Flutter Analysing Over an Aircraft Wing During Cruise Speed
TL;DR: In this article, a subsonic passenger aircraft in its cruise speed was analyzed using optimization tools CFD and FEA tools, and the results were exposed computationally including both fluid and structural interaction problem, which can able to predict accurately the nature of an aircraft during its flutter.
About: This article is published in Procedia Engineering.The article was published on 2012-01-01 and is currently open access. It has received 10 citations till now. The article focuses on the topics: Flutter & Aeroelasticity.
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TL;DR: In this article, a battery thermal management system is used and they having various techniques to cool the battery and maintain the optimum temperature, including air cooling, liquid cooling, phase change materials, cold plates and heat pipes.
73 citations
TL;DR: In this paper, a technique based upon artificial neural network (ANN) for applying aerodynamic pressure loads on the UAV for the purpose of carrying out finite element (FE) analysis during its structural design process is presented.
24 citations
TL;DR: In this article , a Harris Hawks Optimizer (HHO) is employed to acquire the optimal global solution of initial state KF parameters for the W-H system identification problem.
Abstract: Block oriented models are recurrently employed to describe the dynamic characteristics of nonlinear systems. This paper adopts an efficacious block-oriented model called cascaded Wiener-Hammerstein (W-H) structure to model a nonlinear system. The parameters of the W-H model are identified using a nature-inspired evolution algorithm-supported Kalman filter (KF). In the proposed technique, the utility of the employed optimisation algorithm named Harris Hawks optimiser (HHO) is to acquire the optimal global solution of initial state KF parameters for the W-H system identification problem. Then, the conventional KF algorithm utilises these optimised KF parameters to beget the near-global estimated W-H system parameters. The effectiveness of the proposed HHO-based KF algorithm is verified through a comparison study with other variants of particle swarm optimisation (PSO) and harmony search (HS) algorithms-supported KF methods on two numerical W-H problems with different nonlinearity levels and two practical benchmark plants, namely, real electronic diode switching network and flutter clearance of F-18 systems research aircraft. The simulation results ensure that the proposed HHO-KF approach offers significantly improved results over other competing methods in terms of various well known standard metrics. The hypothesis test verifies the stability and consistency of the proposed identification method. Moreover, the proposed approach provides a faster convergence rate and the lowest estimation precision compared with other reported techniques.
9 citations
01 Jan 2006
TL;DR: A design methodology that integrates an aircraft performance model with a program valuation technique based on real options theory to address uncertain market demand and managerial flexibility and shows that a willingness to spend up-front money in the design process to ensure long-term profitability is a better strategy.
Abstract: Traditional commercial aircraft design attempts to improve performance and reduce operating costs by minimizing takeoff weight. A better design approach also takes into account factors such as aircraft demand, market uncertainty, and development and manufacturing costs. This paper presents a design methodology that integrates an aircraft performance model with a program valuation technique based on real options theory to address uncertain market demand and managerial flexibility. The coupled performance/financial framework enables an integrated approach to technical design and programmatic decisions. In addition, the methodology provides a framework for specification of design requirements and for quantification of the financial implications associated with technical and business uncertainty. The methodology is demonstrated for an aircraft design example of the blended-wing-body concept. Comparing performance-optimized and value-optimized designs, we show that use of value as a design metric leads to a trade-off between aerodynamic efficiency and reduced manufacturing costs. Key findings demonstrate that traditional financial metrics cause the decision maker to focus overly on reducing costs in the short term. The stochastic methodology shows that a willingness to spend up-front money in the design process to ensure long-term profitability is a better strategy.
7 citations
TL;DR: Analysis indicate that the proposed EFEM-based topology optimization can improve the dynamic performance of high-frequency vibrating structures by 20%–80% and be applied to classic stiffened plates.
