A Case Study on School-Oriented Management Successfully Launched ABSTRACT The present study is primarily intended to probe into a case school¡XMin-chyuan Elementary School of Kaohsiung regarding its process and experiences via compilation and analysis of documents in promoting its school-oriented management so as to look into what efforts Min-chyuan Elementary School of Kaohsiung has made toward the school-oriented management. Through focus interview, triangulation, we look into the key school personnel regarding how they view the issues and what they have in mind. The study is backed by a small-scale questionnaire survey to analyze the performance and satisfaction level, added with the personal observation and comments by the researcher (the founding Principal of the subject School) as appropriate, in reciprocation and reflection. In the present study, the connotation to define the school-oriented management includes such six key issues, i.e., the Principal¡¦s philosophy in leadership, formulation and enforcement of school vision, forging and deepening the school culture, concept and characteristics of campus landscaping, shape and application of school classes which are open for use, school-oriented curricula in planning and enforcement. I. The Principal¡¦s philosophy in leadership: Including the Principal¡¦s thoughts in leadership philosophy, what the Principal has acted in leadership, co-sharing of hands-on examples and reciprocation of school faculty toward the Principal in the wake of efforts of leadership. II. Formulation and enforcement of school vision: Based on the school vision and backgrounds of the school philosophy, it will forge the bold vision through hands-on actions and through school faculty who will point out their view points and reciprocation toward the school vision. III. Forging and deepening the school culture: Through elaborately written stories, it will combine the cultural efforts and sentiment of Min-chyuan Elementary School of Kaohsiung. For instance, a flock of ducks are visiting the newly founded campus to create the topics in common, to let the school grow and flourish along with us all. The significance of education will be merged into the hands-on experiences accumulated in school construction. The little ant¡¦s legend and others will bring the school faculty and students firmly together into strong sense of honors. IV. Concept and characteristics of campus landscaping: The concept and blueprints of campus planning, co-sharing of hands-on examples and feedback of the fruits. V. Shape and application of school classes which are open for use: The analysis of the school classes, the shapes and post-use status, the co-sharing of the examples, relevant issues of the classes and methodology to solution. VI. School-oriented curricula in planning and enforcement: The evolution of the school-oriented curricula, co-sharing of examples, reciprocation feedback and viewpoints toward school-oriented curricular. The present study yields the precious finding that in the school-oriented management, the Principal plays the core role, holding the open-minded and human-cored leadership. In turn, the Principal receives tremendous recognition from entire teams and faculty members. The School will take the school culture as the core of the vision to formulate the ¡§culture-based campus, education-based communities¡¨. Such vision and blueprints are matched with hands-on and concrete practice which form the tremendous momentum of continual development of the school to forge a promising and upbeat dream. Through toughing stories one after another, the school will shape up warm and sweet campus culture which is profoundly embedded into children through the characteristics of their behaviors. Under the breakthrough philosophy engineered by the Principal, the school is not a school alone and a classroom is not a classroom alone. With the elaborately designed spaces, the campus speaks. The space is in brisk dialogue. Thanks to the unique and sophisticated thoughts, Min-chyuan Elementary School of Kaohsiung impresses all and receives the Architectural and Landscaping Award for the Greater Kaohsiung Region¡Xthe first school ever awarded such tremendous honor. Through the efforts for compilation and co-sharing from the researcher, i.e., the founding principal of Min-chyuan Elementary School of Kaohsiung, both the tangible campus planning and intangible philosophy of spatial design profoundly impress all as the very target to probe into. In a nutshell, the school-oriented management efforts launched by Min-chyuan Elementary School of Kaohsiung are indeed unique breakthrough. The hands-on experiences so accumulated are precious lessons as worthwhile reference to other elementary schools.

This thesis determined the feasibility of developing a 16-inch, gun-launched anti-satellite weapon. The general performance capability of rocket-and scramjet-boosted, gun-launched vehicles is examined with regards to propelling a miniature homing vehicle to a satellite intercept altitude. Rocket and scramjet boost vehicle performance is modeled and optimum trajectories are determined. A low gun elevation at launch and a pop-up manuever are required to maximize the scramjet boost vehicle acceleration potential. The rocket boost vehicle is capable of intercepting a low altitude satellite without a pop-up manuever from a gun elevation of 45 degrees. Both boost methods provide apogees consistent with the intercept of known Soviet Electronic Intelligence Ocean Reconnaissance satellites, EORSAT, and Radar Ocean Reconnaissance satellites, RORSAT.

