Asteroides

In response to the current interest in CubeSats and potential applications for planetary exploration, this work studies the feasibility of using autonomous CubeSats to flyby near-Earth asteroids. Considering the limited performance of current propulsion systems for CubeSats, low-energy (impulsive and low-thrust) trajectories are designed to encounter near-Earth asteroids in the medium-fidelity Circular Restricted Three-Body Problem, and their existence in a high-fidelity ephemeris model is also verified. The use of large ground antennas for deep-space communications might represent a major portion of CubeSat mission budgets, and thus the feasibility of performing optical navigation to autonomously estimate and correct the trajectory of the CubeSat is also evaluated through Monte Carlo simulations. Preliminary results show that approximately 4 asteroids per year could be reached by a 3U CubeSat if deployed around the first or second Sun-Earth Lagrange points. According to the limited...

Fast development of CubeSat technology now enables the first interplanetary missions. The potential application of CubeSats to flyby near-Earth asteroids is explored in this paper in consideration of CubeSats' limited propulsive capabilities and systems constraints. Low-energy asteroid flyby trajectories are designed assuming a CubeSat is initially parked around to the Sun-Earth Lagrange points. High-impulse and low-thrust trajectories with realistic thrusting models are computed first in the Circular Restricted Three-Body Problem (CR3BP), and then in a high-fidelity ephemeris model. Analysis in the ephemeris model is used to confirm that trajectories computed in the CR3BP model also exist in a more realistic dynamical model, and to verify the validity of the results obtained in CR3BP analysis. A catalogue of asteroid flyby opportunities between years 2019 and 2030 is provided, with 80 m/s of available ΔV and departure from halo orbits around the first and second Sun-Earth Lagrange points (of similar size to those typically used by scientific missions). Results show that the CR3BP model can serve as an effective tool to identify reachable asteroids and can provide an initial estimation of the ΔV cost in the ephemeris model (with ±15 m/s accuracy). An impulsive maneuver model can also provide an accurate estimation of the ΔV requirement for a CubeSat equipped with a high-impulse thruster (with 4 m/s accuracy), even if its thrust magnitude is small and requires duty cycling; low-thrust ΔV requirements, however, may differ significantly from the impulsive results (±15 m/s).

A crucial topic in planetology research is establishing links between primitive meteorites and their parent asteroids. In this study we investigate the feasibility of a connection between asteroids similar to 21 Lutetia, fly-bied by the Rosetta mission in July 2010, and the CH3 carbonaceous chondrite Pecora Escarpment 91467 (PCA 91467). Several spectra of this meteorite were acquired in the ultraviolet to near-infrared (0.3 to 2.2 µm) and in the mid-infrared to thermal infrared (2.5 to 30.0 µm or 4000 to ~333 cm-1), and they are compared here to spectra from the asteroid 21 Lutetia. There are several similitudes in absorption bands and overall spectral behavior between this CH3 meteorite and 21 Lutetia. Considering also that the bulk density of Lutetia is similar to that of CH chondrites, we suggest that this asteroid could be similar, or related to, the parent body of these meteorites, if not the parent body itself. However, the apparent surface diversity of Lutetia pointed out in previous studies indicates that it could simultaneously be related to other types of chondrites. Future discovery of additional unweathered CH chondrites could provide deeper insight in the possible connection between this family of metal-rich carbonaceous chondrites and 21 Lutetia or similar asteroids.

Context. The discovery that the Centaur (10199) Chariklo possesses a ring system opens questions about their origin. Aims. We here asses the plausibility of different scenarios for the origin of the observed ring system. Methods. We first consider the possibility that the material of the ring originated in the disruption of a satellite that had reached a critical distance from the Centaur. We discuss the conditions for the putative satellite to approach the Centaur as a consequence of tidal interaction. A three-body encounter is also considered as a transport mechanism. In addition, we study the case in which the ring is formed by the ejecta of a cratering collision on the Centaur and we constrain the collision parameters and the size of the resulting crater of the event. Finally, we consider that the ring material originates from a catastrophic collision between a background object and a satellite located at a distance corresponding to the the current location of the ring. We compute the typical timescales for these scenarios. Results. We estimate that in order to be tidally disrupted a satellite would have had to be larger than approximately 6.5 km at the location of the rings. However the tidal interaction is rather weak for objects of the size of outer solar system bodies at the ring location, therefore we considered other more effective mechanisms by which a satellite might have approached the Centaur. Collisonal scenarios are both physically plausible for the formation, but semianalytical estimations indicate that the probability of the corresponding collisions is low under current conditions.

