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Journal articles on the topic 'Aerospace systems design'

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Author: Grafiati

Published: 10 December 2022

Last updated: 28 January 2023

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1

Valenti, Michael. "Re-Engineering Aerospace Design." Mechanical Engineering 120, no. 01 (January 1, 1998): 70–72. http://dx.doi.org/10.1115/1.1998-jan-5.

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This article reviews that by integrating its CAD/CAM tools, Boeing’s Space Systems Unit hopes to enhance the quality of its products as it reduces both design- and manufacturing-cycle times. Sharper market competition led management to re-emphasize the practice and couple it with integrated CAD/CAM systems to provide a more supportive environment for concurrent engineering, thereby assuring the customer that cost, schedule, and quality goals would be met. This concept, called integrated product development (IPD), was launched in 1991. Boeing’s intention is to use the IPD strategy to reduce design-cycle time and manufacturing-cycle time as well as recurring costs. To support IPD, the Boeing designers developed electronic change control (ECC), an online system that enables engineers, technicians, manufacturers, and logisticians throughout the company to track and control engineering changes on a network of minicomputers, workstations, and desktops. Among the Unigraphics-based tools Boeing uses in IPD is the electronic development fixture (EDF), a three-dimensional digital model. EDF enables its users to electronically investigate fit, form, function, and interference detection.

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Sira-Ramirez, H., P. Lischinsky-Arenas, and O. Llanes-Santiago. "Dynamic compensator design in nonlinear aerospace systems." IEEE Transactions on Aerospace and Electronic Systems 29, no. 2 (April 1993): 364–79. http://dx.doi.org/10.1109/7.210075.

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3

Livne, Eli. "Special Issue: Multidisciplinary Design Optimization of Aerospace Systems." Journal of Aircraft 36, no. 1 (January 1999): 9–10. http://dx.doi.org/10.2514/2.2439.

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4

Monell, Donald W., and William M. Piland. "Aerospace systems design in NASA's collaborative engineering environment." Acta Astronautica 47, no. 2-9 (July 2000): 255–64. http://dx.doi.org/10.1016/s0094-5765(00)00065-5.

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5

Wang, Yi Wen, Ming Na Ding, Wen Juan Zheng, Zhen Chen, and Jing Shu Hu. "Design of Typical Aerospace Materials Database System." Materials Science Forum 800-801 (July 2014): 644–48. http://dx.doi.org/10.4028/www.scientific.net/msf.800-801.644.

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Due to the rapid development of aerospace industry, the amount of cutting data is increasing. Establishing cutting database for aerospace industry is necessary. Therefore, this article designs the typical aerospace material database system. According to project requirements analysis and the conceptual design, nine function blocks is set. They are data management, experiment management, optimization management, cutting tool design, cutting tool simulation, knowledge base, aerospace solutions, systems management, and help. And the article describes content and processes of every function block.

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6

Shi, Renhe, Teng Long, Nianhui Ye, Yufei Wu, Zhao Wei, and Zhenyu Liu. "Metamodel-based multidisciplinary design optimization methods for aerospace system." Astrodynamics 5, no. 3 (September 2021): 185–215. http://dx.doi.org/10.1007/s42064-021-0109-x.

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AbstractThe design of complex aerospace systems is a multidisciplinary design optimization (MDO) problem involving the interaction of multiple disciplines. However, because of the necessity of evaluating expensive black-box simulations, the enormous computational cost of solving MDO problems in aerospace systems has also become a problem in practice. To resolve this, metamodel-based design optimization techniques have been applied to MDO. With these methods, system models can be rapidly predicted using approximate metamodels to improve the optimization efficiency. This paper presents an overall survey of metamodel-based MDO for aerospace systems. From the perspective of aerospace system design, this paper introduces the fundamental methodology and technology of metamodel-based MDO, including aerospace system MDO problem formulation, metamodeling techniques, state-of-the-art metamodel-based multidisciplinary optimization strategies, and expensive black-box constraint-handling mechanisms. Moreover, various aerospace system examples are presented to illustrate the application of metamodel-based MDOs to practical engineering. The conclusions derived from this work are summarized in the final section of the paper. The survey results are expected to serve as guide and reference for designers involved in metamodel-based MDO in the field of aerospace engineering.

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Gil, Paulo J. S., Pedro M. B. Rosa, and Ivo M. L. Ferreira. "Modern approaches in the design of complex aerospace systems." Journal of Aerospace Engineering, Sciences and Applications 2, no. 1 (January 1, 2010): 15–26. http://dx.doi.org/10.7446/jaesa.0201.02.

