Method for Evaluating Electrically Actuated Hybrid Wing–Body Control Surface Layouts

Garmendia, Daniel C.; Chakraborty, Imon; Mavris, Dimitri N.

doi:10.2514/1.c033061

Cited by 15 publications

(8 citation statements)

References 20 publications

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“…With the traditional approach to life cycle management, the system useful life is computed a priori in the design phase, solely from the probabilistic combination of components failure rate. This strategy does not account for the real evolution of the components health status, and then produces estimates affected by a very large uncertainty interval [1,2,3,4]. Popular approaches to RUL estimations aim at obtaining a more precise estimate of the system life either by extrapolating the current fault propagation rate [42], or by employing a model of damage growth until the damage condition reaches a threshold.…”

Section: Prognostics and Health Management (Phm): Problem Formulationmentioning

confidence: 99%

“…The traditional approach to system life-cycle management is based on scheduling maintenance interventions a priori : components are replaced at the end of their design life, regardless their actual health status [1,2,3]. This strategy leads to high maintenance costs and cannot guarantee that no failure will occur before the predicted end of life, for example as the result of an undetected manufacturing defect; to reduce risk on safety-related equipment, critical components are redounded [4,5], increasing weight and further reducing basic reliability. Conversely, latest approaches like Condition Based Maintenance (CBM) [6,7,8] and Integrated Vehicle Health Management (IVHM) [9,10,11] aim to account for advances in Prognostics and Health Management (PHM) disciplines, in order to better manage the maintenance schedule, reducing costs and increasing mission reliability [12,13,14,15,16].…”

Section: Introductionmentioning

confidence: 99%

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Computational framework for real-time diagnostics and prognostics of aircraft actuation systems

Berri,

Vedova,

Mainini

2020

Preprint

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Prognostics and Health Management (PHM) are emerging approaches to product life cycle that will maintain system safety and improve reliability, while reducing operating and maintenance costs. This is particularly relevant for aerospace systems, where high levels of integrity and high performances are required at the same time. We propose a novel strategy for the nearly real-time Fault Detection and Identification (FDI) of a dynamical assembly, and for the estimation of Remaining Useful Life (RUL) of the system. The availability of a timely estimate of the health status of the system will allow for an informed adaptive planning of maintenance and a dynamical reconfiguration of the mission profile, reducing operating costs and improving reliability. This work addresses the three phases of the prognostic flow -namely (1) signal acquisition,(2) Fault Detection and Identification, and (3) Remaining Useful Life estimation -and introduces a computationally efficient procedure suitable for real-time, on-board execution. To achieve this goal, we propose to combine information from physical models of different fidelity with machine learning techniques to obtain efficient representations (surrogate models) suitable for nearly real-time

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Section: Prognostics and Health Management (Phm): Problem Formulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Computational framework for real-time diagnostics and prognostics of aircraft actuation systems

Berri,

Vedova,

Mainini

2020

Preprint

View full text Add to dashboard Cite

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“…The problem of number and spacing of trailing edge control surfaces for BWB was already pointed out by Garmendia et al 16 . 18 They provided an extensive view on all currently studied BWB configurations and controls layouts. Another study of interest was performed by Belschner: 19 an optimisation was run on failure cases considering electro-mechanical actuators (EMA) driving independant control surfaces.…”

Section: Iib2 Control Surfaces Layoutmentioning

confidence: 99%

Interactions of Aircraft Design and Control: Actuators Sizing and Optimization for an Unstable Blended Wing-Body

Denieul

Alazard

Bordeneuve-Guibé

et al. 2015

AIAA Atmospheric Flight Mechanics Conference

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“…3 Cook and de Castro 4 studied both static and dynamic stability and control of a large HWB, and demonstrated the limited static margin range in which longitudinal trim can be attained at low speed. Garmendia et al 5 compared a number of trailing-edge control surface layouts, using between 7 and 11 control surfaces in di↵erent configurations, with the aim of minimizing weight, power, and fuel burn. The same authors also studied the control power implications of various control configurations, stability requirements, and turbulence levels.…”

Section: Introductionmentioning

confidence: 99%

Multifidelity Optimization of Hybrid Wing–Body Aircraft with Stability and Control Requirements

Reist¹,

Zingg²,

Rakowitz³

et al. 2019

Journal of Aircraft

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Methods of satisfying stability and control (S&C) requirements for hybrid wing-body (HWB) aircraft are investigated using a multi-fidelity multidisciplinary optimization framework. A Reynolds-averaged Navier-Stokes solver is used for aerodynamic prediction, together with conceptual-level weight and balance models. These are coupled with a gradientbased optimizer to form a multidisciplinary optimization tool. Two HWB configurations are investigated. The first uses winglets with winglet-mounted rudders for lateral control, while the second uses centerbody-mounted fins with rudders. Longitudinal control is achieved with one centerbody elevator and six wing-mounted elevons. The designs are optimized for a combination of minimum maximum take-o↵ weight and cruise drag. The ability of the designs to maintain lateral trim with one engine inoperative at a specified minimum control speed and to achieve a given rotational acceleration at a specified rotation speed form the o↵-design S&C constraints. Additional constraints at cruise ensure trim and a required static margin. In addition to a classical HWB shape, a narrower cabin layout is also considered which provides improved performance. The required S&C requirements are found to be attainable using both configurations, with the fin-based control having a small performance advantage. The narrow centerbody configuration is found to provide superior performance over the classical configuration.

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Method for Evaluating Electrically Actuated Hybrid Wing–Body Control Surface Layouts

Cited by 15 publications

References 20 publications

Computational framework for real-time diagnostics and prognostics of aircraft actuation systems

Computational framework for real-time diagnostics and prognostics of aircraft actuation systems

Interactions of Aircraft Design and Control: Actuators Sizing and Optimization for an Unstable Blended Wing-Body

Multifidelity Optimization of Hybrid Wing–Body Aircraft with Stability and Control Requirements

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