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Автор: Grafiati

Опубліковано: 14 березня 2023

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1

Tovar, Andres, Nelson Arzola de la Peña, and Alexander Gómez Cassab. "Multidisciplinary design optimisation techniques." Ingeniería e Investigación 27, no. 1 (January 1, 2007): 84–92. http://dx.doi.org/10.15446/ing.investig.v27n1.14785.

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Design optimisation of a multidisciplinary project in engineering involves the decomposition of a system into disciplines and the subsequent association of their contributions. This work was aimed at presenting the most common decomposition and association techniques currently used in multidisciplinary design optimisation (MDO). Amongst the decomposition techniques this work includes hierarchical and non-hierarchical approaches as well as the most popular numerical procedures. The association techniques include: one-level methods (e.g. all-at-once optimisation and simultaneous analysis and design), multilevel methods (e.g. concurrent subspace optimisation and collaborative optimisation) and robust design. This work also incorporates an illustrative numerical example.

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2

Lee, Dong Seop, J. Periaux, L. F. Gonzalez, K. Srinivas, and E. Onate. "Robust multidisciplinary UAS design optimisation." Structural and Multidisciplinary Optimization 45, no. 3 (September 9, 2011): 433–50. http://dx.doi.org/10.1007/s00158-011-0705-0.

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3

Lee, Kyu-Yeul, Myung-Il Roh, and Seonho Cho. "Multidisciplinary design optimisation of mechanical systems using collaborative optimisation approach." International Journal of Vehicle Design 25, no. 4 (2001): 353. http://dx.doi.org/10.1504/ijvd.2001.005207.

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4

Mariens, J., A. Elham, and M. J. L. van Tooren. "Influence of weight modelling on the outcome of wing design using multidisciplinary design optimisation techniques." Aeronautical Journal 117, no. 1195 (September 2013): 871–95. http://dx.doi.org/10.1017/s0001924000008563.

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Abstract Weight estimation methods are categorised in different classes based on their level of fidelity. The lower class methods are based on statistical data, while higher class methods use physics based calculations. Statistical weight estimation methods are usually utilised in early design stages when the knowledge of designers about the new aircraft is limited. Higher class methods are applied in later design steps when the design is mature enough. Lower class methods are sometimes preferred in later design stages, even though the designers have enough knowledge about the design to use higher class methods. In high level multidisciplinary design optimisation (MDO) fidelity is often sacrificed to obtain models with shorter computation times. There is always a compromise required to select the proper weight estimation method for an MDO project. An investigation has been performed to study the effect of using different weight estimation methods, with low and medium levels of fidelity, on the results of a wing design using multidisciplinary design optimisation techniques. An MDO problem was formulated to design the wing planform of a typical turboprop and a turbofan passenger aircraft. The aircraft maximum take-off weight was selected as the objective function. A quasi-three-dimensional aerodynamic solver was developed to calculate the wing aerodynamic characteristics. Five various statistical methods and a quasi-analytical method are used to estimate the wing structural weight. These methods are compared to each other by analysing their accuracy and sensitivity to different design variables. The results of the optimisations showed that the optimum wing shape is affected by the method used to estimate the wing weight. Using different weight estimation methods also strongly affects the optimisation convergence history and computational time.

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5

Bäckryd, R. D., A. B. Ryberg, and L. Nilsson. "Multidisciplinary design optimisation methods for automotive structures." INTERNATIONAL JOURNAL OF AUTOMOTIVE AND MECHANICAL ENGINEERING 14, no. 1 (March 30, 2017): 4050–67. http://dx.doi.org/10.15282/ijame.14.1.2017.17.0327.

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6

Giassi, A., F. Bennis, and J. J. Maisonneuve. "Multidisciplinary design optimisation and robust design approaches applied to concurrent design." Structural and Multidisciplinary Optimization 28, no. 5 (August 4, 2004): 356–71. http://dx.doi.org/10.1007/s00158-004-0417-9.

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7

Van Nguyen, N., J. W. Lee, Y. D. Lee, and H. U. Park. "A multidisciplinary robust optimisation framework for UAV conceptual design." Aeronautical Journal 118, no. 1200 (February 2014): 123–42. http://dx.doi.org/10.1017/s0001924000009027.

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Abstract This paper describes a multidisciplinary robust optimisation framework for UAV conceptual design. An in-house configuration designer system is implemented to generate the full sets of configuration data for a well-developed advanced UAV analysis tool. A fully integrated configuration designer along with the UAV analysis tool ensures that full sets of configuration data are provided simultaneously while the UAV configuration changes during optimisation. The computational strategy for probabilistic analysis is proposed by implementing a central difference method and fitting distribution for a reduced number of Monte Carlo Simulation sampling points. The minimisation of a new robust design objective function helps to enhance the reliability while other UAV performance criteria are satisfied. In addition, the fully integrated process and a probabilistic analysis strategy method demonstrate a reduction in the probability of failure under noise factors without any noticeable increase in design turnaround time. The proposed robust optimisation framework for UAV conceptual design case study yields a more trustworthy prediction of the optimal configuration and is preferable to the traditional deterministic design approach. The high fidelity analysis ANSYS Fluent 13 is performed to demonstrate the accuracy of proposed framework on baseline, deterministic and RDO configuration.

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8

He, Jim, Shari Hannapel, David Singer, and Nickolas Vlahopoulos. "Multidisciplinary Design Optimisation of a Ship Hull Using Metamodels." Ship Technology Research 58, no. 3 (September 2011): 156–66. http://dx.doi.org/10.1179/str.2011.58.3.004.