In response to the current interest in CubeSats and potential applications for planetary exploration, this work studies the feasibility of using autonomous CubeSats to flyby near-Earth asteroids. Considering the limited performance of current propulsion systems for CubeSats, low-energy (impulsive and low-thrust) trajectories are designed to encounter near-Earth asteroids in the medium-fidelity Circular Restricted Three-Body Problem, and their existence in a high-fidelity ephemeris model is also verified. The use of large ground antennas for deep-space communications might represent a major portion of CubeSat mission budgets, and thus the feasibility of performing optical navigation to autonomously estimate and correct the trajectory of the CubeSat is also evaluated through Monte Carlo simulations. Preliminary results show that approximately 4 asteroids per year could be reached by a 3U CubeSat if deployed around the first or second Sun-Earth Lagrange points. According to the limited...

Enviado el 7 de abril de 2024

El texto explora las ideas de Charles Fourier sobre la atracción sexual y el amor como fuerzas motrices de los planetas, contrastándolas con las concepciones actuales del universo. Reflexiona sobre la posibilidad de un cosmos vivo y vibrante, en contraposición a la visión predominante. Además, establece paralelismos entre la atracción sexual de los astros y las relaciones humanas, destacando la conexión entre ambas.

The aim of this paper is to study the capture of small Near Earth Objects (NEOs) into the Sun-Earth L2 using low-thrust propulsion for mining or science purposes. As it is well known, the vicinity of these points is inside a net of dynamical channels suitable for the transport in the Earth-Moon neighborhood, so different final destinations from here could be easily considered. Asteroids with very small mass and not representing a potential hazard are analyzed. An initial pruning of asteroids is made, considering NEOs with stellar magnitude bigger than 28, which are the smallest available, and NEOs close to the Earth orbit with semi-major axis between 0.85-1.15. Due to the difficult determination of their physical properties, two methods to estimate the asteroid masses are conducted. A procedure to find the low-thrust optimization trajectories has been implemented. The initial seed is obtained integrating forward the equations of motion plus its conjugated equations expressed in cartesian coordinates and applying the Pontryagins maximum principle to obtain the optimal control with a switching function for the thrust. To refine the trajectory a 4 order Runge-Kutta shooting method has been used. The objective function in this study is the fuel consumption. Finally, the capable asteroids to get captured by a low-thrust engine have been listed indicating the main parameters.

In response to the current interest in CubeSats and potential applications for planetary exploration, this work studies the feasibility of using autonomous CubeSats to flyby near-Earth asteroids. Considering the limited performance of current propulsion systems for CubeSats, low-energy (impulsive and low-thrust) trajectories are designed to encounter near-Earth asteroids in the medium-fidelity Circular Restricted Three-Body Problem, and their existence in a high-fidelity ephemeris model is also verified. The use of large ground antennas for deep-space communications might represent a major portion of CubeSat mission budgets, and thus the feasibility of performing optical navigation to autonomously estimate and correct the trajectory of the CubeSat is also evaluated through Monte Carlo simulations. Preliminary results show that approximately 4 asteroids per year could be reached by a 3U CubeSat if deployed around the first or second Sun-Earth Lagrange points. According to the limited...

Fast development of CubeSat technology now enables the first interplanetary missions. The potential application of CubeSats to flyby near-Earth asteroids is explored in this paper in consideration of CubeSats' limited propulsive capabilities and systems constraints. Low-energy asteroid flyby trajectories are designed assuming a CubeSat is initially parked around to the Sun-Earth Lagrange points. High-impulse and low-thrust trajectories with realistic thrusting models are computed first in the Circular Restricted Three-Body Problem (CR3BP), and then in a high-fidelity ephemeris model. Analysis in the ephemeris model is used to confirm that trajectories computed in the CR3BP model also exist in a more realistic dynamical model, and to verify the validity of the results obtained in CR3BP analysis. A catalogue of asteroid flyby opportunities between years 2019 and 2030 is provided, with 80 m/s of available ΔV and departure from halo orbits around the first and second Sun-Earth Lagrange points (of similar size to those typically used by scientific missions). Results show that the CR3BP model can serve as an effective tool to identify reachable asteroids and can provide an initial estimation of the ΔV cost in the ephemeris model (with ±15 m/s accuracy). An impulsive maneuver model can also provide an accurate estimation of the ΔV requirement for a CubeSat equipped with a high-impulse thruster (with 4 m/s accuracy), even if its thrust magnitude is small and requires duty cycling; low-thrust ΔV requirements, however, may differ significantly from the impulsive results (±15 m/s).

