Thesis (M.S.)--University of Missouri-Columbia, 2008. / The entire dissertation/thesis text is included in the research.pdf file; the official abstract appears in the short.pdf file (which also appears in the research.pdf); a non-technical general description, or public abstract, appears in the public.pdf file. Title from title screen of research.pdf file (viewed on August 17, 2009) Includes bibliographical references.

Thesis (M.App.Sc.) - Carleton University, 2007. / Includes bibliographical references (p. 151-156). Also available in electronic format on the Internet.

The development of a flexible, high-fidelity, generic simulation of transatmospheric and interplanetary motion is described. The simulation incorporates aerodynamic and gravitational force modelling implemented in a Cartesian reference co-ordinate set. Propagation of the motion of a vehicle is carried out in a "working" reference frame whose origin is determined by the current gravitational sphere of influence. A semi-analytic model of planetary motion propagates the motion of the nine planets and six major moons, allowing simulation at any point within the solar system. Expansion and improvement of the model is facilitated through the vector formulation of the problem. The use and applicability of the method of matched asymptotic expansions is examined as a means of producing high quality trajectory predictions quickly and easily. Ballistic launch and entry trajectories are considered incorporating a velocity dependent model for the aerodynamic drag coefficient. Using the derived relations direct launch is considered as a low-cost means of transporting acceleration insensitive payloads to a space station in low Earth orbit. In addition, it is shown that the high quality trajectory predictions may be obtained using a simple spreadsheet package. Analytic modelling is also used as the basis of a highly robust, computationally efficient, controller design for autonomous aerocapture in the context of the lunar return problem. The validity of this approach to lunar return is examined and found to be of considerable potential in both its robustness and the potential improvements in payload mass-fraction available through the substantial fuel savings over direct return to Earth or propulsive return to a space station. The study shows that, using the derived control, the aerocapture manoeuvre can be successfully performed with existing material and technological capabilities.

I am describing a launch strategy of a anti-hairloss product on the Czech market. The launch took place in October 2008 by L'Oreal. It's brand La Roche-Posay has very strict policy, doesn't use any ATL activities. It is a medical brand and is available only in pharmacies.

Cette thèse concerne l'étude et la réduction de la consommation de puissance durant le test par scan des circuits digitaux. Afin de détecter les défauts de délai de transition, les deux principales structures sont utilisés dans la pratique: Launch-Off-Shift (LOS) et launch-Off-Capture (LOC). L'ensemble des travaux réalises montre que le test LOS est plus efficace que le test LOC en terme de couverture de fautes de transition et la longueur de test. Toutefois, le test LOS nécessite une puissance plus élevée lors du launch-to-capture (LTC) du cycle, notamment en terme de consommation de puissance de pic. Ainsi, nous proposons une nouvelle approche de génération de vecteurs de test LOS basée sur la consommation. La technique proposée est capable de réduire et d'évaluer la puissance de pic de test se rapprochant le plus possible de la puissance fonctionnelle. Les avantages qui en résultent permettent de résoudre le problème lié à la perte de rendement et de s'abstenir du test se produisant lorsque la puissance de test est trop faible par rapport à la puissance fonctionnelle. / This thesis relates to study and reduction of power consumption during at-speed scan delay testing for digital circuits. To detect transition delay faults, two main testing schemes are used in practice: Launch-Off-Shift (LOS) and Launch-Off-Capture (LOC). In this work, we prove that LOS testing is more efficient than LOC testing in terms of transition fault coverage (TFC) and test length. However, LOS presents higher power during the launch-to-capture (LTC) cycle, especially in terms of peak power. For this purpose, we propose a novel power-aware test pattern generation technique for LOS testing. The proposed approach is able to reduce and map the test peak power as close as possible to the functional power. The important feature of this framework is that, in additional to solving the yield loss problem, it also avoids test escape that may occur when test power is too much reduced compared to functional power.

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The commercial space transportation industry is growing with the technology that creates more capable spacecrafts to access space. However, there are still some academic discussions related to the delimitation of the outer space and the definition of space objects that could interfere with the regulation of this growing space activity. Because these discussions are not predicted to be solved soon, the developing space policies must attempt to clarify these issues between the parts avoiding the retard in the development of the industry. Moreover, these policies have to promote public-private partnerships and the emersion of private entrepreneurs for a faster development of a safe, reliable, and affordable commercial space transportation.

The marketplace in the 21st century is intense and highly competitive. Customers have a great variety of products and services to choose from, therefor gaining competitive advantage is crucial for a company´s survival. Companies cannot rely on previous product success, they have to be innovative in order to meet the ever-changing customer needs and wants. New product launch is a critical and challenging phase for every company, which is proven by the high failure rates. There are many barriers that can hinder and determine a new product launch process. This study focuses on Business-to-Business, small and medium sized companies within the Swedish steel and metal industry with the purpose to investigate what barriers occur when launching new industrial products. The study also aims to answer the question on what actions can be taken in order to overcome these barriers. This is a qualitative and comparative study based on a theoretical framework combined with empirical findings gathered from five in-depth interviews. By analyzing and comparing the findings throughout this study, the authors can conclude that there are many barriers that can occur and affect a product launch process negatively. The main barriers identified were lack of knowledge, effort, planning as well as targeting and competition. The study also resulted in practical suggestions and actions that can be taken in order to overcome these barriers and ease the launch process.   Key words: New product launch, Barriers in launch processes, B2B, Swedish companies, SME`s, Marketing

Trajectory optimization is an important part of launch vehicle design and operation. With the high costs of launching payload into orbit, every pound that can be saved increases affordability. One way to save weight in launch vehicle design and operation is by optimizing the ascent trajectory. Launch vehicle trajectory optimization is a field that has been studied since the 1950’s. Originally, analytic solutions were sought because computers were slow and inefficient. With the advent of computers, however, different algorithms were developed for the purpose of trajectory optimization. Computer resources were still limited, and as such the algorithms were limited to local optimization methods, which can get stuck in specific regions of the design space. Local methods for trajectory optimization have been well studied and developed. Computer technology continues to advance, and in recent years global optimization has become available for application to a wide variety of problems, including trajectory optimization. The aim of this thesis is to create a methodology that applies global optimization to the trajectory optimization problem. Using information from a global search, the optimization design space can be reduced and a much smaller design space can be analyzed using already existing local methods. This allows for areas of interest in the design space to be identified and further studied and helps overcome the fact that many local methods can get stuck in local optima. The design space included in trajectory optimization is also considered in this thesis. The typical optimization variables are initial conditions and flight control variables. For direct optimization methods, the trajectory phase structure is currently chosen a priori. Including trajectory phase structure variables in the optimization process can yield better solutions. The methodology and phase structure optimization is demonstrated using an earth-to-orbit trajectory of a Delta IV Medium launch vehicle. Different methods of performing the global search and reducing the design space are compared. Local optimization is performed using the industry standard trajectory optimization tool POST. Finally, methods for varying the trajectory phase structure are presented and the results are compared.