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9

Campana, Emilio Fortunato, Giovanni Fasano, and Daniele Peri. "Penalty function approaches for ship multidisciplinary design optimisation (MDO)." European J. of Industrial Engineering 6, no. 6 (2012): 765. http://dx.doi.org/10.1504/ejie.2012.051076.

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10

Harris, J. C., and S. V. Fenwick. "The application of Pareto methods to multidisciplinary design optimisation." Aeronautical Journal 105, no. 1048 (June 2001): 329–34. http://dx.doi.org/10.1017/s0001924000012215.

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Анотація:

Abstract Multidisciplinary design optimisation (MDO) provides a framework for the timely exchange of data necessary to support the highly integrated tasks typical of aerospace design. This will help reduce the duration of the design cycle and improve efficiency of the final product. Well implemented MDO capabilities will play an increasingly important role in DERA's activities to support the definition of future system requirements and the assessment of new equipment. The framework in which an MDO approach is realised must be flexible and accommodate the diverse range of individual discipline-based tools that contribute to the overall process. This paper describes DERA's activity within the EC Framework IV ‘FRONTIER’ project to investigate the use of modern graphical user interface (GUI) methods and genetic algorithms (GAs) for the combined aerodynamic and structural design of a modern combat aircraft. The application of the techniques to identify a Pareto frontier in high level design objective space that represents the boundary beyond which improvements cannot be made without sacrificing one or other aspect of overall aircraft performance is described. The scope of the methods as an aid during the definition of system requirements and for the evaluation of trade-offs during the concept assessment stage of a project is discussed.

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11

Stander, J. N., G. Venter, and M. J. Kamper. "High fidelity multidisciplinary design optimisation of an electromagnetic device." Structural and Multidisciplinary Optimization 53, no. 5 (December 10, 2015): 1113–27. http://dx.doi.org/10.1007/s00158-015-1375-0.

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12

Wang, Chengen. "Advances in information integration infrastructures supporting multidisciplinary design optimisation." Enterprise Information Systems 6, no. 3 (August 2012): 265. http://dx.doi.org/10.1080/17517575.2011.653833.

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13

Reneke, James A., Margaret M. Wiecek, Georges M. Fadel, and Sundeep Samson. "Multidisciplinary design optimisation under uncertainty: an information model approach." International Journal of Vehicle Design 61, no. 1/2/3/4 (2013): 249. http://dx.doi.org/10.1504/ijvd.2013.050848.

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14

Nguyen, N. V., J. W. Lee, M. Tyan, and D. Lee. "Possibility-Based Multidisciplinary Optimisation For Electric-Powered Unmanned Aerial Vehicle Design." Aeronautical Journal 119, no. 1221 (November 2015): 1397–414. http://dx.doi.org/10.1017/s0001924000011313.

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AbstractThis paper describes a possibility-based multidisciplinary optimisation for electric-powered unmanned aerial vehicles (UAVs) design. An in-house integrated UAV (iUAV) analysis program that uses an electric-powered motor was developed and validated by a Predator A configuration for aerodynamics, weight, and performance parameters. An electric-powered propulsion system was proposed to replace a piston engine and fuel with an electric motor, power controllers, and battery from an eco-system point of view. Moreover, an in-house Possibility-Based Design Optimisation (iPBDO) solver was researched and developed to effectively handle uncertainty variables and parameters and to further shift constraints into a feasible design space. A sensitivity analysis was performed to reduce the dimensions of design variables and the computational load during the iPBDO process. Maximising the electric-powered UAV endurance while solving the iPBDO yields more conservative, but more reliable, optimal UAV configuration results than the traditional deterministic optimisation approach. A high fidelity analysis was used to demonstrate the effectiveness of the process by verifying the accuracy of the optimal electric-powered UAV configuration at two possibility index values and a baseline.

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15

Giunta, A. A., V. Balabanov, D. Haim, B. Grossman, W. H. Mason, L. T. Watson, and R. T. Haftka. "Multidisciplinary optimisation of a supersonic transport using design of experiments theory and response surface modelling." Aeronautical Journal 101, no. 1008 (October 1997): 347–56. http://dx.doi.org/10.1017/s0001924000066045.

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AbstractThe presence of numerical noise in engineering design optimisation problems inhibits the use of many gradient-based optimisation methods. This numerical noise may result in the inaccurate calculation of gradients which in turn slows or prevents convergence during optimisation, or it may promote convergence to spurious local optima. The problems created by numerical noise are particularly acute in aircraft design applications where a single aerodynamic or structural analysis of a realistic aircraft configuration may require tens of CPU hours on a supercomputer. The computational expense of the analyses coupled with the convergence difficulties created by numerical noise are significant obstacles to performing aircraft multidisciplinary design optimisation. To address these issues, a procedure has been developed to create noise-free algebraic models of subsonic and supersonic aerodynamic performance quantities, for use in the optimisation of high-speed civil transport (HSCT) aircraft configurations. This procedure employs methods from statistical design of experiments theory and response surface modelling to create the noise-free algebraic models. Results from a sample HSCT design problem involving ten variables are presented to demonstrate the utility of this method.

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16

Pagliuca, G., T. Kipouros, and M. A. Savill. "Surrogate Modelling for Wing Planform Multidisciplinary Optimisation Using Model-Based Engineering." International Journal of Aerospace Engineering 2019 (May 9, 2019): 1–15. http://dx.doi.org/10.1155/2019/4327481.

