TY - JOUR
T1 - Simplified Estimation Algorithms for Aircraft Structural Damage Effects Using an Artificial Immune System
AU - Perhinschi, Mario George
AU - Azzawi, Dia Al
AU - Moncayo, Hever
N1 - D. Dasgupta, (editor), Artificial Immune Systems and Their Applications," (Springer Verlag, 1999). http://dx.doi.org/10.1007/978-3-642-59901-9 D. Dasgupta, L. F. Nino, Immunological Computation - Theory and Applications, (CRC Press, Auerbach Publications, Taylor & Francis Group, 2009). M. G. Perhinschi, H. Moncayo, J. Davis, Integrated Framework for Aircraft Sub-System Failure Detection, Identification, and Evaluation Based on the Artificial Immune System Paradigm, Proc.
PY - 2015/8/31
Y1 - 2015/8/31
N2 - The development of simplified models for the estimation of flight envelope reduction under damages to aircraft structural components, within the artificial immune system paradigm, is presented in this paper. The proposed methodology is part of a comprehensive and integrated framework for aircraft abnormal condition detection, identification, evaluation, and accommodation aimed at ensuring aircraft high survivability rates and operation safety. An artificial immune system built through simulation for a fighter aircraft is used in conjunction with a hierarchical multi-self strategy for estimating ranges of flight envelope relevant variables under structural damages affecting the wing, the horizontal tail, and the vertical tail. Flight envelope ranges are predicted when the lift-generating capabilities of the main aerodynamic surfaces are reduced, based on algorithms that are tailored to the nature and characteristics of the failure and 2-dimensional self projections. The performance of the proposed approach is evaluated using ad-hoc metrics and demonstrated successfully through simulation tests in a motion-based flight simulator.
AB - The development of simplified models for the estimation of flight envelope reduction under damages to aircraft structural components, within the artificial immune system paradigm, is presented in this paper. The proposed methodology is part of a comprehensive and integrated framework for aircraft abnormal condition detection, identification, evaluation, and accommodation aimed at ensuring aircraft high survivability rates and operation safety. An artificial immune system built through simulation for a fighter aircraft is used in conjunction with a hierarchical multi-self strategy for estimating ranges of flight envelope relevant variables under structural damages affecting the wing, the horizontal tail, and the vertical tail. Flight envelope ranges are predicted when the lift-generating capabilities of the main aerodynamic surfaces are reduced, based on algorithms that are tailored to the nature and characteristics of the failure and 2-dimensional self projections. The performance of the proposed approach is evaluated using ad-hoc metrics and demonstrated successfully through simulation tests in a motion-based flight simulator.
KW - Artificial Immune System
KW - Fault Tolerant Control
KW - Structural Damage Evaluation
UR - https://doi.org/10.15866/irease.v8i4.7461
U2 - 10.15866/irease.v8i4.7461
DO - 10.15866/irease.v8i4.7461
M3 - Article
SN - 2533-2279
VL - 8
JO - International Review of Aerospace Engineering
JF - International Review of Aerospace Engineering
ER -