Satellite capabilities greatly enhance both the military and civilian sectors of society. Anti-satellite (ASAT) weapons pose a serious risk to all satellites. Chapter One of this thesis discusses current satellite capabilities. Chapter Two, details the wide variety of ASAT weapons. Chapter Three turns to the intentions of various States to employ ASATs. Chapter Four analyzes the legal implications of using force against satellites---beginning with the laws relating to the use of force in general, including the right of self-defense, and then progressing through relevant provisions of the laws of armed conflict. It also addresses the debate over the militarization and weaponization of outer space and past efforts at non-proliferation that relate to space activities. Chapter Five addresses the creation of space debris---a side effect of ASAT use. I will conclude with a short discussion regarding the potential for a new international agreement restricting the use of ASATs.

Thesis (M.S.)--California Polytechnic State University, 2009. / Mode of access: Internet. Title from PDF title page; viewed on June 11, 2009. Major professor: Kira Abercromby, Ph.D. "Presented to the faculty of California Polytechnic State University, San Luis Obispo." "In partial fulfillment of the requirements for the degree [of] Master of Science in Aerospace Engineering." "May 2009." Includes bibliographical references (p. 74-75). Also available on microfiche.

The main purpose of this thesis is to develop a search strategy for space debris that are in the geosynchronous orbit (GEO) region. The search strategy is not an effort to find the object initially but rather if found one time to aid in finding it again within a small time frame. This was a request from NASA Johnson Space Center Orbital Debris Program Office through the MODEST, Michigan Orbital Debris Survey Telescope, program. A single definitive search pattern was not found, however depending on the COEs of the orbit specific search strategy can be employed. These search strategies are far from perfect and can be improved upon with more rigorous testing as well as a larger data sample. Another goal is to look for correlation between the orbital parameters and the errors in the predicted right ascension (RA) and the declination (DEC). This was accomplished by varying the different orbital parameters by ±10% individually while holding the other parameters constant. This showed some correlation existed between some parameters and their errors, in particular there was correlation between a variation in right ascension of ascending node (RAAN) and the value of RAAN itself. The correlation found was that with the higher the value of RAAN the larger the RMS error.

No description available.

Orientador: Silvia Maria Giuliatti Winter / Banca: Antonio Fernando Bertachini de Almeida Prado / Banca: Jarbas Cordeiro Sampaio / Resumo: Neste trabalho apresentamos uma análise da dinâmica de detritos espaciais na ressonância 14:1. O sistema analisado foi o sistema Terra-detrito considerando a não esfericidade da Terra. Para esta análise foram utilizados dois programas, o Mercury e o Algorítimo de Transformada de Fourier Modificado por Frequência. O desenvolvimento do potencial terrestre foi feito considerando os coeficientes de achatamento J2, J3 e C22, e as equações do movimento foram encontradas. Afim de analisar a evolução temporal dos elementos orbitais as equações do movimento foram inseridas no pacote Mercury e um conjunto de integrações para 1 e 20 dias foi realizado. As integrações mostram que os coeficientes afetam significativamente as trajetórias dos detritos. As regiões de estabilidade, instabilidade e o tempo de difusão para 5000 partículas foram analisadas através do mapa de difusão obtido pelo algorítimo de análise de frequência. Os resultados indicam regiões de estabilidade próximas à ressonância 14:1 / Abstract: In this work we present an analysis of the dynamics of spatial debris in the 14: 1 resonance. The system analyzed was the Earth-debris system considering the non-sphericity of the Earth. For this analysis, two programs, Mercury and Frequency Modified Fourier Transform Algorithm, were used. The development of the earth potential was made considering the gravity coefficients J2, J3 and C22, and the equations of motion were found. In order to analyze the time evolution of the orbital elements, the equations of motion were inserted in the Mercury package and a set of integrations for 1 and 20 days was performed. The integrations show that the coefficients significantly affect the trajectories of the debris . The regions of stability, instability and diffusion time for 5000 particles were analyzed by the diffusion map obtained by the frequency analysis algorithm. The results indicate stable regions of close to 14:1 / Mestre

