The Application of Multi-Disciplinary Optimization Technologies to the Design of a Business Jet

Piperni, Pat; Abdo, Mohammed S.; Kafyeke, F.

doi:10.2514/6.2004-4370

Cited by 13 publications

(11 citation statements)

References 25 publications

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“…Advanced software tools and welldeveloped subsystem design experiences permit greater design integration and optimization [1][2][3][4]. This paper tries to exemplify the hypersonic vehicle collaborative design procedures.…”

Section: Introductionmentioning

confidence: 99%

An aircraft-propulsion geometry/performance collaborative design method

Tian

Gong

2012

IEEE 10th International Conference on Industrial Informatics

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High performance and economic gains are treated as the main target for future aerospace product design. An inward turning inlet equipped hypersonic vehicle parameterization procedure was devised for collaboration of wingbody and scramjet propulsion system modeling. Top design parameters (free-stream Mach number, flight altitude, mission requests, etc.) drive the overall collaborative system construction and both the scramjet engine geometry and wingbody profiles are conveniently generated using the NURBS toolbox and streamline tracing method within the programs developed in this paper. An accelerated digital real time hypersonic vehicle-propulsion integrated controlled plant was prepared for advanced controlling algorithm tests and further researches.

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Section: Introductionmentioning

confidence: 99%

An aircraft-propulsion geometry/performance collaborative design method

Tian

Gong

2012

IEEE 10th International Conference on Industrial Informatics

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“…Their paper described that optimization process not only considers the main objective as reducing the weight and the wing strength, but also simultaneously takes the buckling, fatigue, flutter, and other design criteria of the structure into considerations. Bombardier also made use of MDO to combine the own-developed finite element codes, such as the wing structure and weight analysis codes and the computational fluid dynamics code, to design the wing to solve the problem of static aeroelastic deformation under load [11].…”

Section: Related Studiesmentioning

confidence: 99%

Optimization Simulation of the Light Aircraft’s Cockpit Made of Carbon Fiber Reinforced Composites

Chen¹,

Liu²

2017

Preprint

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Due to the demands of personal travels and entertainments, light airplanes and small business aircrafts are developing rapidly. Light airplane structure is simple; however, it lacks crashworthiness design, especially the considerations on the impact of energy absorption. Therefore, in an event of accident, significant damage to passengers will be usually incurred. Airplanes made of composite materials structurally have high specific strength and good aerodynamic configuration. These materials have become the primary choice for new airplane development. This study mainly explores the topology optimization analysis of the light aircraft's cockpit made of carbon fiber reinforced composites. This paper compares the compression amounts in the original models of composite material and aluminum alloy fuselages with the models after optimization during the crash-landing, in order to investigate the safety of fuselages made of different materials after structural optimization under the dynamic crashing. This study found that the energy absorbed by the aluminum alloy fuselage during crash-landing is still higher than that by the carbon fiber reinforced composites fuselage. On the other hand, the aluminum alloy fuselage after topology optimization could have an energy absorption capability enhanced by 40%, as compared to the that of the original model of aluminum alloy fuselage.

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“…Moreover, at ONERA, 7 MDO was applied on the XRF-1 configuration using a bi-level optimization technique. Piperni et al, 8 on the other hand, showed a first complex application on aero-structural optimization by industry where it was applied on regional and business jets. The levels of fidelity here were compromised in some aspects though.…”

mentioning

confidence: 99%

Aero-Structural Optimization of the NASA Common Research Model

Keye

Klimmek

Abu-Zurayk

et al. 2017

18th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference

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A combined aerodynamic and structural, gradient-based optimization has been performed on the NASA/Boeing Common Research Model civil transport aircraft configuration. The computation of aerodynamic performance parameters includes a Reynoldsaveraged Navier-Stokes CFD solver, coupling to a linear static structural analysis using the finite element method to take into account aero-elastic effects. Aerodynamic performance gradients are computed using the adjoint approach. Within each optimization iteration, the wing's structure is sized via a gradient-based algorithm and an updated structure model is forwarded for the performance analysis. In this pilot study wing profile shape is optimized in order to study engine installation effects. This setting was able to improve the aerodynamic performance by 4% I. IntroductionT he aircraft industry is continuously in the search for advanced designs that consume less fuel and produce less emissions. The Flightpath 2050 a provides a vision for Europe's aviation systems and industries by the year 2050. Concerning the environmental aspects, the vision expects a high reduction in CO 2 and NOx emission per passenger kilometer, in addition to a 65% reduction in noise emission of air vehicles -by 2050relative to those of the year 2000. On the other hand, the worldwide air traffic is predicted to grow by 4-5% per year, which makes the fulfillment of these expectations a highly challenging task.Aircraft optimization, which can be performed using numerical techniques, is an indispensable choice to face the Flightpath 2050 challenges and to increase the aircraft's efficiency. An optimization that incorporates more than one discipline is called a multidisciplinary design optimization (MDO). Employing MDO in aircraft design, yields realistic designs that fulfill the constraints of the engaged disciplines and reduces the development risks. Moreover, MDO reduces the design cycle of an aircraft. However, the complexity of the problem in MDO significantly increases when compared to single-disciplinary optimizations. Therefore, optimization algorithms that drive high-fidelity MDO need to be particularly efficient.There are mainly two types of optimization algorithms, depending on whether the gradients information is required throughout the optimization; gradient-free algorithms and gradient-based algorithms. In the former, only the objectives and constraints values are required by the end of a design (or optimization) iteration. In the latter, on the other hand, the values and the gradients of the objectives and the constraints are required throughout the search for the optimum. The extra expense of these algorithms pays off as efficiency; gradient-based algorithms can reach an optimum more efficiently than gradient-free algorithms, at least the nearest (potentially local) optimum.These characteristics of gradient-based algorithms make them good candidates for optimization problems that start from a good design and require some fine tuning. In this paper the wing of the Common Research

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The Application of Multi-Disciplinary Optimization Technologies to the Design of a Business Jet

Cited by 13 publications

References 25 publications

An aircraft-propulsion geometry/performance collaborative design method

An aircraft-propulsion geometry/performance collaborative design method

Optimization Simulation of the Light Aircraft’s Cockpit Made of Carbon Fiber Reinforced Composites

Aero-Structural Optimization of the NASA Common Research Model

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The Application of Multi-Disciplinary Optimization Technologies to the Design of a Business Jet

Cited by 13 publications

References 25 publications

An aircraft-propulsion geometry/performance collaborative design method

An aircraft-propulsion geometry/performance collaborative design method

Optimization Simulation of the Light Aircraft&rsquo;s Cockpit Made of Carbon Fiber Reinforced Composites

Aero-Structural Optimization of the NASA Common Research Model

Contact Info

Product

Resources

About

Optimization Simulation of the Light Aircraft’s Cockpit Made of Carbon Fiber Reinforced Composites