Thesis (Mechanical Engineer and M.S. in Mechanical Engineering)--Naval Postgraduate School, June 2010. / Thesis Advisor(s): Brophy, Christopher ; Second Reader: Gannon, Anthony. "June 2010." Description based on title screen as viewed on July 13, 2010. Author(s) subject terms: Solid rocket propellant, two phase flow, erosive burning, alumina agglomeration, laser imaging Includes bibliographical references (p. 87). Also available in print.

Thesis (M.S.)--University of Missouri--Rolla, 2007. / Vita. The entire thesis text is included in file. Title from title screen of thesis/dissertation PDF file (viewed May 11, 2007) Includes bibliographical references (p. 115-119).

Resumo: As ações do responsável pela segurança de vôo, em lançamentos de foguetes, são fundamentais para minimizar riscos relacionados à vida, ao meio ambiente e a bens materiais. Nesse contexto está incluída a atividade de cálculo da posição do lançador, para compensação da influência do vento na trajetória de foguetes nãocontrolados. Atualmente, a execução dessa tarefa e a realimentação das informações referentes ao posicionamento do lançador não são realizadas de forma automática. Esse é um dos motivos pelos quais é necessário realizar o ajuste final do lançador, aproximadamente cinco a sete minutos antes do lançamento. No intervalo de tempo até o lançamento, o vento pode mudar de velocidade e direção, promovendo situação com potencial suficiente para causar desvio na trajetória do foguete, com conseqüente aumento da dispersão do seu ponto de impacto. O objetivo desse trabalho é propor uma arquitetura de sistema para automatizar o ajuste da posição em azimute e elevação de lançadores de foguetes de sondagem não-controlados. Os ensaios realizados com o protótipo de lançador mostraram que a proposta deste trabalho é capaz de realizar automaticamente o posicionamento de lançadores durante campanhas de lançamento, para compensar a influência do vento na trajetória do foguete, com o objetivo de diminuir a dispersão de impacto de foguetes não-controlados. / Abstract: The actions taken by the person responsible for flight safety in rocket launch are fundamental to minimize risks related to life, environment and material assets. This context includes the calculation of the launcher's position to compensate for wind influence on the unguided rocket trajectory. Currently, the accomplishment of such task and the feedback of data regarding launcher's positioning are not performed automatically. This is one of the reasons why it is necessary to make the final adjustment of the launcher approximately five to seven minutes before such launch. Within the time interval until the launch, wind speed and direction may change and give rise to a situation with enough potential to cause a deviation in the rocket's trajectory with the consequential increase in the dispersion of its point of impact. The purpose of this work is to propose a system architecture able to automate the adjustment of the position in azimuth and the elevation of unguided sounding rocket launchers. The tests made on the prototype launcher showed that the proposal of this work can automatically make the positioning of the launchers during launch campaigns to compensate for wind influence on the rocket's trajectory in order to reduce dispersion of impact of unguided rockets. / Orientador: Mauro Hugo Mathias / Coorientador: Francisco Carlos Parquet Bizarria / Banca: José Elias Tomazini / Banca: João Zangrandi Filho / Banca: Hilton Cleber Pietrobom / Banca: Viktor A. Pastoukhov / Doutor

Sounding rockets find applications in multiple fields of scientific research including meteorology, astronomy and microgravity. Indigenous sounding rocket technologies are absent on the African continent despite a potential market in the local aerospace industries. The UKZN Phoenix Sounding Rocket Programme was initiated to fill this void by developing inexpensive medium altitude sounding rocket modeling, design and manufacturing capacities. This dissertation describes the development of the Hybrid Rocket Performance Simulator (HYROPS) software tool and its application towards the structural design of the reusable, 10 km apogee capable Phoenix-1A hybrid sounding rocket, as part of the UKZN Phoenix programme. HYROPS is an integrated 6–Degree of Freedom (6-DOF) flight performance predictor for atmospheric and near-Earth spaceflight, geared towards single-staged and multi-staged hybrid sounding rockets. HYROPS is based on a generic kinematics and Newtonian dynamics core. Integrated with these are numerical methods for solving differential equations, Monte Carlo uncertainty modeling, genetic-algorithm driven design optimization, analytical vehicle structural modeling, a spherical, rotating geodetic model and a standard atmospheric model, forming a software framework for sounding rocket optimization and flight performance prediction. This framework was implemented within a graphical user interface, aiming for rapid input of model parameters, intuitive results visualization and efficient data handling. The HYROPS software was validated using flight data from various existing sounding rocket configurations and found satisfactory over a range of input conditions. An iterative process was employed in the aerostructural design of the 1 kg payload capable Phoenix-1A vehicle and CFD and FEA numerical techniques were used to verify its aerodynamic and thermo-structural performance. The design and integration of the Phoenix-1A‟s hybrid power-plant and onboard electromechanical systems for recovery parachute deployment and motor oxidizer flow control are also discussed. It was noted that use of HYROPS in the design loop led to improved materials selection and vehicle structural design processes. It was also found that a combination of suitable mathematical techniques, design know-how, human-interaction and numerical computational power are effective in overcoming the many coupled technical challenges present in the engineering of hybrid sounding rockets. / Thesis (M.Sc.)-University of KwaZulu-Natal, Durban, 2012.