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Bindolino, G., S. Ricci, and P. Mantegazza. "Integrated Servostructural Optimization in the Design of Aerospace Systems." Journal of Aircraft 36, no. 1 (January 1999): 167–75. http://dx.doi.org/10.2514/2.2423.

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9

Gupta, K. K. "An Integrated Systems Approach for Design of Aerospace Structures." International Journal of Space Structures 3, no. 2 (June 1988): 118–29. http://dx.doi.org/10.1177/026635118800300205.

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This paper is primarily concerned with the analysis and design of structural systems relating to aeronautical and aerospace engineering. Some numerical formulations are presented that deal with the synthesis of these systems integrating such disciplines as structures, unsteady aero-dynamics and control engineering. A general-purpose finite element computer program developed for associated large-scale computations is also described in some detail. Finally, results of relevant numerical analyses pertaining to some representative aircraft and spacecraft, obtained by utilizing the program, are presented that testify to the efficacy of the currently developed solution procedures.

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Saleh, Joseph H., Daniel E. Hastings, and Dava J. Newman. "Flexibility in system design and implications for aerospace systems." Acta Astronautica 53, no. 12 (December 2003): 927–44. http://dx.doi.org/10.1016/s0094-5765(02)00241-2.

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11

Schy, A. A., and D. P. Giesy. "Multiobjective Insensitive Computer-Aided Design of Aerospace Control Systems." IFAC Proceedings Volumes 18, no. 2 (June 1985): 177–88. http://dx.doi.org/10.1016/s1474-6670(17)60930-3.

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Schy, A. A., and D. P. Giesy. "Multiobjective insensitive computer-aided design of aerospace control systems." Annual Review in Automatic Programming 13 (January 1985): 177–88. http://dx.doi.org/10.1016/0066-4138(85)90479-3.

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13

Aboelela, Magdy A. S., Mohamed F. Ahmed, and Hassen T. Dorrah. "Design of aerospace control systems using fractional PID controller." Journal of Advanced Research 3, no. 3 (July 2012): 225–32. http://dx.doi.org/10.1016/j.jare.2011.07.003.

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14

Subramanya, N., A. R. Satheesh Kumar, Vikas Yadav, and R. K. Venkatesh. "Manufacturing process planning in aerospace systems." IOP Conference Series: Materials Science and Engineering 1258, no. 1 (October 1, 2022): 012027. http://dx.doi.org/10.1088/1757-899x/1258/1/012027.

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Process planning is a task comprising a broad range of activities to design and develop an appropriate manufacturing process for producing a part. Interpretation of the part design, selection of manufacturing processes, definition of operations, operation sequences, machining datums, geometrical dimensions and tolerances are some common activities associated with the task. Manufacturing process planning can be defined as systematic determination of detailed methods by which work pieces or parts can be manufactured economically and competitively from raw material stage to final finished size. Geometrical features, dimensional sizes, tolerances, materials, and finishes, are analyzed evaluated to determine appropriate sequence of processing operations, which are based on specific, available resources viz machinery and manpower. Inputs to process planning are designing data, raw material data, resource data (machining data, tooling data, fixture data etc), quality requirement data, production type data etc. The output of a process planning is a process document which is an important document in production management. The paper mainly discusses about production planning and control of metallic manufacturing activities in an aerospace Research and Development (R&D) industry, main emphasis on manufacturing process planning. The general process planning methodology adopted in an aircraft industry is discussed. Elements and Functions of process planning, model of process planning, main mission of process planning, the interaction of processes and its process performance indices are discussed and presented. Importance of manufacturing process planning in an aerospace R&D industry is debated. Also, a case study of process planning adopted for manufacturing of a critical Aircraft system component is discussed.

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TAIFI, NOUHA, MARIANGELA LAZOI, ANGELO CORALLO, GIUSEPPINA PASSIANTE, and MARIANGELA LAZOI. "INTEGRATED SYSTEMS AND OUTSOURCING: PROCESS INNOVATION IN AEROSPACE PRODUCT DESIGN." International Journal of Innovation and Technology Management 09, no. 03 (August 2012): 1250019. http://dx.doi.org/10.1142/s0219877012500198.

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Organizations need to share and acquire new information to sustain competitive advantage in complex environment. They communicate through IT-based integrated systems to fasten communication and knowledge sharing for the creation of innovative products. Firms are, thus, extending their operations to integrate strategic knowledge from partners in the product development process. In this paper, we present a case study related to process innovation in an aerospace firm integrating its information systems with one of its partners to facilitate the design of the models of a complex product. We investigate on the strategy followed to integrate the information systems, the types of these latter, on their success factors and their impact on the product development. The case study provides important insights on the integration of information systems for product design outsourcing.