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Optimisation is aimed at enhancing aircraft design by identifying the most promising wing planforms at the early stage while discarding the least performing ones. Multiple disciplines must be taken into account when assessing new wing planforms, and a model-based framework is proposed as a way to include mass estimation and longitudinal stability alongside aerodynamics. Optimisation is performed with a particle swarm optimiser, statistical methods are exploited for mass estimation, and the vortex lattice method (VLM) with empirical corrections for transonic flow provides aerodynamic performance. Three surrogates of the aerodynamic model are investigated. The first one is based on radial basis function (RBF) interpolation, and it relies on a precomputed database to evaluate the performance of new wing planforms. The second one is based on an artificial neural network, and it needs precomputed data for a training step. The third one is a hybrid model which switches automatically between VLM and RBF, and it does not need any precomputation. Its switching criterion is defined in an objective way to avoid any arbitrariness. The investigation is reported for a test case based on the common research model (CRM). Reference results are produced with the aerodynamic model based on VLM for two- and three-objective optimisations. Results from all surrogate models for the same benchmark optimisation are compared so that their benefits and limitations are both highlighted. A discussion on specific parameters, such as number of samples for example, is given for each surrogate. Overall, a model-based implementation with a hybrid model is proposed as a compromise between versatility and an arbitrary level of accuracy for wing early-stage design.

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17

Mosca, V., S. Karpuk, A. Sudhi, C. Badrya, and A. Elham. "Multidisciplinary design optimisation of a fully electric regional aircraft wing with active flow control technology." Aeronautical Journal 126, no. 1298 (October 28, 2021): 730–54. http://dx.doi.org/10.1017/aer.2021.101.

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AbstractThe German research Cluster of Excellence SE2A (Sustainable and Energy Efficient Aviation) is investigating different technologies to be implemented in the following decades, to achieve more efficient air transportation. This paper studies the Hybrid Laminar Flow Control (HLFC) using boundary layer suction for drag reduction, combined with other technologies for load and structural weight reduction and a novel full-electric propulsion system. A multidisciplinary design optimisation framework is presented, enabling physics-based analysis and optimisation of a fully electric aircraft wing equipped with HLFC technologies and load alleviation, and new structures and materials. The main focus is on simulation and optimisation of the boundary layer suction and its influence on wing design and optimisation. A quasi three-dimensional aerodynamic analysis is used for drag estimation of the wing. The tool executes the aerofoil analysis using XFOILSUC, which provides accurate drag estimation through boundary layer suction. The optimisation is based on a genetic algorithm for maximum take-off weight (MTOW) minimisation. The optimisation results show that the active flow control applied on the optimised geometry results in more than 45% reduction in aircraft drag coefficient, compared to the same geometry without HLFC technology. The power absorbed for the HLFC suction system implies a battery mass variation lower than 2%, considering the designed range as top-level requirement (TLR).

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18

Kianifar, Mohammed Reza, and Felician Campean. "Global Optimisation of Car Front-End Geometry to Minimise Pedestrian Head Injury Levels." Proceedings of the Design Society: International Conference on Engineering Design 1, no. 1 (July 2019): 2873–82. http://dx.doi.org/10.1017/dsi.2019.294.

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AbstractThe paper presents a multidisciplinary design optimisation strategy for car front-end profile to minimise head injury criteria across pedestrian groups. A hybrid modelling strategy was used to simulate the car- pedestrian impact events, combining parametric modelling of front-car geometry with pedestrian models for the kinematics of crash impact. A space filling response surface modelling strategy was deployed to study the head injury response, with Optimal Latin Hypercube (OLH) Design of Experiments sampling and Kriging technique to fit response models. The study argues that the optimisation of the front-end car geometry for each of the individual pedestrian models, using evolutionary optimisation algorithms is not an effective global optimization strategy as the solutions are not acceptable for other pedestrian groups. Collaborative Optimisation (CO) multidisciplinary design optimisation architecture is introduced instead as a global optimisation strategy, and proven that it can enable simultaneous minimisation of head injury levels for all the pedestrian groups, delivering a global optimum solution which meets the safety requirements across the pedestrian groups.

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19

Benkhelifa, Elhadj, Ashutosh Tiwari, and Mohamed Abdel-Maguid. "Advanced Design Optimisation by Means of Multiobjective Evolutionary Algorithms: The Case of Two Real World Applications." Key Engineering Materials 572 (September 2013): 589–92. http://dx.doi.org/10.4028/www.scientific.net/kem.572.589.

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The Design Optimisation (DO) of Complex Systems is often a multidisciplinary task and involves multiple conflicting objectives and design constraints, where conventional methods cannot solve efficiently. This paper presents Advanced DO by Means of Evolutional Algorithms in two Real World Applications Electronics and Micro-Electro-Mechanical-Systems (MEMS). The former is presented in the context of multi-objective evolutionary synthesis and optimisation of analogue systems. As for the latter, DO of MEMS bio-mimetically is a very novel area of research, Which addresses the compelling change in the traditional landscape of the associated research disciplines by seeking to provide a novel biologically inspired computational platform for DO of micro-scale designs. This paper presents the latest advancements in the application of EAs in the DO of MEMS and analogue electronic systems and the emergence of the new area of Multidisciplinary Optimisation'.

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20

Henderson, R. P., J. R. R. A. Martins, and R. E. Perez. "Aircraft conceptual design for optimal environmental performance." Aeronautical Journal 116, no. 1175 (January 2012): 1–22. http://dx.doi.org/10.1017/s000192400000659x.

