Multicontrol Surface Optimization for Blended Wing–Body Under Handling Quality Constraints

Denieul, Yann; Bordeneuve-Guibé, Joël; Alazard, Daniel; Toussaint, Clément; Taquin, Gilles

doi:10.2514/1.c034268

Cited by 21 publications

(15 citation statements)

References 38 publications

(49 reference statements)

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“…It has been applied to a variety of domains such as chemistry [9], robotics [10] and powertrains [11] [12]. In aerospace, the method has mainly been used in preliminary design for different purposes such as mass reduction of large flexible structures [13], reduction of avionics requirements for satellite attitude control [14], optimization of an airborne-wind-energy system [15] and aircraft control surfaces sizing under handling qualities constraints [16] [17].…”

Section: B Plant-controller Optimizationmentioning

confidence: 99%

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Concurrent Airframe-Controller Optimization of a Guided Projectile Fitted with Lifting Surfaces

Riss

Roussel

Laroche

2022

AIAA SCITECH 2022 Forum

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Innovative long-range guided projectiles concepts require precise flight path tracking in order to achieve maximum range and terminal accuracy. For such airframes featuring large lifting surfaces, vertical maneuvering performance relies on pitch attitude control.Thus, a challenging problem arises from the conflict between performance requirements and actuator limitations. The projectile static stability should be tailored to limit controls deflections and actuator bandwidth. This work proposes a plant-controller optimization (PCO) procedure to tune the projectile static stability and the controller gains in a single step. This methodology is applied to actuator usage minimization under control performance constraint. The optimal airframe-controller design shows superior actuator roll-off characteristics compared to the outcome of the traditional "design then control" methodology. The codesign also proves to be much less computationally intensive, which confirms the relevance of the approach.

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Section: B Plant-controller Optimizationmentioning

confidence: 99%

“…Alazard et al [14] introduced simultaneous optimization of both plant and controller parameters in a single, fixed-structure H ∞ synthesis problem. Denieul et al [17] applied this methodology to elevons sizing and control allocation for a blended-wing-body aircraft concept.…”

Section: B Plant-controller Optimizationmentioning

confidence: 99%

Concurrent Airframe-Controller Optimization of a Guided Projectile Fitted with Lifting Surfaces

Riss

Roussel

Laroche

2022

AIAA SCITECH 2022 Forum

View full text Add to dashboard Cite

show abstract

“…Such approach, where the aerodynamics, Fig. 1 T-Flex demonstrator aircraft structural dynamics and the control design are optimized in a common step is called co-design [4][5][6][7]. The control design is model based, therefore, a suitable control oriented aeroservoelastic (ASE) model for flexible aircraft is crucial.…”

Section: Introductionmentioning

confidence: 99%

Model Based Automatic Control Design for the T-FLEX Demonstrator Using RCE Environment

Takarics¹,

Patartics²,

Luspay³

et al. 2023

AIAA SCITECH 2023 Forum

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The main goal of the paper is to develop automatic control design methods for flexible aircraft. The motivation for the research is that such automatic control generation enables the inclusion of the control design algorithms into the multidisciplinary design optimization (MDO) of aircraft design. In such an extended MDO framework, called co-design, the sizing, structural dynamics, aerodynamics and the controllers of the aircraft are optimized in one single step. This way control technologies can be included early-on in the preliminary design stage of aircraft design. Since the control design is model based, first a control oriented aeroservoelastic model needs to be developed. The modeling is done via the bottom-up modelling approach. The model generation also needs to be automatic due to parameter changes resulting from the MDO process. The research focuses on flexible aircraft, therefore, the control algorithms include baseline, manoeuvre load alleviation, gust load alleviation and flutter suppression controllers. All of these algorithms needs to be developed in such way that they can automatically executed in the MDO process. The overall MDO framework is based on the Remote Component Environment (RCE) environment and the aircraft investigated is the T-Flex demonstrator of the FLIPASED project. The paper presents the main concepts of the modeling and control synthesis, analysis for the above mentioned four controllers and the most important aspects of integrating such automatic control design methods into the RCE environment.

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“…When an analytical model of the structure is available, the integration of the design variables as uncertain parameters opens the possibility of achieving control/structure co-design in a unique iteration, using the non-smooth techniques available in the robust structured 𝐻 ∞ control framework [35], as shown in several aerospace applications [23,36,37]. A drawback of such a direct co-design is that it could provide a non-global optimal design, by risking to fall within one of the many local minima.…”

Section: Introductionmentioning

confidence: 99%

Parametric sub-structuring models of large space truss structures for structure/control co-design

Finozzi¹,

Sanfedino²,

Alazard³

2022

Mechanical Systems and Signal Processing

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Multicontrol Surface Optimization for Blended Wing–Body Under Handling Quality Constraints

Cited by 21 publications

References 38 publications

Concurrent Airframe-Controller Optimization of a Guided Projectile Fitted with Lifting Surfaces

Concurrent Airframe-Controller Optimization of a Guided Projectile Fitted with Lifting Surfaces

Model Based Automatic Control Design for the T-FLEX Demonstrator Using RCE Environment

Parametric sub-structuring models of large space truss structures for structure/control co-design

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