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Stringfellow, M. V., N. G. Leveson, and B. D. Owens. "Safety-Driven Design for Software-Intensive Aerospace and Automotive Systems." Proceedings of the IEEE 98, no. 4 (April 2010): 515–25. http://dx.doi.org/10.1109/jproc.2009.2039551.

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Troncoso, E., N. Lapeña-Rey, and M. Gonzalez. "Design tool for offgrid hydrogen refuelling systems for aerospace applications." Applied Energy 163 (February 2016): 476–87. http://dx.doi.org/10.1016/j.apenergy.2015.05.026.

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Federici, Fabio, Cecilia Tonelli, Mathieu Le Cam, Marcello Torchio, and David Larsen. "Design and validation of scalable PHM solutions for aerospace onboard systems." PHM Society European Conference 7, no. 1 (June 29, 2022): 126–35. http://dx.doi.org/10.36001/phme.2022.v7i1.3333.

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In recent years, Prognostic & Health Management (PHM) has become a topic of strong interest in the aerospace domain. Health assessment and remaining useful life estimation for on-board systems provide several advantages, mainly related to the increased analysis capabilities and the reduction of maintenance interventions (and, consequently, of operating costs). For this reason, it is of interest for the aerospace industry to identify and define efficient strategies both for the introduction of native PHM capabilities in new generation on-board systems and for the retrofit of existing ones. This paper proposes a strategy for the scalable deployment of PHM techniques for on-board systems, with particular focus on edge computing capabilities. Different reference scenarios (ranging from cloud-based processing to local-only processing) are presented, and an edge-focused PHM architecture is discussed in detail, with the relative challenges addressed. The design and validation of proposed edge-based solution is described, with specific reference to its support for an existing data analytics framework. The solution is then assessed against a reference aerospace use case involving a representative aircraft braking system, focusing on computational aspects to highlight the compatibility of the proposed deployment strategy with efficient on-board computations.

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19

Nilsson, D. "Taking flight in 3D [aerospace design]." Manufacturing Engineer 86, no. 6 (December 1, 2007): 24–26. http://dx.doi.org/10.1049/me:20070602.

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Gopinath, K., K. Raghavendra, M. K. Behera, E. V. Subba Rao, M. Umakanth, and S. Gopinath. "Product Design Aspects for Design of Accurate Mass Properties Measurement System for Aerospace Vehicles." Applied Mechanics and Materials 110-116 (October 2011): 4712–18. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.4712.

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Mass properties of aerospace vehicle viz Weight, Center of Gravity (Xcg, Ycg, Zcg) & Mass Moment of Inertia (Ixx, Iyy & Izz) are critical inertial parameters which are vital to meet the intended mission objectives. Accurate mass properties measurement is needed for fast maneuvering aerospace vehicles to meet the Control and Guidance requirements within the tolerable limits generated by the System Designer. Mass properties estimation is vital during the configuration design phase of an aerospace vehicle. Assumptions and Constraints during the configuration design, limits the accuracy of estimations making the mass properties measurement mandatory. The mass properties of the aerospace vehicle can be measured by numerous methods, but for achieving high accuracies within the tolerable limits, the measurement system should have advanced technologies and measurement methodologies. Based on the experience, mass properties measurement systems were designed using Load Cells and Cross-Flexural Pivots in two different systems (Weight and CG in System-1, MOI in System-2), which have limited accuracy and also involves tedious external measurements. Adopting Air-Bearing (T / H / Spherical shape) supported with accurate sensors using Inverted Torsion Pendulum method, Multiple Point Weighing method and a proper measurement methodology, enhances the accuracy of the measurement system. Usage of spherical bearing yields a better accurate system but has the difficulty in realization of the system indigenously, whereas use of T or H-shape bearing is a feasible solution for achieving the desired accurate mass properties specifications. This paper gives an insight into to the product design aspects to be considered for realization of accurate mass properties measurement system.

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Peng, Yuyang. "Forward Design Method of Avionics System Based on Communication." Mobile Information Systems 2021 (November 8, 2021): 1–6. http://dx.doi.org/10.1155/2021/5984066.

