The application of multi-objective robust design methods in ship design

When designing large complex vessels, the evaluation of a particular design can be both complicated and time consuming. Designers often resort to the use of concept design models enabling both a reduction in complexity and time for evaluation. Various optimisation methods are then typically used to explore the design space facilitating the selection of optimum or near optimum designs. It is now possible to incorporate considerations of seakeeping, stability and costs at the earliest stage in the ship design process. However, to ensure that reliable results are obtained, the models used are generally complex and computationally expensive. Methods have been developed which avoid the necessity to carry out an exhaustive search of the complete design space. One such method is described which is concerned with the application of the theory of Design Of Experiments (DOE) enabling the design space to be efficiently explored. The objective of the DOE stage is to produce response surfaces which can then be used by an optimisation module to search the design space. It is assumed that the concept exploration tool whilst being a simplification of the design problem, is still sufficiently complicated to enable reliable evaluations of a particular design concept. The response surface is used as a representation of the concept exploration tool, and by it's nature can be used to rapidly evaluate a design concept hence reducing concept exploration time. While the methodology has a wide applicability in ship design and production, it is illustrated by its application to the design of a catamaran with respect to seakeeping. The paper presents results exploring the design space for the catamaran. A concept is selected which is robust with respect to the Relative Bow Motion (RBM), the heave, pitch and roll at any particular waveheading. The design space is defined by six controllable design parameters; hull length, breadth to draught ratio, distance between demihull centres, coefficient of waterplane, longitudinal centre of floatation, longitudinal centre of buoyancy, and by one noise parameter, the waveheading. A Pareto-optimal set of solutions is obtained using RBM, heave, pitch and roll as criteria. The designer can then select from this set the design which most closely satisfies their requirements. Typical solutions are shown to yield average reductions of over 25% in the objective functions when compared to earlier results obtained using conventional optimisation methods

Efficient design optimization of complex electromagnetic systems using parametric macromodeling techniques

We propose a new parametric macromodeling technique for complex electromagnetic systems described by scattering parameters, which are parameterized by multiple design variables such as layout or substrate feature. The proposed technique is based on an efficient and reliable combination of rational identification, a procedure to find scaling and frequency shifting system coefficients, and positive interpolation schemes. Parametric macromodels can be used for efficient and accurate design space exploration and optimization. A design optimization example for a complex electromagnetic system is used to validate the proposed parametric macromodeling technique in a practical design process flow

Interpolation-based parameterized model order reduction of delayed systems

Three-dimensional electromagnetic methods are fundamental tools for the analysis and design of high-speed systems. These methods often generate large systems of equations, and model order reduction (MOR) methods are used to reduce such a high complexity. When the geometric dimensions become electrically large or signal waveform rise times decrease, time delays must be included in the modeling. Design space optimization and exploration are usually performed during a typical design process that consequently requires repeated simulations for different design parameter values. Efficient performing of these design activities calls for parameterized model order reduction (PMOR) methods, which are able to reduce large systems of equations with respect to frequency and other design parameters of the circuit, such as layout or substrate features. We propose a novel PMOR method for neutral delayed differential systems, which is based on an efficient and reliable combination of univariate model order reduction methods, a procedure to find scaling and frequency shifting coefficients and positive interpolation schemes. The proposed scaling and frequency shifting coefficients enhance and improve the modeling capability of standard positive interpolation schemes and allow accurate modeling of highly dynamic systems with a limited amount of initial univariate models in the design space. The proposed method is able to provide parameterized reduced order models passive by construction over the design space of interest. Pertinent numerical examples validate the proposed PMOR approach

Shape Memory Alloy Deployable Device For CubeSat Satellite

The purpose of this project was to design and create a release mechanism for a cubesat satellite with the use of shape memory alloys. The goal of the project was to design and create a lightweight, reliable, and simple release mechanism to deploy stowed solar arrays attached to the exterior of a Cubesat satellite. The design and creation of this mechanism is intended to further USM’s goal of creating and launching a Cubesat satellite into low orbit to expand the university into space exploration. The Cubesat project was created by the California Polytechnic State University and Stanford University’s Space Systems Development Lab in hopes of creating a platform that made space exploration more accessible to universities and their students. Other Cubesat groups have used various other release mechanism designs, some of which used shape memory alloys, with varying degrees of success. This project is USM’s first foray into the Cubesat field, with other related projects taking place at the time of this project. The challenge of this project was designing a simple and reliable linear actuator using SMA’s that meet NASA’s Cubesat dimension standards. The end product is a simple, effective, and reliable release mechanism capable of being reset for ground testing

