Real-time simulation results demonstrate that the proposed framework can protect the aircraft within the estimated envelope and save the aircraft from maneuvers that otherwise would result in loss of control. I, R = invariant and reachable sets J = inertia matrix, slug·ft 2 J = augmented inertia matrix

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“…For instance, in Refs. (27)(28)(29)(30), the intended flight envelope is estimated by interpolating closely related envelopes retrieved from an offline generated database being carried onboard. Also, a neural network-based method has been proposed in Ref.…”

Section: Introductionmentioning

confidence: 99%

Evaluating the effects of lateral control surfaces failure on the generic transport model: a case study

2020

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Extensive research in recent years has focused on improving the current loss-of-control prevention systems and developing new strategies for safe path planning of the impaired aircraft. Success in developing such systems requires a comprehensive perception of the influence of damage on the aircraft’s dynamic behaviour and performance, and the effect of various failure degrees on the flight envelope confinement and the remaining safe maneuvers. This paper comprehensively describes the effects of lateral control surface failure on the NASA Generic Transport Model (GTM) flight envelope, defined by a set of attainable steady-state maneuvers herein referred to as trim points. The study utilises a large database of high-fidelity maneuvering flight envelopes computed for the unimpaired case and wide ranges of the aileron and rudder failure cases at different flight conditions. Flight envelope boundary is rigorously investigated, and the key parameters confining the trim points at different boundary sections are identified. Trend analyses of the impaired flight envelopes and the corresponding limiting factors demonstrate the effect of various failure degrees on the remaining feasible trim points. Results can be employed in emergency path planning with potential uses in the development of aircraft resilient control and upset recovery systems.

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Effects of Structural Failure on the Safe Flight Envelope of Aircraft

Cited by 47 publications

References 32 publications

Piecewise Polynomial Modeling for Control and Analysis of Aircraft Dynamics Beyond Stall

Piecewise Polynomial Modeling for Control and Analysis of Aircraft Dynamics Beyond Stall

Probabilistic Flight Envelope Estimation with Application to Unstable Over-Actuated Aircraft

Evaluating the effects of lateral control surfaces failure on the generic transport model: a case study

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