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With the rapid development of computer technology, electronic technology, and control technology, communication-based avionics systems can provide greater potential for the improvement of aircraft combat capabilities. Moreover, during the flight, passengers have an increasing demand for space communications. How to provide passengers with a communication-based aerospace electronic system that is indistinguishable from the ground during the flight is a problem that needs to be solved urgently. The research on the forward design method of this system has been highly valued by experts at home and abroad. This article is a communication-based forward design method for avionics systems. Based on the development of aerospace data communication technology, this article discusses the advantages of the application of the CCSDS (Consultative Committee for Space Data Systems) protocol in the design of aerospace electronic communication systems. This research designs the technical scheme of the entire aerospace communication electronic system and refers to the relevant CCSDS protocol to complete the design of the distributor’s fast transmission telemetry package and the distributor’s slow transmission telemetry package. This article introduces the two existing architectures of the integrated avionics system, compares and analyzes them, and then elaborates the integrated avionics system architecture based on trusted computing and the trust chain transfer mechanism. The experimental results show that the method designed in this paper uses the NBSP basic protocol in an aeronautical communication environment with a nesting depth of 2 s. When the data transmission delay is 2 s, the NBSP scheme is 0.9 and the NERON scheme is 0.4. This shows that the design method of this study is able to meet the requirements of the system and technical indicators.

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22

Mendenhall, M. R. "Corporate memory contribution to integrated design and analysis systems." Aeronautical Journal 110, no. 1106 (April 2006): 257–63. http://dx.doi.org/10.1017/s0001924000001238.

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Abstract The recent decline in the USA aerospace industry has resulted in fewer programs, fewer engineers, and a potential loss of capability for future technology development. As engineers retire or leave the industry, their corporate memory or retained knowledge must be preserved for future use. A process to capture their expert knowledge is described, and a framework which provides a means to retrieve and use this valuable technical information is shown. Four examples of integrated design and analysis systems for four diverse technologies and applications are discussed.

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23

Camberos, José A., and David J. Moorhouse. "Systems Engineering in Terms of Exergy." International Journal of Aerospace Engineering 2009 (2009): 1–7. http://dx.doi.org/10.1155/2009/735680.

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We address the design of a flight vehicle from the viewpoint of a system of systems and we discuss the integration of the individual technical disciplines. Then a conceptual fundamental methodology and tools required for the analysis, design, and optimization of aerospace vehicles in terms of the efficient use of on-board energy are discussed. This suggests changing the design paradigm to the optimization of a system of energy systems. We propose a foundation for system-level design with optimization based on minimum exergy destruction.

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TAIFI, NOUHA, MARIANGELA LAZOI, ANGELO CORALLO, GIUSEPPINA PASSIANTE, and MICHELE MONACO. "ERRATUM: INTEGRATED SYSTEMS AND OUTSOURCING: PROCESS INNOVATION IN AEROSPACE PRODUCT DESIGN." International Journal of Innovation and Technology Management 09, no. 04 (August 2012): 1292002. http://dx.doi.org/10.1142/s0219877012920022.

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Moarref, Miad, and Luis Rodrigues. "Observer design for linear models of multi-rate asynchronous aerospace systems." Aerospace Systems 3, no. 2 (May 4, 2020): 127–37. http://dx.doi.org/10.1007/s42401-020-00049-8.

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Sevillian, Dujuan B. "Human Systems Integration." International Journal of Aviation Technology, Engineering and Management 1, no. 2 (July 2011): 17–45. http://dx.doi.org/10.4018/ijatem.2011070102.

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Effective Human Factors Engineering (HFE) has provided the aerospace industry with design considerations that promote aviation safety in the development of complex aircraft systems, as well as the operators and maintainers that utilize those systems. HFE is an integral aspect within the systems engineering process. Measuring the effectiveness of Human Systems Integration (HSI) in the research & development stage is critical for the design of new and modified systems. This paper focuses on the importance of design and integration in the product development stages as well as understanding the impact on the user population.

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Kakosimos, Panagiotis E., Minos E. Beniakar, and Antonios G. Kladas. "Induction Motor Design for Ad Hoc Actuation Systems." Materials Science Forum 792 (August 2014): 362–66. http://dx.doi.org/10.4028/www.scientific.net/msf.792.362.

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In this paper the application of Taguchis methodology to the design of actuators for aerospace applications is presented. The preliminary design employing time-stepping finite element analysis is carried out in order to determine actuators basic dimensional and operating characteristics. Configuration considered is subsequently optimized regarding the mean torque and torque ripple through the application of a specific optimization procedure employing Taguchis methodology. Resulting IM configuration has been validated through manufactured prototype illustrating the effectiveness of the proposed optimization algorithm.