ITC/USA 2009 Conference Proceedings / The Forty-Fifth Annual International Telemetering Conference and Technical Exhibition / October 26-29, 2009 / Riviera Hotel & Convention Center, Las Vegas, Nevada / The US Army Research Laboratory currently uses a variety of ballistic diagnostic systems for gathering aerodynamic information pertaining to gun launched munitions. Sensors are a vital component of each of these diagnostic systems. Since multiple sensors are commonly used, they are often configured into a sensor suite or inertial measurement unit (IMU). In order to gather information on smaller diameter projectiles, a small diameter IMU was designed using commercial-off-the-shelf (COTS) sensors and components. This IMU was first designed with a 21.6mm diameter and then later reintegrated into a 17.5mm diameter unit. The IMU provides up to ten sensor data channels which can be used to make in-flight projectile motion measurements. These measurements are then used in the determination of the projectile's aerodynamics. It has been successfully flight tested on a variety of projectiles. It has been used in conjunction with an on-board recorder (OBR) to take measurements on 40mm and 25mm projectiles. It has also been used in a telemetry based system on-board a flare stabilized 25mm projectile. This paper covers the design of the IMU and gives examples of various sensor data.

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<p> A proposal is made to extend the present capabilities of gun-launched rocket vehicles to include attitude control during flight. The problems involved are stated and design criteria for possible sensors are listed. A review of presently available sensing devices is made and rejection of unsuitable instruments is based on fundamentals of their design and operation. </p> <p> A report is made upon the sensors which most adequately fulfil the harsh environmental requirements of gun-launch. These sensors are infrared-horizon sensors and a tuning fork vibratory gyroscope. A preliminary design is given for the tuning fork gyroscope a well as a summary of fundamental design considerations. </p> / Thesis / Master of Engineering (ME)

La motivation qui a initié le projet de recherche ANR « Démonstrateur Gun Launched Micro Air Vehicle » est le besoin d’avoir un engin portatif qui permettrait d’obtenir rapidement des images d’une zone d’intérêt située à quelques centaines de mètres, avec la possibilité de pouvoir observer l’intérieur des bâtiments à travers leurs fenêtres ou en allant les explorer directement. Pour répondre à ce besoin, l’Institut franco-allemand de recherche de St Louis a eu l’idée de lancer un minidrone hélicoptère avec un canon. Le GLMAV, sous la forme d’un projectile, est lancé à partir d‘un tube portable à une distance de 500 m et une altitude de 100 m, où il pourra commencer à transmettre des images de la zone à observer. L’utilisation d’un système hybride projectile/minidrone a deux principaux avantages : cela permet d’augmenter l’autonomie du drone, et les premières images de la zone d’intérêt sont obtenues très rapidement. Au cours de cette thèse, nous nous sommes intéressés à la phase de transition, passer d’un projectile à un mini hélicoptère. Un modèle aérodynamique détaillé du GLMAV a été obtenu sur toute son enveloppe de vol. En prenant en compte les difficultés rencontrées lors de la phase de transition (perturbations des capteurs dues à l’accélération de 2500g au lancement, conditions initiales variables), nous avons développé une stratégie de commande, et une loi de commande en vitesse basée sur la technique du backstepping. Cette stratégie de commande a été validée en simulation. La loi de commande en orientation a été validée sur le prototype du GLMAV. Des travaux sur le flux optique, pour obtenir les vitesses latérales, ont été commencés. / The motivation that initiated the ANR research project "Démonstrateur Gun Launched Micro Air Vehicle" is the need to have a portable system which would permi tto quickly obtain images of an zone of interest placed at some hundred of meters, with the possibility to observe inside buildings either by their windows or by going inside them.To answer this need, the French-German Research Institute of St Louis got the idea o fusing a gun launched rotorcraft-MAV. The GLMAV, in its projectile form, is launched from a portable launching tube to a distance of 500m and a height of 100m, where it will collect and transmit visual information from the scene. The use of a projectile/rotorcraft-MAV hybrid system has two main advantages : it allows extending the MAV range,and the first images of the interest zone are obtained very quickly. During this PhD, we studied the transition phase, the passage from a projectile to a rotorcraft-MAV. A detailed aerodynamic model of the GLMAV has been obtained over his whole flight envelope. Taking into account the difficulties encountered during the transition phase (perturbation of the sensors caused by the 2500g acceleration at the launch, varying initial conditions),we developed a control strategy, and a velocity control law based on the backstepping methodology. This control strategy has been validated in simulation. The attitude control law has been validated on the GLMAV prototype. Studies on optical flow, to obtain the lateral velocities of the GLMAV, have been started.