In response to the current interest in CubeSats and potential applications for planetary exploration, this work studies the feasibility of using autonomous CubeSats to flyby near-Earth asteroids. Considering the limited performance of current propulsion systems for CubeSats, low-energy (impulsive and low-thrust) trajectories are designed to encounter near-Earth asteroids in the medium-fidelity Circular Restricted Three-Body Problem, and their existence in a high-fidelity ephemeris model is also verified. The use of large ground antennas for deep-space communications might represent a major portion of CubeSat mission budgets, and thus the feasibility of performing optical navigation to autonomously estimate and correct the trajectory of the CubeSat is also evaluated through Monte Carlo simulations. Preliminary results show that approximately 4 asteroids per year could be reached by a 3U CubeSat if deployed around the first or second Sun-Earth Lagrange points. According to the limited...

Fast development of CubeSat technology now enables the first interplanetary missions. The potential application of CubeSats to flyby near-Earth asteroids is explored in this paper in consideration of CubeSats' limited propulsive capabilities and systems constraints. Low-energy asteroid flyby trajectories are designed assuming a CubeSat is initially parked around to the Sun-Earth Lagrange points. High-impulse and low-thrust trajectories with realistic thrusting models are computed first in the Circular Restricted Three-Body Problem (CR3BP), and then in a high-fidelity ephemeris model. Analysis in the ephemeris model is used to confirm that trajectories computed in the CR3BP model also exist in a more realistic dynamical model, and to verify the validity of the results obtained in CR3BP analysis. A catalogue of asteroid flyby opportunities between years 2019 and 2030 is provided, with 80 m/s of available ΔV and departure from halo orbits around the first and second Sun-Earth Lagrange points (of similar size to those typically used by scientific missions). Results show that the CR3BP model can serve as an effective tool to identify reachable asteroids and can provide an initial estimation of the ΔV cost in the ephemeris model (with ±15 m/s accuracy). An impulsive maneuver model can also provide an accurate estimation of the ΔV requirement for a CubeSat equipped with a high-impulse thruster (with 4 m/s accuracy), even if its thrust magnitude is small and requires duty cycling; low-thrust ΔV requirements, however, may differ significantly from the impulsive results (±15 m/s).

Osservazioni satellitari ad alta risoluzione hanno evidenziato un intenso cambiamento del campo magnetico terrestre ad alte latitudini. Gli autori di un articolo recentemente pubblicato sulla rivista Nature spiegano questo fenomeno con la presenza di un flusso di metallo fuso che si muove da est verso ovest all'interno del nucleo terrestre, attorno a un asse centrato sul polo nord geografico. Questa massa, larga 420 km e lunga 7.000 km, si troverebbe a circa 5.000 km di profondità,

A crucial topic in planetology research is establishing links between primitive meteorites and their parent asteroids. In this study we investigate the feasibility of a connection between asteroids similar to 21 Lutetia, encountered by the Rosetta mission in July 2010, and the CH3 carbonaceous chondrite Pecora Escarpment 91467 (PCA 91467). Several spectra of this meteorite were acquired in the ultraviolet to near-infrared (0.3 to 2.2 µm) and in the mid-infrared to thermal infrared (2.5 to 30.0 µm or 4000 to ~333 cm-1), and they are compared here to spectra from the asteroid 21 Lutetia. There are several similarities in absorption bands and overall spectral behavior between this CH3 meteorite and 21 Lutetia. Considering also that the bulk density of Lutetia is similar to that of CH chondrites, we suggest that this asteroid could be similar, or related to, the parent body of these meteorites, if not the parent body itself. However, the apparent surface diversity of Lutetia pointed out in previous studies indicates that it could simultaneously be related to other types of chondrites. Future discovery of additional unweathered CH chondrites could provide deeper insight in the possible connection between this family of metal-rich carbonaceous chondrites and 21 Lutetia or other featureless, possibly hydrated high-albedo asteroids.