International Telemetering Conference Proceedings / October 25-28, 1993 / Riviera Hotel and Convention Center, Las Vegas, Nevada / This paper presents a history of telemetry at White Sands Missile Range, New Mexico. White Sands Missile Range is located in the Tularosa Basin between the San Andres and the Organ Mountains on the west and the Sacramento Mountains on the east. Designation of more than one million acres of New Mexico range land as a testing areas established White Sands Proving Ground on July 9, 1945 as the Birthplace of Americas Missile and Space activity. On July 16, 1945 the first Atomic Bomb was exploded at Trinity Site. Project Hermes began in November of 1944 with a contract to General Electric by the Ordnance Department to develop a long range guided missile for the Army. Missile testing began in September of 1945 with the firing of Tiny Tim missiles. The capture of German V2 rockets led to testing and firing V2s concurrently with the Hermes. The first two-stage rocket consisted of a WAC Corporal mounted on the nose of a V2. Bumper # 5 set flight records of 5,150 miles an hour and an altitude of 244 miles on February 24, 1949. The paper includes: *Chronological highlights of telemetering events. *Discussion of telemetry systems and events that occurred at WSPG/WSMR from 1944 through 1990. *Telemetry systems and events from 1990 to the present. *Planned future telemetry systems and probable future systems.