In space, visual based relative navigation systems suffer from the harsh illumination conditions of the target (e.g. eclipse conditions, solar glare, etc.). In current Rendezvous and Docking (RvD) missions, most of these issues are addressed by advanced mission planning techniques (e.g strict manoeuvre timings). However, such planning would not always be feasible for Active Debris Removal (ADR) missions which have more unknowns. Fortunately, thermal infrared technology can operate under any lighting conditions and therefore has the potential to be exploited in the ADR scenario. In this context, this study investigates the benefits and the challenges of infrared based relative navigation. The infrared environment of ADR is very much different to that of terrestrial applications. This study proposes a methodology of modelling this environment in a computationally cost effective way to create a simulation environment in which the navigation solution can be tested. Through an intelligent classification of possible target surface coatings, the study is generalised to simulate the thermal environment of space debris in different orbit profiles. Through modelling various scenarios, the study also discusses the possible challenges of the infrared technology. In laboratory conditions, providing the thermal-vacuum environment of ADR, these theoretical findings were replicated. By use of this novel space debris set-up, the study investigates the behaviour of infrared cues extracted by different techniques and identifies the issue of short-lifespan features in the ADR scenarios. Based on these findings, the study suggests two different relative navigation methods based on the degree of target cooperativeness: partially cooperative targets, and uncooperative targets. Both algorithms provide the navigation solution with respect to an online reconstruction of the target. The method for partially cooperative targets provides a solution for smooth trajectories by exploiting the subsequent image tracks of features extracted from the first frame. The second algorithm is for uncooperative targets and exploits the target motion (e.g. tumbling) by formulating the problem in terms of a static target and a moving map (i.e. target structure) within a filtering framework. The optical flow information is related to the target motion derivatives and the target structure. A novel technique that uses the quality of the infrared cues to improve the algorithm performance is introduced. The problem of short measurement duration due to target tumbling motion is addressed by an innovative smart initialisation procedure. Both navigation solutions were tested in a number of different scenarios by using computer simulations and a specific laboratory set-up with real infrared camera. It is shown that these methods can perform well as the infrared-based navigation solutions using monocular cameras where knowledge relating to the infrared appearance of the target is limited.

The next generation of European scientific satellites will carry extremely sensitive measurement devices that require platform stability orders of magnitude higher than current missions. It is considered that the meteoroid and space debris (M/SD) environment poses a risk to the success of these missions as disturbances induced by the impact of these particles at hypervelocity may degrade the platform stability below operational requirements. In this thesis, disturbances induced by the impact of M/SD particles at hypervelocity on a representative scientific satellite platform have been investigated. An extensive experimental impact test program has been performed, from which an empirical ballistic limit equation (BLE) which defines the conditions of structural perforation for composite sandwich panel structures with CFRP facesheets and aluminium honeycomb cores (CFRP/Al HC SP) has been defined. The BLE is used to predict impact conditions capable of inducing the different excitation modes relevant for a SP sandwich panel structure, enabling a significant reduction in the time and expense usually required for calibrating the protective capability of a new structural configuration. As experimental acceleration facilities are unable to cover the complete range of possible in-orbit impact conditions relevant for M/SD impact risk assessment, a Hydrocode model of the representative CFRP/Al HC SP has been constructed. A series of impact simulations have been performed during which the local impact-induced disturbance has been measured. The numerical disturbance signals have been validated via comparison with experimental disturbance measurements, and subsequently subject to a characterisation campaign to define the local elastic excitation of the SP structure equivalent to that induced by impact of a M/SD particle at hypervelocity. The disturbance characterisation is made such that it is applicable as an excitation force on a global satellite Finite Element (FE) model, allowing propagation of impact-induced disturbances throughout the complete satellite body to regions of critical stability (i.e. measurement devices). The disturbance induced upon measurement devices by M/SD impacts at both near- and far-body locations can then be made, allowing the threat to mission objectives to be assessed.

Thesis (M.A. Sc.)--University of Toronto, 2006. / Source: Masters Abstracts International, Volume: 44-06, page: 2869. Includes bibliographical references.

