The use of structural optimality criteria for aircraft conceptual design

Danilin, A. I.; Weisshaar, Terrence A.

doi:10.2514/6.2000-1328

Cited by 3 publications

(3 citation statements)

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“…More recently, Qin et al [17,18] have researched the aeroelastic instability of composite, thin-walled beams to investigate the effect of aeroelastic tailoring. Several papers on the use of aeroelastic tailoring in general and its potential benefits have been written by Weisshaar [19], Danlin and Weisshaar [20], Livne and Weisshaar [21], and Weisshaar and Duke [22]. More specific research on the use of aeroelastic tailoring has been performed to minimize structural weight [23][24][25][26][27][28], to maximize flutter speed [25,26,[29][30][31][32], to optimize the gust response characteristics of wings [33,34], and on the effect of tow-steered composites on wing aeroelastic characteristics [3,5].…”

Section: Subscriptsmentioning

confidence: 99%

Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Sodja

Werter

Breuker

2021

Journal of Aircraft

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Section: Subscriptsmentioning

confidence: 99%

Aeroelastic Demonstrator Wing Design for Maneuver Load Alleviation Under Cruise Shape Constraint

Sodja

Werter

Breuker

2021

Journal of Aircraft

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“…Furthermore, several papers on the use of aeroelastic tailoring in general and the potential benefits it has, have been written recently by Weisshaar. [4][5][6][7] More specific research on the use of aeroelastic tailoring has been done to minimize structural weight, [8][9][10][11][12] maximize flutter speed 10,11,[13][14][15][16] optimise the gust response characteristics of wings, 17,18 and the effect of tow-steered composites on wing aeroelastic characteristics. 19 An example of the use of aeroelastic tailoring in non-aerospace applications is the research by Thuwis et al 20 on the use of aeroelastic tailoring on the rear wing of a F1 car.…”

Section: Introductionmentioning

confidence: 99%

Design of a flying demonstrator wing for manoeuvre load alleviation with cruise shape constraint

Sodja

Werter

Breuker

2018

2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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to a design of the tailored composite wing for a flying demonstrator is presented in this paper. In the design process the structural mass of the wing is minimised including a cruise shape constraint. Introduction of the cruise shape constraint is explained as well as a number of other important design requirements which were imposed in order to obtain a feasible and flight worthy design. The effect of the cruise shape constraint is investigated by performing a comparison study. For this purpose two wing types were defined: the reference wing and the tailored wing. The difference between the two wings is in the laminate definition comprising each wing. The reference wing was designed with symmetric-balanced laminates, while symmetric-only laminates were used for the tailored wing. The comparison was performed in terms of laminate stiffness and thickness distribution along the span, jig twist, and the aeroelastic response. Elastic deformations, aerodynamic load distribution and wing root loads are compared within the scope of aeroelastic response.

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“…Furthermore, several papers on the use of aeroelastic tailoring in general and its potential benefits, have been written recently by Weisshaar. [4][5][6][7] More specifically, research has been done on the use of aeroelastic tailoring in order to minimize structural weight, [8][9][10][11] maximize flutter speed, 10,[12][13][14][15] optimize the gust response characteristics of the wings, 16 or the effect of tow-steered composites on wing aeroelastic characteristics. 17,18 Several researchers [19][20][21] have used a gradient-based optimiser with adjoint sensitivities to achieve aeroelastic tailoring by optimising a combination of laminate thickness and the fraction of 0 deg, 45 deg, −45 deg, and 90 deg plies in the stacking…”

Section: Introductionmentioning

confidence: 99%