Propõe-se aqui uma metodologia de projeto aero-termo-estrutural de motores foguete a propelente sólido. O projeto de um motor foguete deve ser realizado com o objetivo de cumprir requisitos de uma missão. Para cada veículo espacial, com uma nova missão, um novo motor pode ser projetado, necessitando para isso de uma série de ferramentas robustas, capazes de compreender todas as combinações de esforços existentes no funcionamento de um motor, sob condições de altas pressões e temperaturas. A metodologia aqui proposta é testada e validada em bancada de ensaios desenvolvida para este fim. Os resultados obtidos mostram que a metodologia utilizada se aproxima bastante dos resultados teóricos e pode ser ajustada por coeficientes de eficiência com grande facilidade. / It is proposed here an aero-thermo-structural design methodology for solid propellant rocket motors. The design of a rocket motor must be carried out in order to fulfill requirements of a mission. For each new space vehicle, with a new mission, a new motor can be designed, requiring for it a variety of robust tools, able to comprise all combinations of load existing in the operation of a motor under high pressures and temperatures. The methodology proposed here is tested and validated in bank of tests developed for this purpose. The results show that the methodology is very close to the theoretical results and can be adjusted by coefficients of efficiency with great ease.

Cette thèse porte sur la méthode de Fluorescence Induite par Laser (LIF) à haute cadence développée sur deux atomes métalliques (Al et Fe) utilisés comme traceurs fluorescents dans les flammes de propergols solides où ils sont naturellement présents. Deux expériences d’évaporation de l’aluminium sont mises en œuvre pour mettre au point la technique dans des conditions contrôlées sur une large gamme de pressions et températures. Un modèle théorique du processus de fluorescence appliqué à ces deux atomes est élaboré pour calculer les taux de quenching du signal avec la pression et la température. Les données collisionnelles qui sont inconnues sont prédéterminées théoriquement pour Fe et expérimentalement pour Al. Les coefficients de transferts d’énergie et d’élargissements spectraux par collisions de l’atome Al sont déterminés expérimentalement en environnement d’azote pur. Une étude du comportement du signal de Al avec l’énergie laser est effectuée pour mesurer les seuils de saturation avec les gaz N₂, Ar et He en fonction de la pression. Le modèle permet de reproduire correctement les profils temporels et spectraux avec toutefois des approximations et des limitations qui sont explicitées. Une première application de l’imagerie LIF sur Al dans une flamme de propergol solide aluminisé (10 bar et 3000 K) permet de visualiser des gouttes d’aluminium réactives et observer leur évolution dans la flamme. / During the PhD thesis, high-speed laser induced fluorescence (LIF) of two metallic atoms (Al and Fe) is presented, in order to use them as fluorescent markers in solid propellant flames, where they are naturally present. LIF measurements are first performed inside two different evaporation chambers used to generate aluminum vapors in controlled conditions over a broad pressure and temperature range. A theoretical model of the LIF process is elaborated and applied to both atoms in order to calculate the signal quenching rate as a function of pressure and temperature. Unavailable collisional data are determined theoretically for Fe and experimentally for Al. Energy transfer and collisional broadening coefficients are determined experimentally for the Al atom in pure nitrogen environment. Study of the signal level of Al as a function of laser intensity is undertaken to measure saturation thresholds in N₂, He and Ar as a function of pressure. The model is used to properly reproduce the temporal and spectral profiles, though some approximations and limitations remain. A first application of high-speed LIF imaging to the measurement of aluminum in a solid propellant flame (10 bar , 3000 K) is demonstrated. It allows us to clearly visualize reactive aluminum droplets in the flame and to follow their evolution in the flame.

Two topics relating to low gravity fluid behavior in satellite propellant tanks are considered. In the first, static case, the problem of liquid trapping is examined. Satellite propellant tank end caps optimized for weight are generally shallower and more oblate than hemispherical end caps of the same radius. However, these shallower end caps pose an interesting challenge for propellant management. In the absence of vanes, it is possible for liquid propellant to be trapped in the tank and become unusable. Understanding of how propellant tends to distribute itself in the bare, vaneless tank can be used to drive vane design to counteract these tendencies and ensure propellant remains where desired. The first section of this thesis aims to demonstrate methods that can be used to identify when, how, and why liquid trapping occurs in a given tank geometry. A fluid statics code called Surface Evolver is used to calculate possible fluid configurations for different propellant volumes, contact angles, and end cap designs. The specific case of a cylindrical tank with 2:1 ellipsoidal end caps is studied extensively for ranges of fill fractions and contact angles to illustrate the methods used. Results are computed for each possible propellant configuration: a spherical liquid-gas interface, an asymmetric liquid-gas interface, and a liquid ring. Analytical solutions are found and compared against Surface Evolver results for the spherical liquid-gas interface and liquid ring, showing excellent agreement. Results are also found for other aspect ratio ellipsoidal end caps, superellipsoidal end caps, and torispherical end caps. Each non-hemispherical dome design is found to be able to trap liquid away from the axis of the tank regardless of contact angle. The second part of this thesis, focusing on the dynamic case, details the development of an experimental payload designed to fly on Virgin Galactic’s SpaceShipTwo. This experiment is designed to obtain data on sloshing behavior of liquids in microgravity in response to rotation. The payload contains eight scaled down propellant tanks that are rotated while in microgravity, and the resulting slosh is recorded by video cameras inside the payload. The video will be analyzed after the experiment to extract data on damping rates and potentially positional data of the liquid-gas interface. The impact of constraints on the design of the overall experiment are discussed. The purpose of each component in the experiment is explained and justified relative to the design constraints. The remaining work that must be completed before flight on SpaceShipTwo is reviewed, highlighting the most significant unknowns.<br>

