Thesis -- University of Adelaide, 1966. / [Typescript].

Thesis (M.App.Sc.) - Carleton University, 2007. / Includes bibliographical references (p. 194-202). Also available in electronic format on the Internet.

Thesis (M.S.)--Brigham Young University. Dept. of Physics and Astronomy, 2007. / Includes bibliographical references (p. 99-106).

Este trabalho apresenta propostas de modelos computacionais para representar os principais esquemas de aterramento e equipamentos presentes na rede elétrica de serviço que é utilizada por foguetes de sondagem, com a meta de permitir a verificação operacional e viabilidade técnica no contexto da distribuição de energia elétrica. Nesses modelos são simuladas as condições de operação nominal e em falta, sendo que essa última é realizada em pontos estratégicos da rede elétrica com o propósito de determinar valores máximos de corrente alcançados pelo sistema nessas condições. Os valores de corrente obtidos nessas simulações são principalmente utilizados como referência na escolha do esquema de distribuição da energia elétrica mais adequada para ser utilizado pela rede embarcada em foguetes de sondagem e na determinação de características elétricas mínimas que os equipamentos de bordo devem possuir a fim de atenderem as condições nominais e suportar as possíveis faltas que podem acometer o sistema. Os resultados satisfatórios obtidos nas simulações dos modelos computacionais elaborados para representar os esquemas de aterramento e equipamentos pertencentes à rede elétrica de serviço que é utilizada por foguetes de sondagem, apresentados neste trabalho, indicam que os modelos são consistentes e adequados aos propósitos que se destinam. / This work presents the proposals for computational models to represent the main grounding schemes and equipment used in the service electrical network used by sounding rockets with the goal of enabling the operational verification and technical viability in the context of electrical power distribution. In these models are simulated the conditions of nominal operation and in fault, and the latter is carried out at strategic points in the electrical network with the purpose of determining maximum power achieved by the system under these conditions. The current values obtained in these simulations are mainly used as a guide in choosing the distribution of power best suited to be used by the service electrical network and the determination of electrical characteristics requirements that the equipment should possess in order to meet the nominal conditions and support the possible faults that can affect the system. The satisfactory results obtained in the simulations of the computer models designed to represent the grounding schemes and equipment belonging to the service electrical network used by sounding rockets, presented in this paper indicates that the models are consistent and appropriate to the purposes intended.

No description available.

The behavior of the electric and magnetic fields in the upper atmosphere of the Earth is scientifically interesting but difficult to study, since balloons and aircraft are unable to fly high enough to measure it directly. Sounding rockets, which make a one-time flight carrying instruments that measure the environment around them, have been successfully used to study the upper atmosphere. As the rocket flies through the upper atmosphere, it radios down data about the environment. When scientists on the ground use this data to construct a picture of the upper atmosphere, they run into a problem: the fields reported by the rocket change over time, but it is not clear whether this is because these fields are actually changing in time, or just because the rocket has moved to a different place where the fields are different. This inability to determine whether changes are happening in time or space is called the temporal-spatial ambiguity. This thesis describes the Auroral Spatial Structures Probe (ASSP), a sounding rocket mission that attempts to resolve the temporal-spatial ambiguity by using multiple payloads flying in formation. Several payloads will pass through and measure the same point in space one after another, which will enable us to see how the fields are changing over time.

No description available.

Using the Debye-Huckle approximation, the effects of Coulomb interactions on the equilibrium, frozen, and nonequilibrium flow of an ionized gas have been investigated. The gas is assumed to be monatomic, electrically neutral, and thermal equilibrium (i.e., a one temperature fluid); but the composition of the gas is arbitrary, that is, multiple ionization of any degree is allowed. The thermodynamic variables are derived starting from the appropriate expression for the Helmholtz free energy. Using Boltzmann statistics and assuming that the velocity distribution functions are given by their Maxwellian values, the rate of ionization is derived for atom-atom, atom-ion, and atom-electron collisions. The resulting expressions are then employed in solving the quasi-one-dimensional flow in a converging-diverging nozzle for the equilibrium, frozen, and nonequilibrium cases. Numerical examples, using argon as the working substance, are discussed and the results presented graphically. The results of these calculations indicate that, for single ionization, the effect of Coulomb interactions on the performance of rocket engines is negligible; but that data obtained from hypersonic arc jet wind-tunnels can be significantly influenced by the presence of the interactions. / Ph. D.

A microwave measurement system for obtaining continuous burning-rate information from a solid propellant slab-burning rocket motor is described. A previous derivative-based method for reducing the microwave data is reviewed and an improved data reduction technique is introduced. The improved microwave modeling technique is analyzed using simulated data to determine the accuracy of the burning-rate calculations and the sensitivity of the burning-rate calculations to errors in the model parameters. The microwave model is then used to calculate the burning rate of the propellant for a selected firing of the slab motor. / Master of Science

This thesis presents the results of a three-dimensional flow calculation with a model of turbulent viscosity for a tandem-bladed inducer in air. The purpose is to understand the 3D flow development through the two blade rows and to compare the results of the calculation 'with experimental data. A literature review tells the story of the inducer from the flat-plate design to the tandem-bladed configuration and explains its role in cavitation management. The results of a previous 3D-calculation on the first blade row alone are summarized and the MEFP code is briefly described. The generation of a grid for the second blade row is presented in detail. Then, it is shown how this new grid is linked to the previous grid for the first blade row to get an overall calculation grid for the whole inducer. Two 2D blade-to-blade calculations are shown. They give an insight into the flow behavior through the inducer and allow a test of the grid. The results of the 3D-calculation are discussed and presented extensively with the velocity vectors, the static pressure contours and the rotary stagnation pressure contours on blade-to-blade, meridional and iso-8 vie"rs. The three passages of the second blade row appear to behave differently with respect to their position relative to the wake of the first blade row. The experimental data are used for comparison at three measurement planes in terms of pressure and velocity. They show a fairly good agreement. The three-dimensional calculation predicts also very well the work done and the efficiency of the overall inducer. / Master of Science