The fall of the Berduc meteorite took place on April 7, 2008, at 01 h 02 min 28 s ± 1 s UTC. A daylight fireball was witnessed by hundreds of people from Argentina and Uruguay, and also recorded by an infrasound array in Paraguay. From the available data, the fireball trajectory and radiant have been reconstructed with moderate accuracy. The modeled trajectory was tested to fit the infrasound and strewn field data. From the computed apparent radiant a = 87 ± 2°and d =)11 ± 2°and taking into account a range of plausible initial velocities, we obtained a range of orbital solutions. All of them suggest that the progenitor meteoroid originated from the main asteroid belt and followed an orbit of low inclination. Based on petrography, mineral chemistry, magnetic susceptibility, and bulk chemistry, the Berduc meteorite is classified as an L6 ordinary chondrite.

Fast development of CubeSat technology now enables the first interplanetary missions. The potential application of CubeSats to flyby near-Earth asteroids is explored in this paper in consideration of CubeSats' limited propulsive capabilities and systems constraints. Low-energy asteroid flyby trajectories are designed assuming a CubeSat is initially parked around to the Sun-Earth Lagrange points. High-impulse and low-thrust trajectories with realistic thrusting models are computed first in the Circular Restricted Three-Body Problem (CR3BP), and then in a high-fidelity ephemeris model. Analysis in the ephemeris model is used to confirm that trajectories computed in the CR3BP model also exist in a more realistic dynamical model, and to verify the validity of the results obtained in CR3BP analysis. A catalogue of asteroid flyby opportunities between years 2019 and 2030 is provided, with 80 m/s of available ΔV and departure from halo orbits around the first and second Sun-Earth Lagrange points (of similar size to those typically used by scientific missions). Results show that the CR3BP model can serve as an effective tool to identify reachable asteroids and can provide an initial estimation of the ΔV cost in the ephemeris model (with ±15 m/s accuracy). An impulsive maneuver model can also provide an accurate estimation of the ΔV requirement for a CubeSat equipped with a high-impulse thruster (with 4 m/s accuracy), even if its thrust magnitude is small and requires duty cycling; low-thrust ΔV requirements, however, may differ significantly from the impulsive results (±15 m/s).

Parigi un importante Congresso monotematico (negli anni passati il tema era un pianeta per anno). Recentemente ha curato la traduzione del Tetrabyblos dal greco in francese. È tra i soci fondatori dell'Agapè (Association Générale des Astrologues Psycho-professionnels Européens), dove insegna dal 1989. Martine Barbault (nipote di Armand e André Barbault) immersa nell'astrologia dalla più tenera età, ha seguito studi di psicologia e pubblicato numerose opere fra le quali "Il dizionario degli aspetti" e "I transiti in astrologia globale". Dal 1984 investiga sui legami esistenti fra numerologia ed astrologia. Dal 1991 è docente presso l'Agapè (Association Générale des Astrologues Psycho-professionnels Européens) Catherine Gestas, astrologa e psicoterapeuta, in possesso di un DESS in Scienze Umane, ha creato a Parigi un Centro formativo di astrologia, psicologia e genealogia. Applica terapie psicocorporali e tiene seminari di astropsicoanalisi e psicogenealogia in varie città francesi. Organizza con Yves Lenoble i congressi Sep Hermès. Denis Labouré, diplomato al "Modern Astro Studios" di Bangalore in India, è un grande esperto di astrologia indiana. Ha partecipato alla vacanzastudio di Creta e si è fatto apprezzare per la sua simpatia e chiarezza espositiva sull'Astrologia oraria e sulla visione filosofica dell'Astrologia. GERMANIA: Erich Van Slooten, olandese di nascita, italiano di… "adozione" avendo studiato a Firenze, vive a Monaco di Baviera. È un caro amico del Cida, assai noto ai nostri soci per i suoi numerosi seminari in italiano sull'Astrologia oraria. Coordina la sezione di astrologia antica della D.A.V., di cui è stato per molto tempo anche Vicepresidente. È autore di vari testi, pubblicati anche in italiano per le edizioni Mediterranee.

