High Fidelity Multidisciplinary Optimization (HFMDO)

Alston, Katherine; Doyle, Steven; Winter, Tyler; Kim, Hongman; Integration, Phoenix

doi:10.2514/6.2010-1314

Cited by 4 publications

(10 citation statements)

References 1 publication

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“…These equations are solved using the NASA MASCOT trim analysis code. [3][4][5][6] Equilibrium or trim solutions are found using optimization. The terms in the equations of motion are moved to one side, creating nine residual equations that must equal zero simultaneously.…”

Section: Solving the Nonlinear Rigid Body Equations Of Motionmentioning

confidence: 99%

Power Efficient Trim Solutions for the Hybrid Wing Body in Approach Conditions

Garmendia

Mavris

2015

AIAA Atmospheric Flight Mechanics Conference

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The presence of control redundancy in configurations such as the Hybrid Wing Body can result in non-unique trim trim solutions. This can be taken advantage of to minimize a secondary metric in addition to balancing the forces and moments acting on the vehicle. In a previous study, drag was investigated as a secondary metric and was found to work well for several flight conditions. For the approach flight condition, however, the minimum drag solution was found to require a thrust below an assumed approach idle throttle. A different metric must be used in the presence of an active throttle constraint during optimization. Actuation power requirements are known to be a subject of much uncertainty and high risk for the Hybrid Wing Body configuration. Trim solutions that help keep actuation power requirements low are therefore worth investigating. A metric based on control surface hinge moments was developed and used for trim optimization analyses. Under the assumption of electrical actuation systems, it can be used as a stand-in for steady state power in early design phases. The metric was successfully used to identify trim solutions that will likely have low steady state power requirements. The optimizer was able to achieve low power trim solutions by allowing several elevons to float to their neutral hinge moment positions, while using a single pair of elevons to trim the remaining pitching moments. The sensitivity of the minimum power trim solution to deflection limits and the use of trim-only devices was also investigated.

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Section: Solving the Nonlinear Rigid Body Equations Of Motionmentioning

confidence: 99%

Power Efficient Trim Solutions for the Hybrid Wing Body in Approach Conditions

Garmendia

Mavris

2015

AIAA Atmospheric Flight Mechanics Conference

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“…The first example of this is a dedicated model for the geometry which aims to provide a central representation of the aircraft in order to be used by other analyses like for instance in aerodynamics or structures [12,41,45,[57][58][59]. Overall, a fast and robust geometry model that is also compatible with the other disciplines is often stressed as one of the main enablers for a seamless MDO [17,35,60,61], while at the same time, it is important to be able to capture the given problem [27] and have a flexible parametrization that can not only cover the design space but also offer the desired level of detail [32,55,56,62]. Secondly, it can be seen that a model for the stability and trim is usually present in the majority of MDO frameworks so that the trimmed state can be identified and ensure that the optimizer compares designs which share acceptable stability characteristics [17,63,64].…”

Section: Disciplinary Modelsmentioning

confidence: 99%

Multidisciplinary Design Optimization of Aerial Vehicles: A Review of Recent Advancements

Παπαγεωργίου

Tarkian

Amadori

et al. 2018

International Journal of Aerospace Engineering

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The aim of this paper is to present the most common practices in multidisciplinary design optimization (MDO) of aerial vehicles over the past decade. The literature sample is identified through established internet search engines, and a stringent review methodology is implemented in order to ensure the selection of the most relevant sources. In this work, the primary emphasis is on the assessment of the state-of-the-art framework development strategies, while at a secondary level, the objective is to identify the possible improvement directions by evaluating the research trends and gaps. As an additional contribution, statistical studies are also provided, and it is shown how MDO of aerial vehicles has evolved in terms of problem formulation, disciplinary modeling, analysis capabilities, tool implementation, and general applicability. Given this foundation as well as the results of the review, this work concludes by presenting a roadmap for guiding academia and industry in respect to the application of MDO on aerial vehicles. Overall, the roadmap together with the literature review is not only expected to serve as a guide for newcomers into the MDO field but also as an elementary basis which will allow researchers to conduct additional studies in this important and constantly evolving area of design.

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“…Various coupled ASDO frameworks are developed in the past decades [3][4][5]. Typical applications include the detailed wing optimization, winglet design [6], supersonic aircraft design [7,8], and so forth.…”

Section: Introductionmentioning

confidence: 99%

Advanced Aerostructural Optimization Techniques for Aircraft Design

Zuo

Chen²,

et al. 2015

Mathematical Problems in Engineering

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Traditional coupled aerostructural design optimization (ASDO) of aircraft based on high-fidelity models is computationally expensive and inefficient. To improve the efficiency, the key is to predict aerostructural performance of the aircraft efficiently. The cruise shape of the aircraft is parameterized and optimized in this paper, and a methodology named reverse iteration of structural model (RISM) is adopted to get the aerostructural performance of cruise shape efficiently. A new mathematical explanation of RISM is presented in this paper. The efficiency of RISM can be improved by four times compared with traditional static aeroelastic analysis. General purpose computing on graphical processing units (GPGPU) is adopted to accelerate the RISM further, and GPU-accelerated RISM is constructed. The efficiency of GPU-accelerated RISM can be raised by about 239 times compared with that of the loosely coupled aeroelastic analysis. Test shows that the fidelity of GPU-accelerated RISM is high enough for optimization. Optimization framework based on Kriging model is constructed. The efficiency of the proposed optimization system can be improved greatly with the aid of GPU-accelerated RISM. An unmanned aerial vehicle (UAV) is optimized using this framework and the range is improved by 4.67% after optimization, which shows effectiveness and efficiency of this framework.

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High Fidelity Multidisciplinary Optimization (HFMDO)

Cited by 4 publications

References 1 publication

Power Efficient Trim Solutions for the Hybrid Wing Body in Approach Conditions

Power Efficient Trim Solutions for the Hybrid Wing Body in Approach Conditions

Multidisciplinary Design Optimization of Aerial Vehicles: A Review of Recent Advancements

Advanced Aerostructural Optimization Techniques for Aircraft Design

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