Several methods are presented for the design of satellite formations for science missions in high-eccentricity reference orbits with quantifiable performance criteria specified throughout only a portion the orbit, called the Region of Interest (RoI). A modified form of the traditional average along-track drift minimization condition is introduced to account for the fact that performance criteria are only specified within the RoI, and a robust formation design algorithm (FDA) is defined to improve performance in the presence of formation initialization errors. Initial differential mean orbital elements are taken as the design variables and the Gim-Alfriend state transition matrix (G-A STM) is used for relative motion propagation. Using mean elements and the G-A STM allows for explicit inclusion of J2 perturbation effects in the design process. The methods are applied to the complete formation design problem of the NASA Magnetospheric Multiscale (MMS) mission and results are verified using the NASA General Mission Analysis Tool (GMAT). Since satellite formations in high-eccentricity orbits will spend long times at high altitude, third-body perturbations are an important design consideration as well. A detailed analytical analysis of third-body perturbation effects on satellite formations is also performed and averaged dynamics are derived for the particular case of the lunar perturbation. Numerical results of the lunar perturbation analysis are obtained for the example application of the MMS mission and verified in GMAT.

<div> <div> <div> <p>A control methodology to design and establish spacecraft formations is presented. The intuitive design of complex spacecraft formation geometry is achieved by utilizing two different sets of relative orbital elements derived from a linearization of the dynamics. These sets provide strong insights into the shape, size, and orientation of the relative trajectory and facilitate the design of relative orbits in addition to relative positions. An artificial potential function (APF) composed of an attractive potential for goal seeking and a repulsive potential for obstacle avoidance is constructed. The derivation of a control law from this APF results in a computationally efficient algorithm able to fully control the relative position and velocity of the spacecraft and therefore to establish spacecraft formations. The autonomous selection of some of the design parameters of the model based on fuel minimization considerations is described. An assessment of the formation establishment accuracy is conducted for different orbital perturbation as well as various degrees of thrust errors and state uncertainties. Then, the performance of the control algorithm is demonstrated with the numerical simulation of four different scenarios. The first scenario is the design and establishment of a 10-spacecraft triangular lattice, followed by the establishment of a 37-spacecraft formation composed of two hexagonal lattices on two different relative planes. The control method is used to illustrate proximity operations with the visual inspection of an on-orbit structure in the third scenario. Finally, a formation composed of four spacecraft arranged in a tetrahedron is presented.<br></p> </div> </div> </div>

No description available.

The well-known spectroscopic binary ϕ Per is a peculiar compact system, composed of a Be star with an O-type subdwarf companion. A set of nearly 400 spectra in the red and blue regions from Ondřejov and Potsdam Observatories as well as spectra published in the BeSS database were examined. From the radial velocities of Hα, Hβ, and Hγ emission lines and FUV observations from the IUE and HST, a new precise ephemeris was determined. The revised values of M sin3 (i) are 11.84 and 1.48 M (with uncertainties of 0.64 and 0.09 M ), re- spectively, for the primary and secondary. In addition, the system shows cyclic variations (with a time scale of about 5 years) in the profiles of Balmer lines, manifested in their radial velocities, central intensities and V/R ratios. Understanding complex stellar systems requires combining multiple types of ob- servations and creating models of sufficient complexity. In our case, a combination of interferometric visibilities from the CHARA/VEGA array, spectral energy dis- tribution as well as individual spectral lines were used. Radiative-transfer compu- tations were performed with the program PYSHELLSPEC, and physical parameters of the ϕ Per primary and the surrounding disc were derived. They correspond to an evolved system, in which most of mass was transferred from the secondary to...