Abstract: The energy finite element method (EFEM) provides researchers with an efficient tool to analyze high-frequency vibrating solid structures with less calculation and clear distribution of the energy density. However, the corresponding applications in structure optimization mainly focus on modifying the size and material properties, and it leaves a scientific gap that the topology flexibility is not addressed enough in the optimization. Therefore, this work aims at establishing an explicit level-set based topology optimization framework for the energy finite element method. A series of basic technical aspects, including the explicit level set description method, customized finite element mesh, mathematical model, and sensitivity analysis, are presented. With these basic studies, an original EFEM-based topology optimization framework for thin-walled structures is established for the first time. It is a basic work to conduct topology optimization in terms of energy. Additional applications in curved surfaces, spatial structures, and compound materials can also be developed only by modifying the description and EFEM module. Finally, the proposed optimization is applied to classic stiffened plates. Further analyses indicate that the proposed EFEM-based topology optimization can improve the dynamic performance of high-frequency vibrating structures by 20%–80%.
5 citations
References
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09 Jan 2006
TL;DR: A rapid geometry engine (RAGE) has been developed to allow for preliminary design analysis without labor-intensive CAD support and examples of many widely varying geometry models are shown to demonstrate the versatility of the geometry tool.
Abstract: A rapid geometry engine (RAGE) has been developed to allow for preliminary design analysis without labor-intensive CAD support. The geometry tool builds complex aircraft configurations using a component-based approach. Basic algorithms for creating the primary components are presented and discussed. Examples of many widely varying geometry models are shown. A select geometry model is analyzed with several aerodynamic analysis methods ranging in fidelity to further demonstrate the versatility of the geometry tool. Example uses of the tool in optimization problems are also presented. Future plans for the geometry engine are also discussed. I. Background Preliminary aircraft design methods have advanced tremendously in the past few decades due to rapidly developing computer technology and overall algorithmic improvements. Analysis methods that were once considered only feasible for advanced and detailed design are now available and even practical at the preliminary design stage. Rapid analysis methods also allow for simple and even multidisciplinary optimization methods to be utilized in preliminary design. To fully exploit these advanced analysis and optimization methods, the geometric model of the aircraft must be easily and rapidly generated so as not to inhibit the preliminary design process.
66 citations
TL;DR: In this article, the authors present a design methodology that integrates an aircraft performance model with a program valuation technique based on real options theory to address uncertain market demand and managerial flexibility, and demonstrate that use of value as a design metric leads to a trade-off between aerodynamic efficiency and reduced manufacturing costs.
Abstract: Traditional commercial aircraft design attempts to improve performance and reduce operating costs by minimizing takeoff weight. A better design approach also takes into account factors such as aircraft demand, market uncertainty, and development and manufacturing costs. This paper presents a design methodology that integrates an aircraft performance model with a program valuation technique based on real options theory to address uncertain market demand and managerial flexibility. The coupled performance/financial framework enables an integrated approach to technical design and programmatic decisions. In addition, the methodology provides a framework for specification of design requirements and for quantification of the financial implications associated with technical and business uncertainty. The methodology is demonstrated for an aircraft design example of the blended-wing-body concept. Comparing performance-optimized and value-optimized designs, we show that use of value as a design metric leads to a trade-off between aerodynamic efficiency and reduced manufacturing costs. Key findings demonstrate that traditional financial metrics cause the decision maker to focus overly on reducing costs in the short term. The stochastic methodology shows that a willingness to spend up-front money in the design process to ensure long-term profitability is a better strategy.
32 citations
TL;DR: In this article, a coupled fluid-structure method is developed for flutter analysis of blade vibrations in turbomachinery, which is based on the time domain solution of the fluidstructure interaction in which the aerodynamic and structural equations are marched simultaneously in time.
28 citations
TL;DR: In this paper, the improved line sampling (LS) technique is employed to analyze the probabilistic characteristics and reliability sensitivity of flutter with random structural parameter in transonic flow.
21 citations
TL;DR: In this paper, an Integral Input-to-State Stability (iISS) controller was used for the nonlinear flutter suppression of a typical wing section. And a Lyapunov-based controller was also introduced for the system.
Abstract: The nonlinear flutter suppression of a typical wing section is investigated. A structural nonlinearity is considered in the pitch direction. Integral-input-to-state stability (iISS) concept is utilised for the construction of a feedback controller. One of the advantages of this design is its simplicity and straightforwardness. A backstepping method is used to compare the results for the typical section, which is a multi-input system. The iISS controller has an outstanding performance in comparison to the backstepping method, especially with regards to the disturbance attenuation problem. A Lyapunov-based controller was also introduced for the system.
19 citations