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Steinfeldt, Bradley A., and Robert D. Braun. "Using Dynamical Systems Concepts in Multidisciplinary Design." AIAA Journal 52, no. 6 (June 2014): 1265–79. http://dx.doi.org/10.2514/1.j010001.

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Mills, Andrew Robert, and Visakan Kadirkamanathan. "Sensing for aerospace combustor health monitoring." Aircraft Engineering and Aerospace Technology 92, no. 1 (January 6, 2020): 37–46. http://dx.doi.org/10.1108/aeat-11-2018-0283.

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Purpose This paper proposes new methods of fault detection for fuel systems in order to improve system availability. Novel fault systems are required for environmentally friendly lean burn combustion, but can carry high risk failure modes particularly through their control valves. The purpose of the developed technology is the rapid detection of these failure modes, such as valve sticking or impending sticking, and therefore to reduce this risk. However, sensing valve state is challenging due to hot environmental temperatures, which results in a low reliability for conventional position sensing. Design/methodology/approach Starting with the business needs elicited from stakeholders, a quality functional deployment process is performed to derive sensing system requirements. The process acknowledges the difference between test-bed and in-service aerospace needs through weightings on requirements and maps these customer requirements to systems performance metrics. The design of the system must therefore optimise the sensor suite, on- and off-board signal processing and acquisition strategy. Findings Against this systems engineering process, two sensing strategies are outlined which illustrate the span of solutions, from conventional gas path sensing with advanced signal processing to novel non-invasive sensing concepts. While conventional sensing may be feasible within a test cell, the constraints of aerospace in-service operation may necessitate more novel alternatives. Acoustic emission (detecting very high frequency surface vibration waves) sensing technology is evaluated to provide a non-invasive, remote and high temperature tolerant solution. Through this comparison, the considerations for the end-to-end system design are highlighted to be critical to sensor deployment success in-service. Practical implications The paper provides insight into different means of addressing the important problem of monitoring faults in combustor systems in gas turbines. By casting of the complex design problem within a systems engineering framework, the outline of a toolset for solution evaluation is provided. Originality/value The paper provides three areas of significant contributions: a diversity of methods to diagnosing fuel system malfunctions by measuring changes fuel flow distributions, through novel means, and the combustor exit temperature profiles (cause and effect); the use of analytical methods to support the selection (types and quantities) and placement of sensors to ensure adequate state awareness while minimising their impact on the engine system cost and weight; and an end-to-end data processing approach to provide optimised information for the engine maintainers allowing informed decision-making.

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Kutin, Andrey A., and Mikhail Turkin. "Modelling and Design of Closed-Loop Manufacturing Systems." Applied Mechanics and Materials 378 (August 2013): 367–74. http://dx.doi.org/10.4028/www.scientific.net/amm.378.367.

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This paper introduces an analytical method for evaluating the performance of closed loop manufacturing systems with unreliable machines and finite buffers. The method involves transforming an arbitrary loop into one without thresholds and then evaluating the transformed loop using a new set of decomposition equations. It is more accurate than existing methods and is effective for a wider range of cases. The convergence reliability, and speed of the method are also discussed. In addition, observations are made on the behavior of closed loop production systems under various conditions. Finally, the method is used in a case study to design a flexible manufacturing system for production of aerospace parts.

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Citarella, Roberto, Luigi Federico, and Mattia Barbarino. "Aeroacustic and Vibroacoustic Advancement in Aerospace and Automotive Systems." Applied Sciences 10, no. 11 (June 1, 2020): 3853. http://dx.doi.org/10.3390/app10113853.

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This Special Issue highlights the latest enhancements in the abatement of noise and vibrations of aerospace and automotive systems. The reduction of acoustic emissions and the improvement of cabin interior comfort are on the path of all major transportation industries, having a direct impact on customer satisfaction and, consequently, the commercial success of new products. Topics covered in this Special Issue deal with computational, instrumentation and data analysis of noise and vibrations of fixed wing aircrafts, satellites, spacecrafts, automotives and trains, ranging from aerodynamically generated noise to engine noise, sound absorption, cabin acoustic treatments, duct acoustics and vibroacoustic properties of materials. The focus of this Special Issue is also related to industrial aspects, e.g.,: numerical and experimental studies have been performed for an existing and commercialized engine to enable design improvements aimed at reducing noise and vibrations; moreover, an optimization is provided for the design of low vibroacoustic volute centrifugal compressors and fans whose fluids should be strictly kept in the system without any leakage. Existing procedures and algorithms useful to reach the abovementioned objectives in the most efficient way are illustrated in the collected papers.