Vikram Sarabhai Space Centre,Trivandrum / In the space surrounding the earth there are two major regions where orbital debris causes concern. They are the Low Earth Orbits (LEO) up to about 2000 km, and Geosynchronous Orbits (GEO) at an altitude of around 36000 km. The impact of the debris accumulations are in principle the same in the two regions; nevertheless they require different approaches and solutions, due to the fact that the perturbations in the orbital decay due to atmospheric drag effects predominates in LEO, gravitational forces including earth’s oblateness and luni solar effects dominating in GEO are different in these two regions. In LEO it is generally known that the debris population dominates even the natural meteoroid population for object sizes 1 mm and larger. This thesis focuses the study mainly in the LEO region. Since the first satellite breakup in 1961 up to 01 January 2003 more than 180 spacecraft and rocket bodies have been known to fragment in orbit. The resulting debris fragments constitute nearly 40% of the 9000 or more of the presently tracked and catalogued objects by USSPACECOM. The catalogued fragment count does not include the much more numerous fragments, which are too small to be detected from ground. Hence in order to describe the trackable orbital debris environment, it is important to develop mathematical models to simulate the trackable fragments and later expand it to untrackable objects. Apart from the need to better characterize the orbital debris environment down to sub millimeter particles, there is also a pressing necessity of simulation tools able to model in a realistic way the long term evolution of space debris, to highlight areas, which require further investigations, and to study the actual mitigation effects of space policy measures. The present thesis has provided newer perspectives for five major issues in space debris modeling studies. The issues are (i) breakup modeling, (ii) environment modeling, (iii) evolution of the debris environment, (iv) collision probability analysis and (v) reentry prediction. The Chapter 1 briefly describes an overview of space debris environment and the issues associated with the growing space debris populations. A literature survey of important earlier work carried out regarding the above mentioned five issues are provided in the Chapter 2. The new contributions of the thesis commence from Chapter 3. The Chapter 3 proposes a new breakup model to simulate the creation of debris objects by explosion in LEO named “A Semi Stochastic Environment Modeling for Breakup in LEO” (ASSEMBLE). This model is based on a study of the characteristics of the fragments from on orbit breakups as provided in the TLE sets for the INDIAN PSLV-TES mission spent upper stage breakup. It turned out that based on the physical mechanisms in the breakup process the apogee, perigee heights (limited by the breakup altitude) closely fit suitable Laplace distributions and the eccentricity follows a lognormal distribution. The location parameters of these depend on the orbit of the parent body at the time of breakup and their scale parameters on the intensity of explosion. The distribution of the ballistic coefficient in the catalogue was also found to follow a lognormal distribution. These observations were used to arrive at the proper physical, aerodynamic, and orbital characteristics of the fragments. Subsequently it has been applied as an inverse problem to simulate and further validate it based on some more typical well known historical on orbit fragmentation events. All the simulated results compare quite well with the observations both at the time of breakup and at a later epoch. This model is called semi stochastic in nature since the size and mass characteristics have to be obtained from empirical relations and is capable of simulating the complete scenario of the breakup. A new stochastic environment model of the debris scenario in LEO that is simple and impressionistic in nature named SIMPLE is proposed in Chapter 4. Firstly among the orbital debris, the distribution of the orbital elements namely altitude, perigee height, eccentricity and the ballistic coefficient values for TLE sets of data in each of the years were analyzed to arrive at their characteristic probability distributions. It is observed that the altitude distribution for the number of fragments exhibits peaks and it turned out that such a feature can be best modeled with a tertiary mixture of Laplace distributions with eight parameters. It was noticed that no statistically significant variations could be observed for the parameters across the years. Hence it is concluded that the probability density function of the altitude distribution of the debris objects has some kind of equilibrium and it follows a three component mixture of Laplace