Structural weight estimation for multidisciplinary optimization of a high-speed civil transport

Huang, Xudong; Dudley, Jonathan G.; Haftka, Raphael T.; Grossman, Bernard; Mason, William H.

doi:10.2514/3.46989

Cited by 11 publications

(5 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Notice that Eqs. (27) and (28) are directly proportional to the bending moments found by Prandtl in Eq. 7.…”

Section: B Hunsaker's Formulationmentioning

confidence: 85%

“…In place of FEA structural models, beam models [19][20][21][22] and weight equations derived statistically, 24 using response-surface methodology, 25 or other methods 21 have been used. Multi-fidelity aerostructural optimization routines have been successfully used for a wide variety of aircraft configurations, including subsonic configurations, [15][16][17][18] supersonic transports, [26][27][28] and rotorcraft. 29,30 Low-fidelity optimization routines are generally used for conceptual-level design.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Numerical Algorithm for Wing-Structure Design

Taylor

Hunsaker

Joo

2018

2018 AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

“…Notice that Eqs. (27) and (28) are directly proportional to the bending moments found by Prandtl in Eq. 7.…”

Section: B Hunsaker's Formulationmentioning

confidence: 85%

Section: Introductionmentioning

confidence: 99%

Numerical Algorithm for Wing-Structure Design

Taylor

Hunsaker

Joo

2018

2018 AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

“…The structure was assumed to be rigid for the determination of aerodynamic forces. Previous studies indicated that structural flexibility did not have a large effect on the structural wing weight (objective function of the structural optimization) for this particular configuration [12,13]. A surface spline interpolation method was used to translate forces between aerodynamic node and structural node locations.…”

Section: Structural Optimizationmentioning

confidence: 99%

Multifidelity response surface model for HSCT wing bending material weight

Balabanov¹,

Haftkat

Grossman

et al. 1998

7th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization

View full text Add to dashboard Cite

Response surface techniques allow us to combine results from a large number of inexpensive low fidelity analyses with a small number of expensive high fidelity analyses for constructing inexpensive and accurate approximations. The paper demonstrates this approach by constructing approximations to wing bending material weight of a high speed civil transport (HSCT). The approximations employ a large number of structural optimizations of finite element models for a range of HSCT configurations. Thousands of structural optimizations of coarse finite element models are used to construct a quadratic response surface model. Then about a hundred structural optimizations of refined finite element models are used to construct linear correction response surface models. The usefulness of the approximations is demonstrated by performing aerodynamic optimizations of the HSCT while employing the response surface models to estimate wing bending material weight. The approximations for the final HSCT designs are compared to results of structural optimizations of the refined finite element model.

show abstract

“…A finite element model-based structural optimisation procedure with flexible loads was implemented to evaluate the wing-bending material weight of the high-speed civil transport (HSCT) (4) . The physics-based methods were used to estimate the structural weight of innovative conceptual aircraft (Blended Wing Body/BWB) by many researchers.…”

Section: Introductionmentioning

confidence: 99%

Static aeroelastic optimisation to wing structural weight estimation of an extremely manoeuvrable UAV

Yi¹,

Jun²,

Kong³

2015

Aeronaut. j.

View full text Add to dashboard Cite

Estimating the wing structural weight of an extremely manoeuvrable Unmanned Aerial Vehicle (UAV) during conceptual design has proven to be a significant challenge due to its high load factor (the ratio of an aircraft lift to its weight). The traditional empirical method relies on existing statistical data of previously built aircraft, then is inadequate for the innovative UAV structure design which can endure extremely manoeuvrable load (load factor is greater than 9g). In this paper, the finite element model for wing structure of an extremely manoeuvrable UAV with foreplane was built, and the structural weight was estimated by static aeroelastic optimisation considering structural strength and buckling constraints. The methodology developed here is only consisted of three components, which is much less than that for existing method, thus the procedure developed here sacrificed some accuracy, but it's faster and more suitable for aircraft conceptual design. It was validated by the overlap between the weights given by the methodology, and the results from empirical equations when the load factors are less than 9g. Through the analysis procedure developed, the wing structural weights of the extremely manoeuvrable UAV were given under different load cases (load factor changes from 5g to 12g).

show abstract

Structural weight estimation for multidisciplinary optimization of a high-speed civil transport

Cited by 11 publications

References 5 publications

Numerical Algorithm for Wing-Structure Design

Numerical Algorithm for Wing-Structure Design

Multifidelity response surface model for HSCT wing bending material weight

Static aeroelastic optimisation to wing structural weight estimation of an extremely manoeuvrable UAV

Contact Info

Product

Resources

About