scholarly journals Preliminary Design and Development of a Mechanical Ventilator Using Industrial Automation Components for Rapid Deployment During the COVID-19 Pandemic

Cureus ◽  
2021 ◽  
Author(s):  
Benjamin DeBoer ◽  
Ahmad Barari ◽  
Mika Nonoyama ◽  
Adam Dubrowski ◽  
Marco Zaccagnini ◽  
...  
Keyword(s):  
Preliminary Design ◽  
Mechanical Ventilator ◽  
Design And Development ◽  
Industrial Automation ◽  
Rapid Deployment

Rotorcraft virtual engineering; supporting life-cycle engineering through design and development, test and certification and operations

2018 ◽  
Vol 122 (1255) ◽  
pp. 1475-1495 ◽  
Author(s):  
G. D. Padfield
Keyword(s):  
Life Cycle ◽  
Preliminary Design ◽  
Design Development ◽  
Design And Development ◽  
Design Decisions ◽  
Life Cycle Engineering ◽  
Virtual Engineering ◽  
Model Fidelity ◽  
Virtual Prototypes ◽  
Industry Needs

ABSTRACTThe rotorcraft industry needs Virtual Engineering first to ensure decisions made early in the life-cycle, at the requirements capture and preliminary design phases for example, are reliably informed. Later, in design, development and qualification, Virtual Prototypes can become the centre of attention for critical reviews and, ultimately, certification itself. A significant challenge is to ensure that model fidelity is good enough, not only for supporting design decisions but also in establishing requirements based on sufficiently mature technologies. This international conference, Rotorcraft virtual engineering; supporting life-cycle engineering through design and development, test and certification and operations and co-sponsored by the RAeS/AHS/A3F/DGLR/AIDAA addressed these themes and this paper reviews and assesses the value of the various contributions.

Multidisciplinary design and optimization of expendable launch vehicle for microsatellite missions

2021 ◽  
Vol ahead-of-print (ahead-of-print) ◽  
Author(s):  
Qasim Zeeshan ◽  
Amer Farhan Rafique ◽  
Ali Kamran ◽  
Muhammad Ishaq Khan ◽  
Abdul Waheed
Keyword(s):  
Research Effort ◽  
Launch Vehicle ◽  
Low Earth Orbit ◽  
Multidisciplinary Design ◽  
Preliminary Design ◽  
Design And Development ◽  
Content Type ◽  
Design And Optimization ◽  
Design Variables ◽  
Development Costs

Purpose The capability to predict and evaluate various configurations’ performance during the conceptual design phase using multidisciplinary design analysis and optimization can significantly increase the preliminary design process’s efficiency and reduce design and development costs. This research paper aims to perform multidisciplinary design and optimization for an expendable microsatellite launch vehicle (MSLV) comprising three solid-propellant stages, capable of delivering micro-payloads in the low earth orbit. The methodology’s primary purpose is to increase the conceptual and preliminary design process’s efficiency by reducing both the design and development costs. Design/methodology/approach Multidiscipline feasible architecture is applied for the multidisciplinary design and optimization of an expendable MSLV at the conceptual level to accommodate interdisciplinary interactions during the optimization process. The multidisciplinary design and optimization framework developed and implemented in this research effort encompasses coupled analysis disciplines of vehicle geometry, mass calculations, aerodynamics, propulsion and trajectory. Nineteen design variables were selected to optimize expendable MSLV to launch a 100 kg satellite at an altitude of 600 km in the low earth orbit. Modern heuristic optimization methods such as genetic algorithm (GA), particle swarm optimization (PSO) and SA are applied and compared to obtain the optimal configurations. The initial population is created by passing the upper and lower bounds of design variables to the optimizer. The optimizer then searches for the best possible combination of design variables to obtain the objective function while satisfying the constraints. Findings All of the applied heuristic methods were able to optimize the design problem. Optimized design variables from these methods lie within the lower and upper bounds. This research successfully achieves the desired altitude and final injection velocity while satisfying all the constraints. In this research effort, multiple runs of heuristic algorithms reduce the fundamental stochastic error. Research limitations/implications The use of multiple heuristics optimization methods such as GA, PSO and SA in the conceptual design phase owing to the exclusivity of their search approach provides a unique opportunity for exploration of the feasible design space and helps in obtaining alternative configurations capable of meeting the mission objectives, which is not possible when using any of the single optimization algorithm. Practical implications The optimized configurations can be further used as baseline configurations in the microsatellite launch missions’ conceptual and preliminary design phases. Originality/value Satellite launch vehicle design and optimization is a complex multidisciplinary problem, and it is dealt with effectively in the multidisciplinary design and optimization domain. It integrates several interlinked disciplines and gives the optimum result that satisfies these disciplines’ requirements. This research effort provides the multidisciplinary design and optimization-based simulation framework to predict and evaluate various expendable satellite launch vehicle configurations’ performance. This framework significantly increases the conceptual and preliminary design process’s efficiency by reducing design and development costs.

Sign in / Sign up

Export Citation Format

Share Document