Flight Test Protocol Optimization Using Genetic Algorithms

Seren, Cédric; Bommier, François; Bucharles, A.; Verdier, L.; Alazard, Daniel

doi:10.3182/20060329-3-au-2901.00099

Cited by 3 publications

(2 citation statements)

References 2 publications

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“…However, structural deformations produce a significant contribution for highaspect-ratio airplanes (mainly gliders). Therefore, for flight dynamics purposes, a six degree-of-freedom (DOF) rigid-body model is usually used [15][16][17]. This was also done in this study, as Airbus A320 (which was the aircraft under test) aspect ratio is 10.47 [18].…”

Section: Aircraft Point-mass Modelmentioning

confidence: 99%

Fuel-Efficient Trajectories Traffic Synchronization

Pawełek¹,

Lichota²,

Dalmau³

et al. 2019

Journal of Aircraft

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Section: Aircraft Point-mass Modelmentioning

confidence: 99%

Fuel-Efficient Trajectories Traffic Synchronization

Pawełek¹,

Lichota²,

Dalmau³

et al. 2019

Journal of Aircraft

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“…The software system identification and trajectory optimization program (STOP) was developed at the Dipartimento di Scienze e Tecnologie Aerospaziali of the Politecnico di Milano and conceived as a tool to be used in support of certification and 1 Published works that have investigated the use of EAs for the solution of optimal control problems rely on the use of either penalty functions (Wang and Chiou 1997) or specialized genetic operators (Seren et al 2006;Onnen et al 1997). In the former case, one transforms a constrained problem into an unconstrained one by penalizing constraint violations in the objective function with suitably high weights.…”

Section: Introductionmentioning

confidence: 99%

Global Solution of Optimization Problems in Rotorcraft Flight Mechanics

Bottasso

Luraghi

Maisano³

et al. 2015

J. Aerosp. Eng.

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In this paper, the authors present a procedure for the global solution by the use of evolutionary algorithms of trajectory optimization and parameter estimation problems for rotorcraft vehicles. The proposed approach makes use of a novel repair heuristic based on a sequential quadratic programming method to handle problem constraints. The resulting formulation effectively deals with the complex, highly constrained, optimization and optimal control problems plagued by multiple local minima or maxima that are often encountered in practical rotorcraft flight mechanics applications. The performance of the proposed procedures is assessed with applications dealing with the design of optimal inputs for the estimation of model parameters, with the determination of the optimal way of flying continued take-offs under category A requirements, and with the determination of the most dangerous areas of the height-velocity (H-V) plane in terms of impact velocity with the ground

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