The objective of this diploma thesis is to perform a conceptual lay-out of a small launcher. Re- quirements have been defined in order to realize this first preliminary study and design of a small launcher. In that frame, a MATLAB code has been written in order to simulate the rocket tra- jectories. An optimization program on launcher staging has been written as well. To validate this code, the VEGA and Ariane 5 launchers have been used. Then from studies on existing launchers, simulations have been performed in order to find an optimum small launcher and later on to design more precisely the small launcher. As a requirement an upper stage has been newly designed for the purpose of the study. At the end, two small launchers have been considered: a three-stage launcher using the Zefiro 23 as a first stage, the Zefiro 9 as a second stage, and an upper stage using a 3kN thrust engine; a two-stage launcher using the Zenit booster engine in the first stage, and an upper stage using a 22kN thrust engine.

This document details original numerical studies performed by the author pertaining to solid propellant combustion. Detailed kinetic mechanisms have been utilized to model the combustion of the pseudo-propellants RDX/GAP and AP/HTPB. A particle packing model and a diffusion flame model have been utilized to develop a burning rate and an aluminum agglomeration model. The numerical model for RDX/GAP combustion utilizes a "universal" gas-phase kinetic mechanism previously applied to combustion models of several monopropellants and pseudo-propellants. The kinetic mechanism consists of 83 species and 530 reactions. Numerical results using this mechanism provide excellent agreement with RDX and GAP burning rate data, and agree qualitatively with RDX/GAP pseudo-propellant data. The numerical model for AP/HTPB combustion utilizes the same universal mechanism, with chlorine reactions added for modeling AP combustion. Including chlorine, there are 106 species and 611 reactions. Global condensed-phase reactions have been developed for six AP percentages between 59% and 80% AP. The AP/HTPB model accurately predicts burning rates, as well as temperature and species profiles. The numerical burning rate model utilizes a three-dimensional particle-packing model to generate cylindrical particle packs. Particle-size distributions have been modeled using a three-parameter lognormal distribution function. Pressure-dependent homogenization has been used to capture pressure effects and reduce cpu time. A "characteristic" burning path is found through each particle pack. Numerical results showed that different path-finding approaches work better depending on the propellant formulation and combustion conditions. Proposed future work and modifications to the present model are suggested. The numerical agglomeration model utilizes the same particle packing model and particle-size distribution function as in the burning rate model. Three preliminary models have been developed examining the ideas of pockets, separation distance, and aluminum ignition. Preliminary model results indicate the importance of predicting aluminum particle ignition. In the final model, the surface is regressed numerically through each particle pack. At each surface location, calculations are performed to determine whether aluminum particles combine and/or ignite. Ignition criteria have been developed from the results of the diffusion flame model and an analysis of particle-pack cross-sections. Numerical results show qualitative agreement with each experimentally observed trend. Proposed future work and modifications to the present model are suggested.

The application of emission spectroscopy to monitor combustion products of solid rocket propellant combustion can potentially yield valuable data about reactions occurring within the volatile environment of a strand burner. This information can be applied in the solid rocket propellant industry. The current study details the implementation of a compact spectrometer and fiber optic cable to investigate the visible emission generated from three variations of solid propellants. The grating was blazed for a wavelength range from 200 to 800 nm, and the spectrometer system provides time resolutions on the order of 1 millisecond. One propellant formula contained a fine aluminum powder, acting as a fuel, mixed with ammonium perchlorate (AP), an oxidizer. The powders were held together with Hydroxyl-Terminated-Polybutadiene (HTPB), a hydrocarbon polymer that is solidified using a curative after all components are homogeneously mixed. The other two propellants did not contain aluminum, but rather relied on the HTPB as a fuel source. The propellants without aluminum differed in that one contained a bimodal mix of AP. Utilizing smaller particle sizes within solid propellants yields greater surface area contact between oxidizer and fuel, which ultimately promotes faster burning. Each propellant was combusted in a controlled, non-reactive environment at a range of pressures between 250 and 2000 psi. The data allow for accurate burning rate calculations as well as an opportunity to analyze the combustion region through the emission spectroscopy diagnostic. It is shown that the new diagnostic identifies the differences between the aluminized and non-aluminized propellants through the appearance of aluminum oxide emission bands. Anomalies during a burn are also verified through the optical emission spectral data collected.