distributions. For the eccentricity ‘e’ and the ballistic parameter ‘B’ values the present analysis showed that they could be acceptably quite well fitted by Lognormal distributions with two parameters. In the case of eccentricity also the describing parameter values do not vary much across the years. But for the parameters of the B distribution there is some trend across the years which perhaps may be attributed to causes such as decay effect, miniaturization of space systems and even the uncertainty in the measurement data of B. However in the absence of definitive cause that can be attributed for the variation across the years, it turns out to be best to have the most recent value as the model value. Lastly the same kind of analysis has also been carried out with respect to the various inclination bands. Here the orbital parameters are analyzed with respect to the inclination bands as is done in ORDEM (Kessler et al 1997, Liou et al 2001) for near circular orbits in LEO. The five inclination bands considered here are 0-36 deg (in ORDEM they consider 19-36 deg, and did not consider 0-19 deg), 36-61 deg, 61-73 deg, 73-91 deg and 91- 180 deg, and corresponding to each band, the altitude, eccentricity and B values were modeled. It is found that the third band shows the models with single Laplace distribution for altitude and Lognormal for eccentricity and B fit quite well. The altitude of other bands is modeled using tertiary mixture of Laplace distributions, with the ‘e’ and ‘B’ following once again a Lognormal distribution. The number of parameter values in SIMPLE is, in general, just 8 for each description of altitude or perigee distributions whereas in ORDEM96 it is more. The present SIMPLE model captures closely all the peak densities without losing the accuracy at other altitudes. The Chapter 5 treats the evolution of the debris objects generated by on orbit breakup. A novel innovative approach based on the propagation of an equivalent fragment in a three dimensional bin of semi major axis, eccentricity, and the ballistic coefficient (a, e, B) together with a constant gain Kalman filter technique is described in this chapter. This new approach propagates the number density in a bin of ‘a’ and ‘e’ rapidly and accurately without propagating each and every of the space debris objects in the above bin. It is able to assimilate the information from other breakups as well with the passage of time. Further this approach expands the scenario to provide suitable equivalent ballistic coefficient values for the conglomeration of the fragments in the various bins. The heart of the technique is to use a constant Kalman gain filter, which is optimal to track the dynamically evolving fragment scenario and further expand the scenario to provide time varying equivalent ballistic coefficients for the various bins. In the next chapter 6 a new approach for the collision probability assessment utilizing the closed form solution of Wiesel (1989) by the way of a three dimensional look up table, which takes only air drag effect and an exponential model of the atmosphere, is presented. This approach can serve as a reference collision probability assessment tool for LEO debris cloud environment. This approach takes into account the dynamical behavior of the debris objects propagation and the model utilizes a simple propagation for quick assessment of collision probability. This chapter also brings out a comparison of presently available collision probability assessment algorithms based on their complexities, application areas and sample space on which they operate. Further the quantitative assessment of the collision probability estimates between different presently available methods is carried out and the obtained collision probabilities are match qualitatively. The Chapter 7 utilizes once again the efficient and robust constant Kalman gain filter approach that is able to handle the many uncertain, variable, and complex features existing in the scenario to predict the reentry time of the risk objects. The constant gain obtained by using only a simple orbit propagator by considering drag alone is capable of handling the other modeling errors in a real life situation. A detailed validation of the approach was carried out based on a few recently reentered objects and comparison of the results with the predictions of other agencies during IADC reentry campaigns are also presented. The final Chapter 8 provides the conclusions based on the present work carried together with suggestions for future efforts needed in the study of space debris. Also the application of the techniques evolved in the present work to other areas such as atmospheric data assimilation and forecasting have also been suggested.