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Abstract Consideration of the environmental impact of aircraft has become critical in commercial aviation. The continued growth of air traffic has caused increasing demands to reduce aircraft emissions, imposing new constraints on the design and development of future airplane concepts. In this paper, an aircraft design optimisation framework is used to design aircraft that minimise specific environmental metrics. Multidisciplinary design optimisation is used to optimise aircraft by simultaneously considering airframe, engine and mission. The environmental metrics considered in this investigation are CO2 emissions — which are proportional to fuel burn — and landing-takeoff NOx emissions. The results are compared to those of an aircraft with minimum direct operating cost. The design variables considered in the optimisation problems include aircraft geometry, engine parameters, and cruise settings. An augmented Lagrangian particle swarm optimiser and a genetic algorithm are used to solve the single objective and multi-objective optimisation problems, respectively.

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21

Ma, Zheng-Dong, and Chang Qi. "Multidisciplinary design optimisation of elastomeric mounting systems in automotive vehicles." International Journal of Product Development 1, no. 3/4 (2005): 365. http://dx.doi.org/10.1504/ijpd.2005.005947.

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22

Wang, Hao, Shaoping Wang, and Mileta M. Tomovic. "Multidisciplinary integrated design optimisation platform and application on active suspension." International Journal of Manufacturing Technology and Management 19, no. 3/4 (2010): 211. http://dx.doi.org/10.1504/ijmtm.2010.031369.

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23

ONEL, Alexandru-Iulian, and Teodor-Viorel CHELARU. "Trajectory assessment and optimisation in the context of small launcher design." INCAS BULLETIN 12, no. 2 (June 5, 2020): 117–32. http://dx.doi.org/10.13111/2066-8201.2020.12.2.10.

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The paper presents a mathematical model that can be used to quickly define a nominal trajectory for the studied small launcher configuration. The tool developed based on the proposed mathematical model can be used separately for trajectory assessments or it can be integrated in a multidisciplinary optimisation algorithm for a preliminary small launcher design, together with the trajectory optimisation for a maximum orbital performance.

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24

Rajagopal, S., and R. Ganguli. "Conceptual design of UAV using Kriging based multi-objective genetic algorithm." Aeronautical Journal 112, no. 1137 (November 2008): 653–62. http://dx.doi.org/10.1017/s0001924000002621.

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Abstract This paper highlights unmanned aerial vehicle (UAV) conceptual design using the multi-objective genetic algorithm (MOGA). The design problem is formulated as a multidisciplinary design optimisation (MDO) problem by coupling aerodynamic and structural analysis. The UAV considered in this paper is a low speed, long endurance aircraft. The optimisation problem uses endurance maximization and wing weight minimisation as dual objective functions. In this multi-objective optimisation, aspect ratio, wing loading, taper ratio, thickness-to-chord ratio, loiter velocity and loiter altitude are considered as design variables with stall speed, maximum speed and rate of climb as constraints. The MDO system integrates the aircraft design code, RDS and an empirical relation for objective function evaluation. In this study, the optimisation problem is solved in two approaches. In the first approach, the RDS code is directly integrated in the optimisation loop. In the second approach, Kriging model is employed. The second approach is fast and efficient as the meta-model reduces the time of computation. A relatively new multi-objective evolutionary algorithm named NSGA-II (non-dominated sorting genetic algorithm) is used to capture the full Pareto front for the dual objective problem. As a result of optimisation using multi-objective genetic algorithm, several non-dominated solutions indicating number of useful Pareto optimal designs is identified.

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25

Kodiyalam, Srinivas, and Jaroslaw Sobieszczanski-Sobieski. "Multidisciplinary design optimisation - some formal methods, framework requirements, and application to vehicle design." International Journal of Vehicle Design 25, no. 1/2 (2001): 3. http://dx.doi.org/10.1504/ijvd.2001.001904.

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26

Li, Ying, Ping Jiang, Liang Gao, and Xinyu Shao. "Sequential optimisation and reliability assessment for multidisciplinary design optimisation under hybrid uncertainty of randomness and fuzziness." Journal of Engineering Design 24, no. 5 (May 2013): 363–82. http://dx.doi.org/10.1080/09544828.2012.753995.

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27

Perez-Moreno, S. Sanchez, K. Dykes, K. O. Merz, and M. B. Zaaijer. "Multidisciplinary design analysis and optimisation of a reference offshore wind plant." Journal of Physics: Conference Series 1037 (June 2018): 042004. http://dx.doi.org/10.1088/1742-6596/1037/4/042004.

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28

Sobieszczanski-Sobieski, Jaroslaw. "Multidisciplinary design optimisation (MDO) methods: their synergy with computer technology in the design process." Aeronautical Journal 103, no. 1026 (August 1999): 373–82. http://dx.doi.org/10.1017/s0001924000064599.

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Abstract The paper identifies speed, agility, human interface, generation of sensitivity information, task decomposition, and data transmission (including storage) as important attributes for a computer environment to have in order to support engineering design effectively. It is argued that when examined in terms of these attributes the presently available environment can be shown to be inadequate. A radical improvement is needed, and it may be achieved by combining new methods that have recently emerged from multidisciplinary design optimisation (MDO) with massively parallel processing computer technology. The caveat is that, for successful use of that technology in engineering computing, new paradigms for computing will have to be developed - specifically, innovative algorithms that are intrinsically parallel so that their performance scales up linearly with the number of processors. It may be speculated that the idea of simulating a complex behaviour by interaction of a large number of very simple models may be an inspiration for the above algorithms; the cellular automata are an example. Because of the long lead time needed to develop and mature new paradigms, development should begin now, even though the widespread availability of massively parallel processing is still a few years away.