The purpose of this study is to examine the burning behaviour of composite solid propellants (CSP) in the presence of nanoscale, heterogenous catalysts. The study targets the decomposition of ammonium perchlorate (AP) as a key component in the burning profile of these propellants, and seeks to identify parameters of AP decomposition reaction that can be affected by catalytic additives. The decomposition behavior of AP was studied in the presence of titanium dioxide nanoparticles in varying configurations, surface conditions, dopants, morphology, and synthesis parameters with the AP crystals. The catalytic nanoparticles were found to enhance the decomposition rate of the ammonium perchlorate, and promote an accelerated burning rate of CSP propellants containing the additives. Furthermore, different configurations were shown to have varying degrees of effectiveness in promoting the decomposition behaviour. To study the effect of the catalyst’s configuration in the bulk propellant, controlled dispersion conditions of the nanoparticle catalysts were created and studied using differential scanning calorimetry, as well as model propellant strand burning. The catalysts were shown to promote the greatest enthalpy of reaction, as well as the highest burn rate, when the AP crystals were recrystalized around the nanoparticle additives. This is in contrast to the lowest enthalpy condition, which corresponded to catalysts being dispersed upon the AP crystal surface using bio-molecule templates. Additionally, a method of facile, visible light nanoparticle tracking was developed to study the effect of mixing and settling parameters on the nano-catalysts. To accomplish this, the titania nanoparticles were doped with fluorescent europium molecules to track the dispersion of the catalysts in the propellant binder. This method was shown to succesfully allow for dispersion and agglomeration monitoring without affecting the catalytic effect of the TiO2 nanoparticles.

The radiation environment in space is a threat that engineers and astronauts need to mitigate as exploration into the solar system expands. Passive shielding involves placing as much material between critical components and the radiation environment as possible. However, with mass and size budgets, it is important to select efficient materials to provide shielding. Currently, NASA and other space agencies plan on using water as a shield against radiation since it is already necessary for human missions. Water has been tested thoroughly and has been proven to be effective. Liquid propellants are needed for every mission and also share similar characteristics to water such as their density and hydrogenous composition. This thesis explores the shielding potentials of various liquid propellants as they compare to water for the purpose of providing an additional parameter when choosing propellants for any given mission. Testing propellants is done by first creating an experimental setup involving radioisotope sources Cs-137 and Co-60, a column of liquid with variable depths, and a Geiger-Mueller tube. Water and three other liquids: acetone, 70% isopropyl alcohol, and 12% hydrogen peroxide are physically tested and their linear attenuation coefficients are calculated. Then, the test setup is replicated in CERN’s Monte Carlo base radiation transport code, FLUKA. Although the calculated linear attenuation outputs from FLUKA are discrepant from experimental results by an average of 34%, they produce the same trends. FLUKA is used to expand upon experimental results by simulating a multitude of liquid propellants and comparing them all to water. FLUKA has the ability to simulate all propellants including hydrogen, oxygen, hydrazine, and dinitrogen tetroxide. Most of the tested propellants are found to have similar, to within 35%, gamma radiation linear attenuation coefficients as compared to water. The gamma radiation in this thesis’s experiment and simulations comes from Cs-137 and Co-60 radioisotope sources. For gamma radiation from the Co-60 source, liquid hydrogen provides 90% less attenuation than water and nitric acid and AF-M315E provide 35% and 38% more attenuation than water respectively. For gamma radiation emitted by Cs-137, liquid hydrogen, isopropyl alcohol, and methane have 90%, 35%, and 29% less attenuation than water respectively. Dinitrogen tetroxide, hydrogen peroxide, AF-M315E, and nitric acid have 34%, 41%, 46%, and 52% greater attenuation coefficients than water respectively. The liquids that are similar to water for the Cs-137 source have linear attenuation coefficients within 20% of water’s. Ultimately, most of the tested liquid propellants are shown to shield against radiation at a similar rate to water. Thus, an additional parameter for choosing liquid propellants on any given mission should be their radiation shielding capabilities.

