The master thesis named "Launch marketing strategy of Becherovka Lemond" analyses the launch marketing campaign. The thesis is divided into two parts -- theoretical and practical. Theoretical part deals with characterization of marketing mix and brand management. Practical part includes analysis of the market of alcoholic beverages in Czech Republic and consumers trends and analysis of up to now marketing strategy of the firm. Properly it deals with analysis and evaluation of marketing strategy while launching new product. The thesis also contains marketing consumer research. In the end there is the whole evaluation of the campaign with some recommendations for future progress.

International Telemetering Conference Proceedings / October 22-25, 2001 / Riviera Hotel and Convention Center, Las Vegas, Nevada / For every space mission, there are challenges with the launch site/field operations process that are addressed too late in the development cycle. This potentially causes schedule delays, cost overruns, and adds risk to the mission success. This paper will discuss how a single interface, representing the payload at the launch site in all phases of development, will mitigate risk, and minimize or even alleviate potential problems later on. Experience has shown that a single interface between the project and the launch site allows for issues to be worked in a timely manner and bridges the gap between two diverse cultures.

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Context. With the evolvement of cloud computing in recent years many companies have stated providing various services using it. Desktop as a Service, DaaS is one of services in the cloud computing in which the backend of Virtual Desktop Infrastructure, VDI is hosted by a cloud service provider. Although in SaaS, Software as a Service Web applications are used, all kinds of applications can be used in DaaS. There are many companies which provide VDI for private cloud and they are VMware Horizon, XenDesktops by Citrix, OpenStack VDI solution and etc. Objectives. In this thesis two VDI solutions are analyzed based on the virtual desktop launch time and the performance of the desktop in various test cases. The VDI solutions considered are VMware Horizon view and OpenStack VDI. Methods. The method for this research consists of two stages. The first stage was a qualitative analysis in which literature study and a survey was conducted. In the next stage, experiment was setup where different performance metrics were calculated when the virtual desktop was put under several test cases. Results. Results collected include the virtual desktops launch time in two scenarios and several performance metrics such as CPU usage, memory usage, average IO size, average latency, throughput, IOPS and queue length at the processor. Conclusions. Performance of Virtual desktop running on OpenStack VDI was better in most of the test cases. In the test scenario where disk was put under stress OpenStack VDI solution performance was better than VMware Horizon View. Even considering the launch time for virtual desktops, OpenStack VDI performed better compared to VMware Horizon View.

Thesis (Ph.D.)--Auburn University, 2007. / Abstract. Vita. Includes bibliographic references (ℓ. 169-175)

Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, Sept. 2004. / Thesis Advisor(s): I. Michael. Ross. Includes bibliographical references (p. 127-129). Also available online.

Thesis (M.S. in Space Systems Operations)--Naval Postgraduate School, September 2002. / Thesis advisor(s): Stephen A. Whitmore, Charles M. Racoosin. Includes bibliographical references (p. 93). Also available online.

ITC/USA 2006 Conference Proceedings / The Forty-Second Annual International Telemetering Conference and Technical Exhibition / October 23-26, 2006 / Town and Country Resort & Convention Center, San Diego, California / XX launch vehicle has been flying onboard video system which includes video cameras, data compression devices and channel switch device for the second Chinese spaceflight. The camera is a PAL analog camera that been sampled and compressed by compression device. The compressed digital video data is combined with telemetry data into the telemetry radio channel. Lighting is provided by sunlight, or a light has been equipped when sunlight is unavailable. IRIG-B timing is used to correlate the video with other vehicle telemetry. The video system’s influences to the vehicle flight have been decreased to minimum.

ITC/USA 2007 Conference Proceedings / The Forty-Third Annual International Telemetering Conference and Technical Exhibition / October 22-25, 2007 / Riviera Hotel & Convention Center, Las Vegas, Nevada / In pursuit to understanding the flight behavior and characterizing the stability of a flarestabilized projectile, an experiment was conducted to assess the robustness of an inertial sensor suite the size of a dime (17.5mm) by integrating to a telemetry system for recording. The system had to survive launch acceleration exceeding 25,000G’s. This is the beginning of an effort to reduce the size of telemetry systems and diagnostic devices for use in medium caliber munitions and smaller. A description of the telemetry system and subsystem will be presented along with the results.

ITC/USA 2006 Conference Proceedings / The Forty-Second Annual International Telemetering Conference and Technical Exhibition / October 23-26, 2006 / Town and Country Resort & Convention Center, San Diego, California / The National Aeronautics and Space Administration is developing a new launch vehicle to replace the Space Shuttle. The Crew Launch Vehicle (CLV) will be a combination of new design hardware and heritage Apollo and Space Shuttle hardware. The current CLV configuration is a 5 segment solid rocket booster First Stage and a new Upper Stage design with a modified Apollo era J-2 engine. The current schedule has an Ascent Development Test Flight (ADFT-0) with a First Stage and a dummy structurally identical, but without engine, Upper Stage. The ADFT-0 test results will determine if there will be multiple ADFT flights. There will be a minimum of two test flights with a full complement of flight hardware. After the completion of the test flights, the first manned flight to the International Space Station is scheduled for late 2014. To verify the CLV’s design margins a developmental flight instrumentation (DFI) system is needed. The DFI system will collect environmental and health data from the various CLV subsystems’ and either transmit it to the ground or store it onboard for later evaluation on the ground. The CLV consists of 4 major elements: the First Stage, the Upper Stage, the Upper Stage Engine and the integration of these elements together. It is anticipated that each of CLV’s elements will have some version of DFI. This paper will discuss a conceptual DFI design for each element and also of an integrated CLV DFI system.