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29

Ali, F., K. Tzanidakis, I. Goulos, V. Pachidis, and R. d’Ippolito. "Multidisciplinary design and optimisation of conceptual rotorcraft powerplants for operational performance and environmental impact." Aeronautical Journal 119, no. 1217 (July 2015): 891–914. http://dx.doi.org/10.1017/s0001924000010976.

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AbstractThis paper demonstrates the application of an integrated rotorcraft multidisciplinary design and optimisation framework, deployed for the purpose of preliminary design and assessment of optimum regenerative powerplant configurations for rotorcraft applications. The proposed approach comprises a wide-range of individual modelling theories applicable to rotorcraft flight dynamics, gas turbine engine performance and weight estimation as well as a physics-based stirred reactor model, for the rapid estimation of various gas turbine gaseous emissions. A single-objective Particle Swarm Optimiser is coupled with the aforementioned rotorcraft design framework. The overall methodology is deployed for the design and optimisation of a reference multipurpose Twin-Engine-Light civil rotorcraft, modelled after the Bo105 helicopter, which employs two Rolls-Royce Allison 250-C20B turboshaft engines. Through the implementation of a single-objective optimisation strategy, notionally based optimum engine design configurations are acquired in terms of engine weight, mission fuel burn and mission gaseous emissions inventory at constant technology level.The acquired optimum regenerative engine configurations are subsequently deployed for the design of conceptual rotorcraft regenerative engine configurations, targeting improved mission fuel economy, enhanced payload-range capability as well as overall environmental impact, while maintaining the respective rotorcraft airworthiness requirements. The proposed methodology essentially constitutes as an enabler for designing rotorcraft powerplants within realistic, three-dimensional operations and towards realising their associated design trade-offs at mission level.

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30

Shukla, Suchita, Abhishek Singh, Atul Singh, and Neelam Srivastava. "Optimisation of Cognitive Engine Design using Cultural Algorithm." Indian Journal of Science and Technology 10, no. 21 (June 1, 2017): 1–15. http://dx.doi.org/10.17485/ijst/2017/v10i21/113400.

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31

Khosroshahi, Siamak Farajzadeh, Marinella Masina, Alessandro Antonini, Edward Ransley, James Mark William Brownjohn, Peter Dobson, and Dina D’Ayala. "A Multidisciplinary Computational Framework for Topology Optimisation of Offshore Helidecks." Journal of Marine Science and Engineering 10, no. 9 (August 24, 2022): 1180. http://dx.doi.org/10.3390/jmse10091180.

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Maintaining offshore steel structures is challenging and not environmentally friendly due to the frequent visits for inspection and repairs. Some offshore lighthouses are equipped with carbon steel helidecks fixed onto their lantern galleries in the 1970s to provide easy and safe access to maintenance staff and inspectors. Even though the helidecks supporting structures have maintained their integrity and are still functional in the offshore harsh environmental conditions, their inspection and maintenance remains a challenge due to the need of frequent visits which requires flying to the location of the lighthouse to bring the maintenance staff and equipment. We have developed a multidisciplinary computational framework to design new generation of aluminium helidecks for offshore lighthouses. We calculated the wind speed at the location of the Bishop Rock lighthouse based on the meteorological data, and the load distribution on the helideck due to such a wind condition, using computational fluid dynamic analysis. Then, we used the calculated wind load with other mechanical loads in the events of normal and emergency landings of a helicopter on this structure to find the best design configuration for this helideck. We generated a design space for different configurations of a beam structure and carried out, static, transient and buckling analysis to assess each case using finite element method. The selection criterion was set to find the structure with the minimum volume fraction and compliance while keeping the stress below the allowable stress. We found the structure with eight vertical and circumferential sections featuring two rows of diagonal bracing with one at the base and the other one at the third section from the base of the helideck was the optimum design for the considered loading in this work. This framework can be adopted for the design and optimisation of other offshore structures by other researchers and designers.

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32

Sferza, Massimo, Jelena Ninić, Dimitrios Chronopoulos, Florian Glock, and Fernass Daoud. "Multidisciplinary Optimisation of Aircraft Structures with Critical Non-Regular Areas: Current Practice and Challenges." Aerospace 8, no. 8 (August 12, 2021): 223. http://dx.doi.org/10.3390/aerospace8080223.

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The design optimisation of aerostructures is largely based on Multidisciplinary Design Optimisation (MDO), which is a set of tools used by the aircraft industry to size primary structures: wings, large portions of the fuselage or even an entire aircraft. The procedure is computationally expensive, as it must account for several thousands of loadcases, multiple analyses with hundreds of thousands of degrees of freedom, thousands of design variables and millions of constraints. Because of this, the coarse Global Finite Element Model (GFEM), on which the procedure is based, cannot be further refined. The structures represented in the GFEM contain many components and non-regular areas, which require a detailed modelling to capture their complex mechanical behaviour. Instead, in the GFEM, these components are represented by simplified models with approximated stiffness, whose main role is to contribute to the identification of the load paths over the whole structure. Therefore, these parts are kept fixed and are not constrained during the optimisation, as the description of their internal deformation is not sufficiently accurate. In this paper, we show that it would nevertheless be desirable to size the non-regular areas and the overall structures at once. Firstly, we introduce the concept of non-regular areas in the context of a structural airframe MDO. Secondly, we present a literature survey on MDO with a critical review of several architectures and their current applications to aircraft design optimisation. Then, we analyse and demonstrate with examples the possible consequences of neglecting non-regular areas when MDO is applied. In the conclusion, we analyse the requirements for alternative approaches and why the current ones are not viable solutions. Lastly, we discuss which characteristics of the problem could be exploited to contain the computational cost.