Poon, Ho Shing. / Thesis (M.Phil.)--Chinese University of Hong Kong, 2009. / Includes bibliographical references (leaves 66-69). / Abstracts in English and Chinese. / ACKNOWLEDGEMENTS --- p.III / TABLE OF CONTENTS --- p.IV / TABLE OF FIGURES --- p.VI / LIST OF TABLES --- p.IX / Chapter CHAPTER 1: --- INTRODUCTION --- p.1 / Chapter 1.1 --- Intrinsic Problem of Conventional Aerodynamic Flying Devices --- p.1 / Chapter 1.2 --- Novel Ionic Propulsion Technology - Ionic Flyer --- p.2 / Chapter 1.3 --- Historical Development and Related Work of Ionic Flyer --- p.2 / Chapter 1.4 --- Existing Results in Our Group --- p.3 / Chapter 1.5 --- Objective and Current Achievements --- p.4 / Chapter 1.6 --- Organization of the remaining thesis --- p.5 / Chapter CHAPTER 2: --- FUNDAMENTAL KNOWLEDGE OF IONIC FLYERS --- p.6 / Chapter 2.1 --- Basic structure of Ionic Flyers --- p.6 / Chapter 2.2 --- Working Principle of Ionic Flyers --- p.7 / Chapter 2.3 --- Parametric models of the Ionic Flyers --- p.8 / Chapter 2.3.1 --- Electrical Current-Voltage Model --- p.8 / Chapter 2.3.2 --- Mechanical Lift-Force Model --- p.9 / Chapter CHAPTER 3: --- STRUCTURAL ANALYSIS OF IONIC FLYERS --- p.11 / Chapter 3.l --- Analysis on the Electrode Length --- p.11 / Chapter 3.2 --- Analysis on the Emitter radius --- p.12 / Chapter 3.3 --- Analysis on the Gap Distance between Emitter and Collector --- p.13 / Chapter 3.4 --- Analyses on the Emitter-Collector Electrodes Configuration --- p.15 / Chapter 3.4.1 --- Single-Emitter-Single-Collector Wire-Plate Configuration --- p.15 / Chapter 3.4.2 --- Multiple-Emitter-Single-Collector Wire-Plate Configuration --- p.16 / Chapter 3.4.3 --- Single-Emitter-Multiple-Collector Wire-Plate Configuration --- p.17 / Chapter 3.4.4 --- Single-Emitter-Surface-Collector Wire-Plate Configuration --- p.19 / Chapter 3.5 --- Summary - Optimization Design Methodology --- p.21 / Chapter CHAPTER 4: --- HIGH VOLTAGE POWER GENERATION SYSTEM --- p.22 / Chapter 4.1 --- Existing Marketable High Voltage Power Supplies --- p.22 / Chapter 4.2 --- design of the High Voltage Power Supply --- p.24 / Chapter 4.2.1 --- Battery --- p.25 / Chapter 4.2.2 --- Step-up Transformer --- p.25 / Chapter 4.2.3 --- Voltage Multiplier --- p.26 / Chapter 4.2.4 --- Driving Circuit --- p.27 / Chapter 4.3 --- Testing prototypes --- p.28 / Chapter 4.3.1 --- First Prototype --- p.28 / Chapter 4.3.2 --- Second Prototype --- p.29 / Chapter 4.3.3 --- Third Prototype --- p.30 / Chapter 4.3.4 --- Fourth Prototype --- p.31 / Chapter 4.3.5 --- Comparison of the Four Prototypes --- p.32 / Chapter 4.4 --- Performance of the High Voltage Power Supply --- p.34 / Chapter 4.4.1 --- Vary with Frequency --- p.34 / Chapter 4.4.2 --- Vary with Duty Cycle --- p.34 / Chapter 4.4.3 --- Efficiency --- p.35 / Chapter 4.5 --- Resonance Frequency Tracking Algorithm --- p.36 / Chapter 4.5.1 --- Fixed Frequency --- p.37 / Chapter 4.5.2 --- Scan Through a Frequency Range --- p.37 / Chapter 4.5.3 --- Continuous Comparison of Feedback Voltages --- p.38 / Chapter 4.5.4 --- Comparison of the Three Approaches --- p.40 / Chapter 4.6 --- Possibility Analysis on Self-Sufficient On-board Power Supply --- p.41 / Chapter 4.6.1 --- Analysis Based on the Parametric models --- p.41 / Chapter 4.6.2 --- Proposed Solution - Ionic Propulsion Blimp --- p.43 / Chapter CHAPTER 5: --- DEVELOPMENT OF IONIC PROPULSION BLIMP --- p.44 / Chapter 5.l --- Design and Structure of Ionic Propulsion Blimp --- p.44 / Chapter 5.1.1 --- Required Volume of the Blimp --- p.45 / Chapter 5.1.2 --- Initial Experimental results of Ionic Propulsion Blimp --- p.46 / Chapter 5.2 --- Advanced Navigation System for Ionic Propulsion Blimp --- p.47 / Chapter 5.2.1 --- Direction Control System --- p.47 / Chapter 5.2.2 --- Vision-Based Sensing and Control System --- p.48 / Chapter 5.3 --- Experimental results of the Advanced Navigation System --- p.55 / Chapter 5.3.1 --- Manual Control for Directional Movement --- p.55 / Chapter 5.3.2 --- Object Tracking using L-K Feature Tracking method --- p.56 / Chapter 5.3.3 --- Object Tracking using CamShift method --- p.57 / Chapter 5.3.4 --- Short summary for Vision-Based Control --- p.57 / Chapter CHAPTER 6: --- FURTHER DEVELOPMENT --- p.58 / Chapter 6.1 --- Improvement on Fabrication of Ionic Flyer --- p.58 / Chapter 6.2 --- Feasibility study on decreasing the operation voltage by minimizing the Gap Distance --- p.59 / Chapter 6.3 --- Improvement of the Design of Ionic Propulsion Blimp --- p.60 / Chapter 6.3.1 --- Design of Configuration of the Navigation System --- p.60 / Chapter 6.3.2 --- Design of the Ionic Flyer --- p.60 / Chapter 6.4 --- Commercialization Issue --- p.61 / Chapter 6.4.1 --- Safety Concerns --- p.61 / Chapter 6.4.2 --- Potential Application of Ionic Propulsion Technology --- p.63 / Chapter CHAPTER 7: --- CONCLUSION --- p.64 / BIBLIOGRAPHY --- p.66 / PUBLICATIONS --- p.69

No description available.

No description available.

No description available.

No description available.