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32

Chudoba, B., and W. Heinze. "Evolution of generic flight vehicle design synthesis." Aeronautical Journal 114, no. 1159 (September 2010): 549–67. http://dx.doi.org/10.1017/s0001924000004036.

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AbstractWhen defining a new product like an aircraft, space access vehicle or space mission, the Advanced Projects Group evaluates the available design space and compares it with the design space required to accomplish the specified mission. As with any product development process, the general life-cycle characteristics are established first during the conceptual design (CD) phase, clearly before a design proposal can be released to the follow-on design phases such as preliminary design (PD), detail design (DD), flight test (FT), and finally operation and disposal. As a rule of thumb, it can be assumed that around 80% of the flight vehicle configuration and mission tandem are determined during the CD phase alone, which is the key phase where the initial brainstorming has to take place. Clearly, it is the responsibility of the CD team to simulate the entire life-cycle of the project from ‘cradle to grave’ where the focus is on correctness rather accuracy in order to identify the design space and offer an overall proof of design convergence. Currently, the important primary aerospace vehicle and mission design decisions at CD level are still made using extremely simple analysis and heuristics. A reason for this scenario is the difficulty in synthesising the range of individual design disciplines for both, classical and novel aerospace vehicle conceptual designs, in more than anad hocfashion. Although the CD segment is seen as the most important step in the product development phase due to its pre-defining function, it is the least well understood part of the entire product evolution process due to its level of abstraction. This paper presents the roadmap towards the next generation of aerospace life-cycle synthesis systems, a software and management process capable to immediately calculate cost and time implications while simultaneously linking design, manufacturing, testing, and operation. A historical review of how design has been accomplished until today is presented. The design approaches are categorised and the characteristics of today’s state-of-the-art design synthesis systems are discussed. A specification for the new class of intelligent generic design synthesis systems is presented capable of satisfying the demands imposed by the new breed of high-performance aircraft, space access vehicles, space missions, and others. Finally, the development status of the next generation aerospace vehicle design synthesis (AVDS-PrADO) simulation-based acquisition environment is presented.

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Astridge, D. G. "Helicopter Transmissions—design for Safety and Reliability." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 203, no. 2 (July 1989): 123–38. http://dx.doi.org/10.1243/pime_proc_1989_203_063_01.

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Recent improvements in design and component technologies are reviewed against a background of accident data analysis, resulting in grounds for confidence in higher safety levels in future rotorcraft transmission designs. Recommendations are made concerning the realization of significant safety and reliability benefits afforded by effective health and usage monitoring systems. The results of this study are applicable to all new aerospace gearbox applications including helicopters, tilt-rotor aircraft, advanced propeller engines and accessory drive systems.

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Sun, Xiaoqian, Volker Gollnick, Yongchang Li, and Eike Stumpf. "Intelligent Multicriteria Decision Support System for Systems Design." Journal of Aircraft 51, no. 1 (January 2014): 216–25. http://dx.doi.org/10.2514/1.c032296.

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35

Rowell, Lawrence F., Robert D. Braun, John R. Olds, and Resit Unal. "Multidisciplinary Conceptual Design Optimization of Space Transportation Systems." Journal of Aircraft 36, no. 1 (January 1999): 218–26. http://dx.doi.org/10.2514/2.2428.

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Jensen, Hector A., and Abdon E. Sepulveda. "Optimal Design of Uncertain Systems Under Stochastic Excitation." AIAA Journal 38, no. 11 (November 2000): 2133–41. http://dx.doi.org/10.2514/2.876.

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Grandhi, Ramana V., Iftikhar Haq, and N. S. Khot. "Enhanced robustness in integrated structural/control systems design." AIAA Journal 29, no. 7 (July 1991): 1168–73. http://dx.doi.org/10.2514/3.10719.

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Gavel, Hampus, Johan Olvander, and Petter Krus. "Optimal Conceptual Design of Aircraft Fuel Transfer Systems." Journal of Aircraft 43, no. 5 (September 2006): 1334–40. http://dx.doi.org/10.2514/1.19548.

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Crespo, Luis G., Daniel P. Giesy, and Sean P. Kenny. "Robustness Analysis and Robust Design of Uncertain Systems." AIAA Journal 46, no. 2 (February 2008): 388–96. http://dx.doi.org/10.2514/1.28683.

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Hosman, R., S. Advani, and N. Haeck. "Integrated design of flight simulator motion cueing systems." Aeronautical Journal 109, no. 1091 (January 2005): 1–12. http://dx.doi.org/10.1017/s000192400000049x.