Submitted by TAÍS ALVES SILVA RIBEIRO (taisalsiri@hotmail.com) on 2018-10-02T18:03:27Z No. of bitstreams: 1 Dissertacao_certa.pdf: 20657410 bytes, checksum: d693c41e2509cbc2849f995113ce5400 (MD5) / Rejected by Pamella Benevides Gonçalves null (pamella@feg.unesp.br), reason: Solicitamos que realize correções na submissão seguindo as orientações abaixo: • A capa e ficha catalográfica não são consideradas para contagem de páginas. a paginação deve aparecer no canto superior direito a partir da introdução, realizei a contagem das páginas e seu trabalho deve iniciar com o número 15*, após você precisa atualizar a numeração nas listas e no sumário. • Precisa adequar suas referências de acordo com a ABNT 6023 para cada tipo de documento (principalmente artigos de periódicos, artigo publicado em eventos, trabalho acadêmico(tese, dissertações etc), assim, sobre a elaboração das referencias e citações favor solicitar revisão com a bibliotecária Juciene (juciene.pedroso@unesp.br) Mais informações acesse o link: http://www2.feg.unesp.br/Home/Biblioteca21/diretrizes-2016.pdf Agradecemos a compreensão. on 2018-10-02T19:34:08Z (GMT) / Submitted by TAÍS ALVES SILVA RIBEIRO (taisalsiri@hotmail.com) on 2018-10-05T13:09:35Z No. of bitstreams: 1 dissertação_correta.pdf: 20638194 bytes, checksum: 4ad859be9baee51c207bfe90cad14bce (MD5) / Approved for entry into archive by Pamella Benevides Gonçalves null (pamella@feg.unesp.br) on 2018-10-05T19:07:02Z (GMT) No. of bitstreams: 1 ribeiro_tas_me_guara.pdf: 20638194 bytes, checksum: 4ad859be9baee51c207bfe90cad14bce (MD5) / Made available in DSpace on 2018-10-05T19:07:02Z (GMT). No. of bitstreams: 1 ribeiro_tas_me_guara.pdf: 20638194 bytes, checksum: 4ad859be9baee51c207bfe90cad14bce (MD5) Previous issue date: 2018-02-21 / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / Fundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP) / Ocultações estelares de Chariklo em 2013 revelaram algo que era desconhecido até o momento: anéis de partículas em torno de um corpo celeste do Sistema Solar diferente de um planeta. Este fato despertou o interesse da comunidade científica a respeito de assuntos como, por exemplo, o processo de formação desses anéis, por quanto tempo eles existirão, qual a probabilidade de corpos como o de Chariklo possuírem anéis ou ainda como eles se mantêm estáveis ao redor de um pequeno objeto, se comparado aos planetas. Neste trabalho estamos interessados em determinar o modelo físico de Chariklo através da manutenção da estrutura atual dos anéis. Acreditamos que este centauro é um corpo semelhante a um elipsoide, entretanto não sabemos com exatidão as dimensões de seus semieixos físicos a, b e c. As razões entre os valores destes semieixos resultam em diferentes valores para os termos de achatamento e elipticidade de Chariklo, que podem ser representados pelos termos J 2 e C 22 em seu potencial gravitacional. Além de determinar os limites para a forma de Chariklo, queremos também estudar quais são os efeitos que o achatamento e elipticidade do corpo central provocam na dinâmica das partículas dos anéis. Para isso, fizemos simulações numéricas usando um integrador que leva em conta os termos relacionados aos coeficientes J 2 e C 22 . O sistema que integramos é composto por Chariklo sendo orbitado por uma partícula com aproximadamente a mesma distância em que estão os anéis, fazendo uso dos elementos orbitais osculadores. O objetivo dessas simulações foi reproduzir as características físicas dos anéis obtidas através das ocultações estelares, entretanto apenas conseguimos fazer essa reprodução usando valores de J 2 e C 22 muito pequenos, o que contradiz a hipótese do centauro ter diferenças significativas entre seus semieixos físicos. Para valores maiores de J 2 e C 22 as partículas descrevem órbitas com excentricidades muito altas, gerando uma grande variação no raio orbital. Diante disso, passamos a estudar o sistema fazendo uso dos elementos orbitais geométricos encontrados nos artigos de Borderies; Longaretti (1987), Longaretti; Borderies (1991), Borderies-Rappaport; Longaretti (1994) e Renner; Sicardy (2006). Estes trabalhos mostram que o uso de elementos orbitais osculadores, em simulações de partículas que orbitam corpos que são muito achatados, não é adequada. Assim sendo, utilizamos esses novos elementos em nossas simulações considerando apenas o termo J 2 e o efeito de altas excentricidades, que antes ocorria, foi corrigido. No entanto, ao adicionarmos o termo C 22 , a excentricidade das órbitas das partículas voltou a aumentar significativamente, efeito que havia ocorrido quando usamos elementos osculadores nas simulações considerando o termo J 2 . Então, fazemos uma discussão sobre uma possível forma de diminuir a excentricidade provocada pela elipticidade de Chariklo. Por fim, além do estudo sobre a dinâmica das partículas este trabalho conta com uma análise, usando seções de Poincaré, de uma possível ressonância