The main objective of this thesis is to introduce the reader to the problematics of air-launch and to a custom design solution applying this concept. The specifics of this method of bringing a payload into orbit are described and explained. Overview of projects which use aircraft to launch spacecraft is included. Determination of primary parameters of a launch vehicle designed to carry a payload of a specified mass is conducted. The required flight performance has been estimated, a computational model has been developed in software MATLAB, and a multidisciplinary optimization of the design parameters has been performed using a genetic algorithm optimization method. Parameters of the designed air-launched rocket are compared with those of a ground-launched rocket. According to the specific criteria, the Airbus A310-300 aircraft was selected as the most suitable transport aircraft to be used for launching the designed launch vehicle. The last part of the thesis is devoted to the proposal of necessary modifications and estimation of the flight performance.

In the present thesis, the objective was to find the maximum amount of payload mass that can be put into a 500 km polar orbit by a 1400 kg air-launched multi-stage rocket launched from a fighter jet platform. To fulfill the objective an algorithm incorporating several modules was developed. The modules performed calculations based on theoretical models and literature values to arrive at optimal design variables. From the design the maximum payload mass was able to be derived and it was concluded that a three-stage launch vehicle was able to deliver a 22.0 kg payload to the desired orbit. / I den här avhandlingen var syftet att hitta den maximala mängden nyttolastmassa som kan transporteras av en 1400 kg flerstegsraket uppskjuten från luften till en 500 km polär bana. För att uppfylla målet utvecklades en algoritm med flera moduler. Modulerna utförde beräkningar baserade på teoretiska modeller och litteraturvärden för att komma fram till optimala designvariabler. Från konstruktionen kunde den maximala nyttolastmassan härledas och det konstaterades att en trestegsraket kunde leverera en nyttolast på 22.0 kg till den önskade omloppsbanan.

In the present thesis, the objective was to find the maximum amount of payload mass that can be put into a 500 km polar orbit by a 1400 kg air-launched multi-stage rocket launched from a fighter jet platform. To fulfill the objective an algorithm incorporating several modules was developed. The modules performed calculations based on theoretical models and literature values to arrive at optimal design variables. From the design the maximum payload mass was able to be derived and it was concluded that a three-stage launch vehicle was able to deliver a 22.0 kg payload to the desired orbit. / I den här avhandlingen var syftet att hitta den maximala mängden nyttolastmassa som kan transporteras av en 1400 kg flerstegsraket uppskjuten från luften till en 500 km polär bana. För att uppfylla målet utvecklades en algoritm med flera moduler. Modulerna utförde beräkningar baserade på teoretiska modeller och litteraturvärden för att komma fram till optimala designvariabler. Från konstruktionen kunde den maximala nyttolastmassan härledas och det konstaterades att en trestegsraket kunde leverera en nyttolast på 22.0 kg till den önskade omloppsbanan.

The aim of this diploma thesis was the design of three possible variants, how to span the wide and deep valley with a bridge. After an evaluation, situation of the highway on the only wide load-bearing structure which is constituted by a box girder with transverse cantilevers supported by prefabricated bar braces, was chosen as an optimal solving. The load- bearing structure made of post- tensioned concrete is going to be incrementally launched and be supported by one-column pillars along an axis of the motorway. The work is composed of a detailed design of this preferred variant, which is processed according to the ultimate and serviceability limit state including the construction stage analysis of the bridge by the construction technology by an incremental launching method.