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A referência deve ser informada ao final, seguindo os padrões da ABNT. Para indicar a fonte, deve ser colocada a autoria e o ano entre parênteses. Ex.: Martins (2010). Quando uma referência for retirada de um meio eletrônico deve-se identificar uma autoria para o que é visualizado na página; se não houver título, escrever uma pequena descrição do que foi visto e seguir com os dados: disponível em:<endereço eletronico> . Acesso em: xx mes xxxx. A autoria pode ser uma pessoa física, uma Instituição, uma empresa, uma pessoa jurídica e até o nome do próprio site. Ex.:  ECOVILAS. Condomínios autossustentados e permaculturais. Disponível em: <http://www.ecoovilas.com/projetos/permacultura>. 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No. of bitstreams: 1 xavier_jr_me_guara.pdf: 4376263 bytes, checksum: 5621e66ab7ef541b1bfd222168e65ef8 (MD5) Previous issue date: 2018-03-07 / Conselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq) / Neste trabalho apresentamos uma análise da dinâmica de detritos espaciais na ressonância 14:1. O sistema analisado foi o sistema Terra-detrito considerando a não esfericidade da Terra. Para esta análise foram utilizados dois programas, o Mercury e o Algorítimo de Transformada de Fourier Modificado por Frequência. O desenvolvimento do potencial terrestre foi feito considerando os coeficientes de achatamento J2, J3 e C22, e as equações do movimento foram encontradas. Afim de analisar a evolução temporal dos elementos orbitais as equações do movimento foram inseridas no pacote Mercury e um conjunto de integrações para 1 e 20 dias foi realizado. As integrações mostram que os coeficientes afetam significativamente as trajetórias dos detritos. As regiões de estabilidade, instabilidade e o tempo de difusão para 5000 partículas foram analisadas através do mapa de difusão obtido pelo algorítimo de análise de frequência. Os resultados indicam regiões de estabilidade próximas à ressonância 14:1. / In this work we present an analysis of the dynamics of spatial debris in the 14: 1 resonance. The system analyzed was the Earth-debris system considering the non-sphericity of the Earth. For this analysis, two programs, Mercury and Frequency Modified Fourier Transform Algorithm, were used. The development of the earth potential was made considering the gravity coefficients J2, J3 and C22, and the equations of motion were found. In order to analyze the time evolution of the orbital elements, the equations of motion were inserted in the Mercury package and a set of integrations for 1 and 20 days was performed. The integrations show that the coefficients significantly affect the trajectories of the debris . The regions of stability, instability and diffusion time for 5000 particles were analyzed by the diffusion map obtained by the frequency analysis algorithm. The results indicate stable regions of close to 14: 1

Every space launch increases the overall amount of space debris. Satellites have limited awareness of nearby objects that might pose a collision hazard. Astrometric, radiometric, and thermal models for the study of space debris in low-Earth orbit have been developed. This modeled approach proposes analysis methods that provide increased Local Area Awareness for satellites in low-Earth and geostationary orbit. Local Area Awareness is defined as the ability to detect, characterize, and extract useful information regarding resident space objects as they move through the space environment surrounding a spacecraft. The study of space debris is of critical importance to all space-faring nations. Characterization efforts are proposed using long-wave infrared sensors for space-based observations of debris objects in low-Earth orbit. Long-wave infrared sensors are commercially available and do not require solar illumination to be observed, as their received signal is temperature dependent. The characterization of debris objects through means of passive imaging techniques allows for further studies into the origination, specifications, and future trajectory of debris objects. Conclusions are made regarding the aforementioned thermal analysis as a function of debris orbit, geometry, orientation with respect to time, and material properties. Development of a thermal model permits the characterization of debris objects based upon their received long-wave infrared signals. Information regarding the material type, size, and tumble-rate of the observed debris objects are extracted. This investigation proposes the utilization of long-wave infrared radiometric models of typical debris to develop techniques for the detection and characterization of debris objects via signal analysis of unresolved imagery. Knowledge regarding the orbital type and semi-major axis of the observed debris object are extracted via astrometric analysis. This knowledge may aid in the constraint of the admissible region for the initial orbit determination process. The resultant orbital information is then fused with the radiometric characterization analysis enabling further characterization efforts of the observed debris object. This fused analysis, yielding orbital, material, and thermal properties, significantly increases a satellite’s Local Area Awareness via an intimate understanding of the debris environment surrounding the spacecraft.