responsável pela estabilidade dos anéis. / Chariklo’s stellar occultations in 2013 revealed something that was unknown to date: particle rings around a celestial body of the Solar system other than a planet. This fact has aroused the interest of the scientific community on issues such as the process of forming these rings, how long they will exist, how likely Chariklo bodies are to have rings or how stable they are around of a small object, compared to the planets. In this work we are interested in determining Chariklo’s physical model by maintaining the current structure of the rings. We believe that this centaur is a body similar to an ellipsoid, but we do not know exactly the dimensions of its physical axes a, b, and c. The ratios between the values of these semi axes result in different values for the Chariklo flattening and ellipticity terms which can be represented by the terms J2 and C22 in its gravitational potential. In addition to determining the limits for the Chariklo form, we also want to study the effects of flattening and ellipticity on the dynamics of ring particles. For this, we did numerical simulations using an integrator that takes into account the terms related to the coefficients J2 and C22. The system we integrate is composed of Chariklo being orbited by a particle approximately the same distance as the rings, making use of the orbital osculating elements. The objective of these simulations was to reproduce the physical characteristics of the rings obtained through stellar occultations, however we can only do this reproduction using values of J2 and C22 very small, which contradicts the hypothesis of the centaur to have significant differences between their physical semi axis. For values greater than J2 and C22 the particles describe orbits with very high eccentricities, generating a large variation in the orbital radius. Therefore, we proceed to study the system making use of the geometric orbital elements found in the Borderies and Longaretti (1987), Longaretti and Borderies (1991), Borderies-Rappaport and Longaretti (1994) and Renner and Sicardy (2006). These studies show that the use of orbital osculating elements in simulations of particles orbiting bodies that are very flattened is not adequate. Therefore, we use these new elements in our simulations considering only the term J2 and the effect of high eccentricity that before happened was corrected. However, in addition to adding the term C22, an eccentricity of the orbits of the particles has again increased significantly, an effect that has occurred when using osculating elements in the simulations considering the term J2. So we did discuss about a possible way to lessen the eccentricity brought about by Chariklo’s elipticity. Finally, besides the study on the dynamics of the particles, this work has an analysis, using sections of Poincaré, of a possible resonance responsible for the stability of the rings / 2016/03727-7

Submitted by TAÍS ALVES SILVA RIBEIRO (taisalsiri@hotmail.com) on 2018-04-24T12:32:11Z No. of bitstreams: 1 Dissertacao.pdf: 20609749 bytes, checksum: a18d083a1bd5b26da4e1633ea672e9fb (MD5) / Approved for entry into archive by Pamella Benevides Gonçalves null (pamella@feg.unesp.br) on 2018-04-25T14:48:36Z (GMT) No. of bitstreams: 1 ribeiro_tas_me_guara.pdf: 20609749 bytes, checksum: a18d083a1bd5b26da4e1633ea672e9fb (MD5) / Made available in DSpace on 2018-04-25T14:48:36Z (GMT). No. of bitstreams: 1 ribeiro_tas_me_guara.pdf: 20609749 bytes, checksum: a18d083a1bd5b26da4e1633ea672e9fb (MD5) Previous issue date: 2018-02-21 / Coordenação de Aperfeiçoamento de Pessoal de Nível Superior (CAPES) / Fundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP) / Ocultações estelares de Chariklo em 2013 revelaram algo que era desconhecido até o momento: anéis de partículas em torno de um corpo celeste do Sistema Solar diferente de um planeta. Este fato despertou o interesse da comunidade científica a respeito de assuntos como, por exemplo, o processo de formação desses anéis, por quanto tempo eles existirão, qual a probabilidade de corpos como o de Chariklo possuírem anéis ou ainda como eles se mantêm estáveis ao redor de um pequeno objeto, se comparado aos planetas. Neste trabalho estamos interessados em determinar o modelo físico de Chariklo através da manutenção da estrutura atual dos anéis. Acreditamos que este centauro é um corpo semelhante a um elipsoide, entretanto não sabemos com exatidão as dimensões de seus semieixos físicos a, b e c. As razões entre os valores destes semieixos resultam em diferentes valores para os termos de achatamento e elipticidade de Chariklo, que podem ser representados pelos termos J 2 e C 22 em seu potencial gravitacional. Além de determinar os limites para a forma de Chariklo, queremos também estudar quais são os efeitos que o achatamento e elipticidade