Automatic Optimization of Wing–Body–Under-the-Wing-Mounted-Nacelle Configurations

Epstein, Boris; Peigin, S. V.

doi:10.2514/1.c033641

Cited by 6 publications

(3 citation statements)

References 17 publications

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“…Conversely, there has been research into nacelle design that considers the integration eects with the airframe during the design process [17,18,19]. Nevertheless, these studies simplify the powerplant and only throughow nacelle congurations are employed.…”

Section: Propulsion System Integration Challengementioning

confidence: 99%

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Effects of Aircraft Integration on Compact Nacelle Aerodynamics

Tejero

Goulos

MacManus

et al. 2020

AIAA Scitech 2020 Forum

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To reduce specic fuel consumption, it is expected that the next generation of aero-engines will operate with higher bypass-ratios, and therefore fan diameters, than current in-service architectures. These new propulsion systems will increase the nacelle size and incur in an additional overall weight and drag contribution to the aircraft. In addition, they will be installed more closely-coupled with the airframe, which may lead to an increase in adverse installation eects. As such, it is required to develop compact nacelles which will not counteract the benets obtained from the new engine cycles. A comprehensive investigation of the eects of nacelle design on the overall aircraft aerodynamic performance is required for a better understanding on the eects of aero-engine integration. This paper presents a method for the multi-objective optimisation of drooped and scarfed non-axisymmetric nacelle aero-engines. It uses intuitive Class Shape Tranformations (iCSTs) for the aero-engine geometry denition, multi-point aerodynamic simulation, a near-eld nacelle drag extraction method and the NSGA-II genetic algorithm. The process has been employed for the aerodynamic optimisation of a compact nacelle aero-engine as well as a conventional nacelle conguration. Subsequently, the designed architectures were installed on a conventional commercial transport aircraft and evaluated at dierent installation positions. A novel thrust-drag bookkeeping method has been used to 1

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Section: Propulsion System Integration Challengementioning

confidence: 99%

“…A new throughow nacelle design with a reduction of 16dc at cruise conditions was achieved relative to the baseline conguration. Epstein et al [19] proposed a design method of aircraft congurations with under-the-wing-mounted nacelles.…”

Section: Propulsion System Integration Challengementioning

confidence: 99%

Effects of Aircraft Integration on Compact Nacelle Aerodynamics

Tejero

Goulos

MacManus

et al. 2020

AIAA Scitech 2020 Forum

View full text Add to dashboard Cite

show abstract

“…In addition to the above research on the dynamic characteristics of the multi-support structure system of the power plant for automobiles, locomotives, ships, and in the aviation field, researchers have also studied the dynamic characteristics of the multi-support engine nacelle mounting system, mainly regarding the dynamic coupling characteristics of the engine and the suspension inside the nacelle [22,23].…”

Section: Introductionmentioning

confidence: 99%

Dynamic Characteristics Analysis of a Rigid Body System with Spatial Multi-Point Supports

et al. 2022

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This paper presents the dynamic characteristics analysis of a rigid body system with spatial multi-point elastic supports, as well as the sensitivity analysis of support parameters. A rigid object is characterized by six degrees-of-freedom (DOFs) motions and considering the spatial location vector decomposition of elastic supports, a rigid body system dynamic model with spatial multi-point elastic supports is derived via the Lagrangian energy method. The system modal frequencies are calculated, and to be verified by finite element modal analysis results. Next, based on the above-mentioned model, system modal frequencies are obtained under different support locations, where the support stiffness components are different. Interpolate the stiffness components corresponding to each support location, calculate system modal frequencies, and the response surface model (RSM) for system modal frequencies is established. Further, based on the RSM modal analysis results, the allowable support location for the system modal insensitive area can be obtained. At last, a lubricating oil-tank system with four supports is taken as an example, and the effects of support spatial locations and stiffness components on the system inherent characteristics are discussed. This present work can provide a basis for the dynamic design of the spatial location and stiffness for this type of installation structures.

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Aerodynamic optimization of civil aircraft with wing-mounted engine jet based on adjoint method

Lei

Bai

2019

Aerospace Science and Technology

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Automatic Optimization of Wing–Body–Under-the-Wing-Mounted-Nacelle Configurations

Cited by 6 publications

References 17 publications

Effects of Aircraft Integration on Compact Nacelle Aerodynamics

Effects of Aircraft Integration on Compact Nacelle Aerodynamics

Dynamic Characteristics Analysis of a Rigid Body System with Spatial Multi-Point Supports

Aerodynamic optimization of civil aircraft with wing-mounted engine jet based on adjoint method

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