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33

Perez-Moreno, S. Sanchez, M. B. Zaaijer, C. L. Bottasso, K. Dykes, K. O. Merz, P.-E. Réthoré, and F. Zahle. "Roadmap to the multidisciplinary design analysis and optimisation of wind energy systems." Journal of Physics: Conference Series 753 (September 2016): 062011. http://dx.doi.org/10.1088/1742-6596/753/6/062011.

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34

Sinsay, J. D. "Re-imagining rotorcraft advanced design." Aeronautical Journal 122, no. 1256 (October 2018): 1497–521. http://dx.doi.org/10.1017/aer.2018.107.

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ABSTRACTAdvanced design offices have traditionally applied conceptual design techniques based on semi-empirical methods in an attempt to develop an accurate prediction of aircraft designs at the end of the development process. Continuing advances in computer capability and rotorcraft analysis software present an opportunity to re-think conceptual design to include the greater use of physics-based analyses. A roadmap for developing this capability is outlined, taking into account techniques and ideas from Model-Based Systems Engineering, Design Thinking and Multidisciplinary Optimisation. Recent activities that demonstrate some of these desired capabilities are briefly described along with lessons learned.

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35

ONEL, Alexandru-Iulian, and Teodor-Viorel CHELARU. "Aerodynamic assessment of axisymmetric launchers in the context of multidisciplinary optimisation." INCAS BULLETIN 12, no. 1 (March 1, 2020): 135–44. http://dx.doi.org/10.13111/2066-8201.2020.12.1.13.

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The paper presents a fast mathematical model that can be used to quickly assess the aerodynamic force coefficients of axisymmetric launchers as functions of Mach number and angle of attack. The tool developed based on the proposed mathematical model can be used separately or it can be integrated in a multidisciplinary optimisation algorithm for a preliminary small launcher design.

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36

Shahpar, S. "Challenges to overcome for routine usage of automatic optimisation in the propulsion industry." Aeronautical Journal 115, no. 1172 (October 2011): 615–25. http://dx.doi.org/10.1017/s0001924000006308.

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Abstract In industry, there is an ever-increasing requirement not only to design high performance new products but also to deliver them at lower cost and in shorter time. To meet these demanding engineering challenges, it is not sufficient to treat the different disciplines involved in a product design in isolation; rather they must be considered together as an integrated system that reflects the dependencies and interactions of the different disciplines. The design process must be automated to meet the stringent design time-lines. In spite of promising forays for over a decade, automatic design optimisation (ADO) and multidisciplinary optimisation (MDO) has not been widely adapted by the Turbomachinery design practitioners. This presentation will explore some of the technical and nontechnical barriers such as cultural and organisational issues that must be addressed if ADO/MDO is to be used routinely in industry. Some recent, successful application of automatic optimisation is also reported herein.

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37

Zheng, Lingyu, Daxu Zhang, Long Wang, Aman Shrestha, Zhensen Song, Shengbin Gao, Teng Xu, and Mingming Xu. "Lightweight cylindrical composite shell structures to support optical instruments in extremely large telescopes: A case study." Science Progress 104, no. 3 (July 2021): 003685042110361. http://dx.doi.org/10.1177/00368504211036147.

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Aiming at the issues of heavy weight and insufficient structural performance of optical instrument supporting structures in extremely large telescopes, the Wide-Field Optical Spectrograph (WFOS) of the Thirty Meter Telescope (TMT) was taken as a case to study. In order to develop lightweight structures which satisfies the design requirements for mass and stiffness, a design scheme of cylindrical composite shells supporting structure was proposed and their finite element models were developed. A size optimisation and a ply sequence optimisation of the composite structure were carried out. The structures before and after optimisation were evaluated from the aspects of mass, displacement, failure index and fundamental frequency. After the optimised design, the mass of the optimised WFOS cylindrical composite shell structure is reduced to approximately 50%, but its maximum displacement (0.513 mm) and fundamental frequency (8.275 Hz) are nearly unchanged. The study indicates that a cylindrical composite shell structure is an efficient structural form for large optical instruments.

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38

Cosyn, P., and J. Vierendeels. "Design of fixed wing micro air vehicles." Aeronautical Journal 111, no. 1119 (May 2007): 315–26. http://dx.doi.org/10.1017/s0001924000004565.

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Abstract The paper describes the methodology and computational design strategies used to develop a series of fixed wing micro air vehicles (MAVs) at the Ghent University. The emphasis of the research is to find an optimal MAV-platform that is bound to geometrical constraints but superior in its performance. This requires a multidisciplinary design optimisation but the challenges are mainly of aerodynamic nature. Key areas are endurance, stability, controllability, manoeuvrability and component integration. The highly three-dimensional low Reynolds number flow, the lack of experimental databases and analytical or empirical models of MAV-aerodynamics required fundamental research of the phenomena. This includes the use of a vortex lattice method, three-dimensional CFD-computations and a numerical propeller optimisation method to derive the forces and their derivatives of the MAV and propeller for performance and stability-related optimisation studies. The design method leads to a simple, stable and robust flying wing MAV-platform that has the agility of a fighter airplane. A prototype, the UGMAV25, was constructed and flight tests were performed. The capabilities of the MAV were tested in a series of successful flight manoeuvres. The UGMAV15, a MAV with a span of 15cm, is also developed to test flight-qualities and endurance at this small scale. With the current battery technology, a flight-time of at least one hour is expected.