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Abstract An advanced design process applicable to the specification of flight simulator cueing systems is presented in this paper. This process is based on the analysis of the pilot-vehicle control loop by using a pilot model incorporating both visual and vestibular feedback, and the aircraft dynamics. After substituting the model for the simulated aircraft, the analysis tools are used to adjust the washout filter parameters with the goal of restoring pilot control behaviour. This process allows the specification of the motion cueing algorithm. Then, based on flight files representative of the operational flight envelope, the required motion system space is determined. The motion-base geometry is established based on practical limitations, as well as criteria for the stability of the platform with respect to singular conditions. With this process the characteristics of the aircraft, the tasks to be simulated, and the missions themselves are taken into account in defining the simulator motion cueing system.

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Allison, James T., and Daniel R. Herber. "Special Section on Multidisciplinary Design Optimization: Multidisciplinary Design Optimization of Dynamic Engineering Systems." AIAA Journal 52, no. 4 (April 2014): 691–710. http://dx.doi.org/10.2514/1.j052182.

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Mohammad Zadeh, Parviz, and Mohadeseh Sadat Shirazi. "Multidisciplinary design optimization architecture to concurrent design of satellite systems." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 10 (September 14, 2016): 1898–916. http://dx.doi.org/10.1177/0954410016665412.

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The design of space systems is a complex and multidisciplinary process with multiple conflicting objectives, large number of design variables, and constraints that limits application of the existing multidisciplinary design optimization architectures to this class of design problems. This paper presents an enhanced multidisciplinary design optimization architecture to concurrent holistic design optimization of a satellite system. The proposed multidisciplinary design optimization architecture extends concepts of multidiscipline feasible and bi-level integrated system synthesis into a unified architecture using metamodels. The proposed architecture was evaluated and compared with the existing multidisciplinary design optimization architectures that include all-at-once, bi-level integrated system synthesis, and multidisciplinary design optimization using a remote sensing small satellite in low earth orbit. The satellite design optimization problem deals with the minimization of the total mass of the satellite, involving disciplines of mission analysis, payload, structures, attitude determination and control, communication, command and data handling, power and thermal. The computational performance and accuracy of the proposed architecture were compared with multidisciplinary design optimization benchmark problems. Then the proposed architecture is successfully applied to the satellite system design problem. The results obtained show that metamodel-based bi-level integrated system synthesis-multidisciplinary design optimization architecture presented in this paper provides an effective way of solving large-scale design problems.

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Panferov, Alexander I., Sergey A. Brodsky, and Alexander V. Nebylov. "Intelligent Control Systems Design for Flexible Aerospace Vehicles: Theoretical and Software Tools." IFAC Proceedings Volumes 42, no. 19 (2009): 373–78. http://dx.doi.org/10.3182/20090921-3-tr-3005.00066.

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Parrish, J., M. Rais-Rohani, and M. Janus. "Reduced-Order Techniques for Sensitivity Analysis and Design Optimization of Aerospace Systems." AIAA Journal 53, no. 12 (December 2015): 3567–76. http://dx.doi.org/10.2514/1.j053559.

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Manolopoulos, Charalampos D., Matteo F. Iacchetti, Alexander C. Smith, Kevin Berger, Mark Husband, and Paul Miller. "Stator Design and Performance of Superconducting Motors for Aerospace Electric Propulsion Systems." IEEE Transactions on Applied Superconductivity 28, no. 4 (June 2018): 1–5. http://dx.doi.org/10.1109/tasc.2018.2814742.

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Selcon, S. J., R. M. Taylor, and E. Koritsas. "Workload or Situational Awareness?: TLX vs. SART for Aerospace Systems Design Evaluation." Proceedings of the Human Factors Society Annual Meeting 35, no. 2 (September 1991): 62–66. http://dx.doi.org/10.1518/107118191786755706.

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Mennicken, M., D. Schoenweitz, M. Schnoes, and R. Schnell. "Fan design assessment for BLI propulsion systems." CEAS Aeronautical Journal 13, no. 1 (October 4, 2021): 3–19. http://dx.doi.org/10.1007/s13272-021-00532-8.