do corpo central provocam na dinâmica das partículas dos anéis. Para isso, fizemos simulações numéricas usando um integrador que leva em conta os termos relacionados aos coeficientes J 2 e C 22 . O sistema que integramos é composto por Chariklo sendo orbitado por uma partícula com aproximadamente a mesma distância em que estão os anéis, fazendo uso dos elementos orbitais osculadores. O objetivo dessas simulações foi reproduzir as características físicas dos anéis obtidas através das ocultações estelares, entretanto apenas conseguimos fazer essa reprodução usando valores de J 2 e C 22 muito pequenos, o que contradiz a hipótese do centauro ter diferenças significativas entre seus semieixos físicos. Para valores maiores de J 2 e C 22 as partículas descrevem órbitas com excentricidades muito altas, gerando uma grande variação no raio orbital. Diante disso, passamos a estudar o sistema fazendo uso dos elementos orbitais geométricos encontrados nos artigos de Borderies; Longaretti (1987), Longaretti; Borderies (1991), Borderies-Rappaport; Longaretti (1994) e Renner; Sicardy (2006). Estes trabalhos mostram que o uso de elementos orbitais osculadores, em simulações de partículas que orbitam corpos que são muito achatados, não é adequada. Assim sendo, utilizamos esses novos elementos em nossas simulações considerando apenas o termo J 2 e o efeito de altas excentricidades, que antes ocorria, foi corrigido. No entanto, ao adicionarmos o termo C 22 , a excentricidade das órbitas das partículas voltou a aumentar significativamente, efeito que havia ocorrido quando usamos elementos osculadores nas simulações considerando o termo J 2 . Então, fazemos uma discussão sobre uma possível forma de diminuir a excentricidade provocada pela elipticidade de Chariklo. Por fim, além do estudo sobre a dinâmica das partículas este trabalho conta com uma análise, usando seções de Poincaré, de uma possível ressonância responsável pela estabilidade dos anéis. / Chariklo’s stellar occultations in 2013 revealed something that was unknown to date: particle rings around a celestial body of the Solar system other than a planet. This fact has aroused the interest of the scientific community on issues such as the process of forming these rings, how long they will exist, how likely Chariklo bodies are to have rings or how stable they are around of a small object, compared to the planets. In this work we are interested in determining Chariklo’s physical model by maintaining the current structure of the rings. We believe that this centaur is a body similar to an ellipsoid, but we do not know exactly the dimensions of its physical axes a, b, and c. The ratios between the values of these semi axes result in different values for the Chariklo flattening and ellipticity terms which can be represented by the terms J2 and C22 in its gravitational potential. In addition to determining the limits for the Chariklo form, we also want to study the effects of flattening and ellipticity on the dynamics of ring particles. For this, we did numerical simulations using an integrator that takes into account the terms related to the coefficients J2 and C22. The system we integrate is composed of Chariklo being orbited by a particle approximately the same distance as the rings, making use of the orbital osculating elements. The objective of these simulations was to reproduce the physical characteristics of the rings obtained through stellar occultations, however we can only do this reproduction using values of J2 and C22 very small, which contradicts the hypothesis of the centaur to have significant differences between their physical semi axis. For values greater than J2 and C22 the particles describe orbits with very high eccentricities, generating a large variation in the orbital radius. Therefore, we proceed to study the system making use of the geometric orbital elements found in the Borderies; Longaretti (1987), Longaretti; Borderies (1991), Borderies-Rappaport; Longaretti (1994) and Renner; Sicardy (2006). These studies show that the use of orbital osculating elements in simulations of particles orbiting bodies that are very flattened is not adequate. Therefore, we use these new elements in our simulations considering only the term J2 and the effect of high eccentricity that before happened was corrected. However, in addition to adding the term C22, an eccentricity of the orbits of the particles has again increased significantly, an effect that has occurred when using osculating elements in the simulations considering the term J2. So we did discuss about a possible way to lessen the eccentricity brought about by Chariklo’s elipticity. Finally, besides the study on the dynamics of the particles, this work has an analysis, using sections of Poincaré, of a possible resonance responsible for the stability of the rings. / 16/03727-7