The development of a cislunar space infrastructure

The primary objective of this Advanced Mission Design Program is to define the general characteristics and phased evolution of a near-Earth space infrastructure. The envisioned foundation includes a permanently manned, self-sustaining base on the lunar surface, a space station at the Libration Point between earth and the moon (L1), and a transportation system that anchors these elements to the Low Earth Orbit (LEO) station. The implementation of this conceptual design was carried out with the idea that the infrastructure is an important step in a larger plan to expand man's capabilities in space science and technology. Such expansion depends on low cost, reliable, and frequent access to space for those who wish to use the multiple benefits of this environment. The presence of a cislunar space infrastructure would greatly facilitate the staging of future planetary missions, as well as the full exploration of the lunar potential for science and industry. The rationale for, and a proposed detailed scenario in support of, the cislunar space infrastructure are discussed

A Low Power, Rad-Hard, ECL Standard Cell Library

Space exploration for life both inside and outside of our solar system demand the design and fabrication of robust, reliable electronics that can take measurements, process data, and sustain necessary operations. However, the presence of high radiation and the cold temperature of space poses a challenge to most designers. This thesis presents the design of a radiation-hardened, cold capable emitter coupled logic standard cell library with the intention of being used for space applications. The cells are designed and fabricated in a 90nm silicon germanium BiCMOS process. First, a review of emitter coupled logic is presented. Then, the design methodology for the standard cells are presented. Next, the results of several fabricated standard cells are discussed and analyzed. Finally, the work is concluded and future work is discussed

Surrogate Modelling with Sequential Design for Expensive Simulation Applications

The computational demands of virtual experiments for modern product development processes can get out of control due to fine resolution and detail incorporation in simulation packages. These demands for appropriate approximation strategies and reliable selection of evaluations to keep the amount of required evaluations were limited, without compromising on quality and requirements specified upfront. Surrogate models provide an appealing data‐driven strategy to accomplish these goals for applications including design space exploration, optimization, visualization or sensitivity analysis. Extended with sequential design, satisfactory solutions can be identified quickly, greatly motivating the adoption of this technology into the design process

Geometry parametrization and aerodynamic characteristics of axisymmetric afterbodies

A key aspect of the preliminary design process for a new generation combat aircraft is the prediction of afterbody aerodynamic drag. Current prediction methods for preliminary design are constrained in terms of number of independent geometric degrees of freedom that can be studied due to the classic circular arc or conical afterbody geometry parametrization. In addition, the amount of data available for the construction of the reliable performance correlations is too sparse. This paper presents a methodology for the generation of aerodynamic performance maps for transonic axisymmetric afterbody and exhaust systems. It uses a novel parametric geometry definition along with a compressible flow solver to conduct an extensive design space exploration. The proposed geometry parametrization is based on the Class Shape Transformation method and it enables the assessment of the aerodynamic performance of a wider range of afterbodies at the expense of one additional geometric degree of freedom. Relative to the conventional approach, this enables the exploration of a wider design space and the construction of more complete aerodynamic performance maps. This research quantifies the impact of a number of geometric degrees of freedom on the aerodynamic performance of transonic afterbody and exhaust systems at different operating conditions

NASA Exploration Launch Projects Systems Engineering Approach for Astronaut Missions to the Moon, Mars, and Beyond

The U.S. Vision for Space Exploration directs NASA to design and develop a new generation of safe, reliable, and cost-effective transportation systems to hlfill the Nation s strategic goals and objectives. These launch vehicles will provide the capability for astronauts to conduct scientific exploration that yields new knowledge from the unique vantage point of space. American leadership in opening new fi-ontiers will improve the quality of life on Earth for generations to come. The Exploration Launch Projects office is responsible for delivering the Crew Launch Vehicle (CLV) that will loft the Crew Exploration Vehicle (CEV) into low-Earth orbit (LEO) early next decade, and for the heavy lift Cargo Launch Vehicle (CaLV) that will deliver the Lunar Surface Access Module (LSAM) to LEO for astronaut return trips to the Moon by 2020 in preparation for the eventual first human footprint on Mars. Crew travel to the International Space Station will be made available as soon possible after the Space Shuttle retires in 2010