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AbstractCivil aviation is aiming at fuel efficient aircraft concepts. Propulsion systems using boundary layer ingestion (BLI) are promising to reach this goal. The focus of this study is on the DLR UHBR fan stage of a tube and wing aircraft with rear-integrated engines. In this integration scenario the propulsion system and especially the fan stage receives distorted inflow in steady-state flight conditions. The distortion pattern and distortion intensity are dependent on the operating conditions. Consequently, the interaction of the fan and the distortion changes over the flight envelope. The first part of the paper aims at gaining knowledge of the BLI fan performance in the operating points end of field, approach, cruise (CR) and top of climb (TOC) using high-fidelity, unsteady RANS approaches. The analysis includes fan map performance metrics and a deeper insight into the flow field at CR and TOC. The preliminary design of a fan stage requires fast turn-around times, which are not fulfilled by high-fidelity approaches. Therefore, a fast, throughflow-based methodology is developed, which enables aerodynamicists to design distortion-tolerant fans. The main characteristics of the methodology is outlined in the second part. Consequently, the methodology is taken advantage of to investigate parameter sensitivities in terms of tip speed, blade thickness, solidity, the annulus geometry and a non-axisymmetric stator. This study suggests that distortion-tolerant fans should be designed at higher tip speeds than conventional design experience recommends to limit the local operating point excursion.

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Mennicken, M., D. Schoenweitz, M. Schnoes, and R. Schnell. "Fan design assessment for BLI propulsion systems." CEAS Aeronautical Journal 13, no. 1 (October 4, 2021): 3–19. http://dx.doi.org/10.1007/s13272-021-00532-8.

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AbstractCivil aviation is aiming at fuel efficient aircraft concepts. Propulsion systems using boundary layer ingestion (BLI) are promising to reach this goal. The focus of this study is on the DLR UHBR fan stage of a tube and wing aircraft with rear-integrated engines. In this integration scenario the propulsion system and especially the fan stage receives distorted inflow in steady-state flight conditions. The distortion pattern and distortion intensity are dependent on the operating conditions. Consequently, the interaction of the fan and the distortion changes over the flight envelope. The first part of the paper aims at gaining knowledge of the BLI fan performance in the operating points end of field, approach, cruise (CR) and top of climb (TOC) using high-fidelity, unsteady RANS approaches. The analysis includes fan map performance metrics and a deeper insight into the flow field at CR and TOC. The preliminary design of a fan stage requires fast turn-around times, which are not fulfilled by high-fidelity approaches. Therefore, a fast, throughflow-based methodology is developed, which enables aerodynamicists to design distortion-tolerant fans. The main characteristics of the methodology is outlined in the second part. Consequently, the methodology is taken advantage of to investigate parameter sensitivities in terms of tip speed, blade thickness, solidity, the annulus geometry and a non-axisymmetric stator. This study suggests that distortion-tolerant fans should be designed at higher tip speeds than conventional design experience recommends to limit the local operating point excursion.

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HOSSAIN, Aynul. "Conceptual Design of a Low - Cost Linear Actuator for Variable Span Wing Application." INCAS BULLETIN 13, no. 1 (March 5, 2021): 69–76. http://dx.doi.org/10.13111/2066-8201.2021.13.1.7.

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Aerospace actuators can be found throughout modern commercial and experimental aircraft, as well as in military and space exploration. The aerospace industry is not only growing, but also rapidly changing and the demand for aerospace actuators is permanently increasing. Linear actuator is able to push, pull, and hold objects in a way that our bodies cannot. Additionally, electrically powered technology provides more sophisticated control options. Linear actuator drive many different functions that are essential to safe and efficient aircraft operation. Manufacturers and hobbyists alike are always on the hunt for new ways to automate functions while keeping development costs low. Providing cost-effective linear solutions for aerospace application is one of the biggest challenge. This research will provide a cost-effective actuator conceptual design for variable span morphing wing UAV. The cost-effective design will be presented along with the application-based selection of linear actuators for morphing wing UAV.

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Ludvigsen, Jennifer, Mustapha Mouloua, and Peter A. Hancock. "Human Factors/Ergonomics Contributions to Aerospace Systems, 1980–2012." Ergonomics in Design: The Quarterly of Human Factors Applications 23, no. 4 (October 2015): 20–22. http://dx.doi.org/10.1177/1064804615572627.

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We examined aerospace systems research trends in papers published in the Proceedings of the Human Factors and Ergonomics Society Annual Meeting from 1980 to 2012. We categorized articles based on authors’ affiliation type, content area, population, sample size, apparatus, and nature and specification of outcome dependent variables. Our results, available at http://erg.sagepub.com/supplemental , revealed an increase in research interests related to cognition and pilot–cockpit systems interface design. Our findings are intended to guide students, educators, and researchers by providing an analysis of these trends and a searchable online database.

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