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Wang, Q., J. Chen, G. Fu, D. Duan, and H. Zhao. "A methodology for optimisation design and analysis of stratosphere airship." Aeronautical Journal 113, no. 1146 (August 2009): 533–40. http://dx.doi.org/10.1017/s0001924000003183.

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Abstract This paper presents a methodology for studying the feasibility of stratosphere airship for high altitude long endurance missions and arriving at the baseline specifications of conventional configuration of stratosphere airship, given the performance and operational requirements. Based on this methodology, the AODAP platform (Airship Optimisation Design and Analysis Platform) was developed. Some innovative concepts used in AODAP that are different from previous methods and codes are presented. The shape optimisation of airship was introduced into the design process, and several optimum objectives can be selected including minimum drag, minimum weight and composite objective based on MDO (Multidisciplinary Design Optimisation). The methodology was validated for other design concepts previously developed for similar missions and also was compared to a low altitude vehicle. The baseline specifications of stratosphere airships designed for various shapes using this methodology are presented. The results of sensitivity analyses for a specified airship are discussed, and the sensitivity of airship length with some critical parameters including area density of envelope fabric, area density of solar cell, efficiency of solar cell and efficiency of fuel cell for the specified shape is also provided.

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40

Wu, Yizhou, Wentao Li, Jiacheng Yang, Siqin Wu, Heyuan You, Shenyan Wu, Xin Wu, and Xuxu Guo. "Simulation-Based Optimisation for Urban Environmental Noise Coupled with Auditory and Visual Subjective Evaluation." Complexity 2020 (August 7, 2020): 1–21. http://dx.doi.org/10.1155/2020/6958367.

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Environmental noise has a major negative impact, causing interference for people to communicate, rest, sleep, and general annoyance. In order to control urban environmental noise, simulation-based optimisation for urban environmental noise is conducted. On the basis of the current acoustic environment of Zhaohui Campus of Zhejiang University of Technology, three optimisation plans that include noise barrier optimisation, greenbelt optimisation, and a combination optimisation of noise barrier and greenbelt are proposed. These scenarios are simulated using NoiseSystem software to obtain their ability to reduce noise and determine auditory perception by using different control measures. To determine the visual perception of the optimisation plan, 100 people of different age groups were randomly selected, and each person scored the noise barrier and the greenbelt in the simulated scenarios. Results of the comprehensive evaluation of auditory and visual perception show that noise barriers can provide better auditory feelings, but greenbelts can provide a better auditory and visual subjective experience. Therefore, in addition to the application of noise control measures, their visual design must be fully considered. Moreover, the visual perception of plants is stronger than that of others.

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41

ONEL, Alexandru-Iulian, and Teodor-Viorel CHELARU. "Weights and sizing assessment in the context of small launcher design." INCAS BULLETIN 12, no. 3 (September 1, 2020): 137–50. http://dx.doi.org/10.13111/2066-8201.2020.12.3.11.

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The paper presents mathematical models that can be used to quickly define preliminary key aspects regarding the sizing and weight characteristics of studied small launchers. The tool developed based on the proposed mathematical models can be used for standalone liquid propelled stage design or it can be integrated in an iterative multidisciplinary optimisation design scheme (MDO) for a preliminary small launcher design, able to insert the desired payload into a predefined orbit.

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42

Berchiolli, Guarda, Walsh, and Pesyridis. "Turbocharger Axial Turbines for High Transient Response, Part 2: Genetic Algorithm Development for Axial Turbine Optimisation." Applied Sciences 9, no. 13 (June 30, 2019): 2679. http://dx.doi.org/10.3390/app9132679.

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In a previous paper [1], a preliminary design methodology was proposed for the design of an axial turbine, replacing a conventional radial turbine used in automotive turbochargers, to achieve improved transient response, due to the intrinsically lower moment of inertia. In this second part of the work, the focus is on the optimisation of this preliminary design to improve on the axial turbine efficiency using a genetic algorithm in order to make the axial turbine a more viable proposition for turbocharger turbine application. The implementation of multidisciplinary design optimisation is essential to the aerodynamic shape optimisation of turbocharger turbines, as changes in blade geometry lead to variations in both structural and aerodynamics performance. Due to the necessity to have multiple design objectives and a significant number of variables, genetic algorithms seem to offer significant advantages. However, large generation sizes and simulation run times could result in extensively long periods of time for the optimisation to be completed. This paper proposes a dimensioning of a multi-objective genetic algorithm, to improve on a preliminary blade design in a reasonable amount of time. The results achieved a significant improvement on safety factor of both blades whilst increasing the overall efficiency by 2.55%. This was achieved by testing a total of 399 configurations in just over 4 h using a cluster network, which equated to 2.73 days using a single computer.

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Butler, R., M. Lillico, J. R. Banerjee, M. H. Patel, and G. T. S. Done. "Sequential use of conceptual MDO and panel sizing methods for aircraft wing design." Aeronautical Journal 103, no. 1026 (August 1999): 389–97. http://dx.doi.org/10.1017/s0001924000064617.

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Abstract The optimisation results for composite and metallic versions of a regional aircraft wing are compared using the multidisciplinary optimisation (MDO) program CALFUNOPT. The program has been developed for the conceptual design stage and models the wing using just 11 beam elements. The wing has been optimised for three combinations of the following constraint cases: static strength; aeroelastic roll efficiency (represented by limiting the twist of the wing for an aileron loading) and aeroelastic divergence. As expected, comparison shows that the composite wing designs are significantly lighter than the metallic ones, due to the well-known tailoring of the composite material. However, the simple model reveals some insight that may be useful to the designer, and which could be lost within a more detailed finite element approach. The upper-skin compression panels produced by the conceptual MDO program, for both versions of the wing, have then been optimised using the more detailed and accurate panel sizing tool VICONOPT, which takes buckling into account. Such optimisation increases the panel mass by 5-10% and also provides a suitable ratio of stiffener to skin area for use in the conceptual MDO model.