<p>When characterizing a new solid propellant, one of the most important steps in determining its usefulness is discovering how the burning rate changes in response to changes in pressure. While there are many dynamic methods for directly measuring the regression rate of a burning propellant sample, few of them are capable of being used in typical harsh motor conditions: high pressures, high temperatures, and in an environment comprised of propellant exhaust products. This paper describes and evaluates the use of two custom-built microwave interferometers, one operating at 35 GHz and the other operating at 94 GHz, in several different configurations for the measurement of propellant regression rates. Four different configurations of interferometer and waveguide are presented and contrasted, with example results of experiments included. A polytetrafluoroethylene (PTFE) waveguide, utilized in previous works for explosives detonation velocity characterization, was used to directly couple interferometer signal with a burning propellant strand. This PTFE coupling is shown to be applicable to pressure vessel studies by simply using a cable feedthrough. In this configuration, signal quality is high but signal amplitude is low, especially when the waveguide is encased by support structures. A novel PTFE truncated cone waveguide expander is presented which performs three tasks: expanding the microwave signal such that an oversized (relative to signal wavelength) strand may be examined via microwave interferometry, functioning as a weak antenna that can observe phenomena through interstitial material without picking up significant amounts of environmental reflection, and acting as a sealing surface for pressure vessel experiments. Additionally, the use of a more-standard hollow-core waveguide and high-gain antenna is displayed, highlighting the increased signal strength but the larger number of spurious reflections in the signal. This study shows, through various experiments using the aforementioned configurations, the capability of microwave interferometry to quickly characterize a full propellant burning rate curve using a single dynamic-pressure test with 40g of propellant in a 2.5cm diameter propellant strand. Several novel combinations of mechanical configuration and propellant composition are shown that may guide future studies into the use microwave interferometry for solid propellant regression rate analysis.</p>

<p dir="ltr">Smart energetics are energetic materials (propellants, explosives, and pyrotechnics) with on/off capabilities or in real time modification of combustion behavior. Solid propellants are known for many positive qualities such as their simplicity and low cost but also their glaring lack of active burning rate control. Previous proposed methods of active control of solid propellants include pintle valve actuation and electronically controlled solid propellants, however there is a need for improved methods. Surface area modification is one proposed method and can be employed in real time to affect the burning behavior of solid propellants. To this end, derivations were conducted regarding a slot adjacent to a solid propellant strand and the pressure and slot width threshold conditions that allow for burning to occur inside of the adjacent slot. The derivations considered different modes of combustion (convective and conductive) and combustion threshold conditions. The derivations resulted in five equations that were curve fit to existing literature for validation resulting in high R squared values. A demonstration of the creation of an adjacent slot with a piezoelectric actuator, a mini case study of the adjacent slot proposal, and a discussion of methods to create an adjacent slot as well as the effect of propellant selection on convective burning in slots were all done to follow up on the promising results of the theoretical work. </p><p dir="ltr">Furthermore, flexoelectricity is the coupling between strain gradient and charge generation and has been considered to modify the combustion characteristics of energetic materials. This work measured the flexoelectric properties of polymers and their associated energetic composites including polyvinylidene fluoride (PVDF), micron aluminum (μAl)/PVDF, nano aluminum (nAl)/PVDF, poly(vinylidene fluoride-co-trifluoroethylene) (P(VDF-TrFE)), nAl/P(VDF-TrFE), poly(vinylidene fluoride-co-hexafluoropropylene) (P(VDF-HFP)), μAl/P(VDF-HFP), hydroxylterminated polybutadiene (HTPB), ammonium perchlorate (AP)/HTPB, μAl/AP/HTPB, polytetrafluoroethylene (PTFE), and polydimethylsiloxane (PDMS). The measurements made on PVDF, μAl/PVDF, P(VDF-TrFE), P(VDF-HFP), PTFE, and PDMS were all within or near to the range of measurements from the literature. Novel measurements were made on nAl/PVDF, nAl/P(VDF-TrFE), μAl/P(VDF-HFP), HTPB, AP/HTPB, and μAl/AP/HTPB. Additionally, the effect of porosity, particle additions (μAl, nAl, or AP), and manufacturing method (3D printing, casting, different 3D printers, etc.) on the flexoelectric performance of these samples was investigated. It was found that large pores (millimeter scale) added via the infill pattern of 3D printed PVDF and Al/PVDF samples decreased the effective flexoelectric effect relative to the near full density control samples. This contrasts with previous work showing that adding small (micron scale) pores increases the flexoelectric performance of various polymers and energetic materials. Mixed results were found with respect to the effect of particle additions (μAl, nAl, or AP) on the flexoelectricity of a variety of materials. This may be explained by the competing effect of particle additions adding extra local strain gradients which amplify flexoelectricity but also replace some polymer binder material (PVDF, P(VDF-TrFE), P(VDF-HFP), and HTPB) with the particle additions (μAl, nAl, and AP) which are typically less flexoelectric. Our work demonstrates that manufacturing method does affect the flexoelectric properties of polymers and energetic composites. Lastly, our flexoelectric measurements of P(VDF-HFP) and PTFE may help explain accidents related to Magnesium-Teflon®-Viton® (MTV) flare systems that have, in many cases, been attributed to electrostatic discharge.</p>