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., Mariani Rajin, Awang Bono ., and Ho Chong Mun . "Optimisation of Natural Ingredient Based Lipstick Formulation by Using Mixture Design." Journal of Applied Sciences 7, no. 15 (July 15, 2007): 2099–103. http://dx.doi.org/10.3923/jas.2007.2099.2103.

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45

Jayaraman, B. "Design, optimisation and performance analysis of orifice pulse tube cryogenic refrigerators." Indian Journal of Science and Technology 3, no. 4 (April 20, 2010): 425–36. http://dx.doi.org/10.17485/ijst/2010/v3i4.17.

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46

Ibsen, Claus H., and David Toal. "InDEStruct: engineering advanced heat transfer systems." Open Access Government 36, no. 1 (October 12, 2022): 234–37. http://dx.doi.org/10.56367/oag-036-10199.

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InDEStruct: engineering advanced heat transfer systems Within the University of Southampton, Atul Singh – also referred to as ESR1 – works on his PhD within a Horizon 2020 Programme project InDEStruct. His scope within this project is to work on optimisation and design methods to improve decision-making in heat exchanger conceptual design, in other words, a more effective design taking into account multidisciplinary aspects of such designs and reducing the experimental cost required to make decisions on new heat exchanger topologies. Open Access Government interviews members of the team of the InDEStruct project, a Horizon 2020 project which works toward inter-disciplinary design approaches for advanced heat transfer systems.

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47

Fritzsche, Matthias, Konstantin Kittel, Alexander Blankenburg, and Sándor Vajna. "Multidisciplinary design optimisation of a recurve bow based on applications of the autogenetic design theory and distributed computing." Enterprise Information Systems 6, no. 3 (August 2012): 329–43. http://dx.doi.org/10.1080/17517575.2011.650216.

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48

Прокопова, Софья Михайловна, Светлана Геннадьевна Кравчук, and Николай Петрович Гарин. "ARCTIC URBAN REALM: OPTIMISATION AND DIGITALISATION." Академический вестник УралНИИпроект РААСН, no. 3(50) (September 30, 2021): 40–44. http://dx.doi.org/10.25628/uniip.2021.50.3.007.

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Становясь самым высокоурбанизированным регионом в мире, Крайний Север России ставит вопрос о совмещении агрессивного климата и комфорта человека. Исследование истории арктической урбанизации показало, что видение северных городов будущего в проектах советских архитекторов заключалось в создании изолированного микроклимата. Благосостояние человека требует не только нейтрализации агрессивных природных воздействий, но и поддержки психоэмоционального состояния через оптимизацию городской среды. Данное исследование поднимает вопрос о том, как архитектура и дизайн через междисциплинарный подход могут участвовать в формировании комфортного и «умного» - поддерживаемого современными технологиями - города в Арктике. While becoming the most urbanized region in the world, the High North brought up an issue of combining harsh conditions and human wellbeing. The research of the Arctic urban planning / architecture history has shown that these projects were mainly aimed to design an isolated microclimate. A complete wellbeing in terms of living in extreme climate conditions demands not only neutralization of harsh natural settings, but also empowering psychological state and comfort level. This research investigates a question of design and architecture’s contribution to forming comfortable and smart (empowered by modern technologies) city in the Arctic through multidisciplinary approach.

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McDonald, Robert A., Brian J. German, T. Takahashi, C. Bil, W. Anemaat, A. Chaput, R. Vos, and N. Harrison. "Future aircraft concepts and design methods." Aeronautical Journal 126, no. 1295 (December 6, 2021): 92–124. http://dx.doi.org/10.1017/aer.2021.110.

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AbstractWith an annual growth in travel demand of about 5% globally, managing the environmental impact is a challenge. In 2019, the International Civil Aviation Organisation (ICAO) issued emission reduction targets, including well-to-wake greenhouse gas (GHG) emissions reduced at least 50% from 2005 levels by 2050. This discusses several technologies from an aircraft design perspective that can contribute to achieving these targets. One thing is certain: aircraft will look different in the future. The Transonic Truss-Braced Wing and Flying V configurations are promising significant efficiency improvements over conventional configurations. Electric propulsion, in various architectures, is becoming a feasible option for general aviation and commuter aircraft. It will be a growing field of aviation with zero-emissions flight and opportunities for special missions. Lastly, this paper discusses methods and design processes that include all relevant disciplines to ensure that the aircraft is optimised as a complete system. While empirical methods are essential for initial design, Multidisciplinary Design Optimisation (MDO) incorporates models and simulations integrated in an optimisation environment to capture critical trade-offs. Concurrent design places domain experts in one site to facilitate collaboration, interaction, and joint decision-making, and to ensure all disciplines are equally considered. It is supported by a Collaborative Design Facility (CDF), an information technology facility with connected hardware and software tools for design analysis.

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M. Sail, Asmawati, Wan Aida Wan Mustapha, Salma Mohamad Yusop, Mohamad Yusof Maskat, and Ahmad Fuad Shamsuddin. "Optimisation of Cinnamaldehyde-in-water Nanoemulsion Formulation using Central Composite Rotatable Design." Sains Malaysiana 47, no. 9 (September 30, 2018): 1999–2008. http://dx.doi.org/10.17576/jsm-2018-4709-07.

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