The aim of this paper is to study the capture of small Near Earth Objects (NEOs) into the Sun-Earth L2 using low-thrust propulsion for mining or science purposes. As it is well known, the vicinity of these points is inside a net of dynamical channels suitable for the transport in the Earth-Moon neighborhood, so different final destinations from here could be easily considered. Asteroids with very small mass and not representing a potential hazard are analyzed. An initial pruning of asteroids is made, considering NEOs with stellar magnitude bigger than 28, which are the smallest available, and NEOs close to the Earth orbit with semi-major axis between 0.85-1.15. Due to the difficult determination of their physical properties, two methods to estimate the asteroid masses are conducted. A procedure to find the low-thrust optimization trajectories has been implemented. The initial seed is obtained integrating forward the equations of motion plus its conjugated equations expressed in cartesian coordinates and applying the Pontryagins maximum principle to obtain the optimal control with a switching function for the thrust. To refine the trajectory a 4 order Runge-Kutta shooting method has been used. The objective function in this study is the fuel consumption. Finally, the capable asteroids to get captured by a low-thrust engine have been listed indicating the main parameters.

Em primeiro lugar, quero agradecer à minha família, em especial aos meus pais, que através de sacrifícios pessoais e profissionais possibilitaram o meu estudo nesta universidade e que me apoiaram economicamente durante todo o meu percurso académico. De seguida, quero dar um agradecimento especial ao meu orientador, Professor Doutor Luís Filipe Ferreira Marques Santos, por terme ajudado com qualquer problema e questão a qual quer altura do dia e do ano. Agradeço todo o conhecimento, conselhos, sugestões que me fac ultou desde o princípio. Agradeço também a prontidão e disponibilidade que demonstrou, a vários níveis, durante toda a realização do trabalho, quer nas simulações quer na escrita do relatório. Quero agradecer também ao Professor Doutor André Resende Rodrigues da Silva por todo o conhecimento que transmitiu e introspeção sobre assuntos específicos à engenharia ao longo dos semestres enquanto professor das várias unidades curriculares. Enquanto orientador agradeço a possibilidade de trabalhar num tema da dissertação que se enquadrasse com os meus gostos pessoais, e por todas as sugestões e respostas que me deu ao longo da elaboração do trabalho. Ao Professor Doutor Rui Melício, quero agradecer o interesse que demonstrou desde o início pelo trabalho. Agradeço também a divulgação do trabalho à qual se disponibilizou à partida, e ao envolvimento e apoio na continuação deste estudo. À Universidade da Beira Interior, ao departamento de Ciências Aeroespaciais e à cidade da Covilhã, agradeço o facto de me terem acolhido e permitido estudar no curso de Engenharia Aeronáutica ao longo destes anos, bem como possibilitarem todas as experiências académi cas e pessoais que lá vivenciei. Por último, mas não menos importante, agradeço aos meus amigos, quer de longa data, quer os que me acompanharam durante a minha jornada académica, o apoio e a amizade que disponibilizaram a vários níveis. iii Asteroids Deep Ocean Impact and the ShortTerm Consequences to the Portuguese Territory and Population Resumo O impacto de asteroides é uma ameaça global estabelecida. Cada local na Terra tem uma probabilidade de impacto de asteroides, à partida semelhante, que é limitada pelo conheci mento atual da humanidade. Como a superfície da Terra é maioritariamente água, um im pacto de asteroides na água é duas vezes mais provável do que um impacto no solo. Os im pactos no oceano estão naturalmente mais distantes das áreas povoadas, mas podem ainda representar uma ameaça significativa. Os impactos têm probabilidades baixas, mas consequências elevadas, tornandoos um con ceito difícil para o público, uma vez que tais acontecimentos não acontecem no dia a dia. Embora os impactos de asteroides tenham provado ser letais no passado, ainda é necessário aumentar a consciência pública para este perigo. A potencial devastação global obriga a me didas de mitigação que viriam naturalmente com a consciencialização. Nesta dissertação, foi assumido um impacto de asteroides no oceano e os efeitos imediatos do impacto foram avaliados para os municípios portugueses. A localização do impacto foi fixa num ponto médio entre Portugal Continental, e as ilhas dos Açores e da Madeira. Foi assumido que todos os asteroides impactariam a Terra com um ângulo de 45 graus. O es tudo abrange abalos sísmicos, ondas de pressão, depósito de ejeta, radiação térmica e ondas de tsunami; bem como as possíveis implicações globais na Terra, a perturbação da órbita, mudança no período de rotação, variação da inclinação do eixo, e perda de massa. Foram também estimadas as vulnerabilidades e fatalidades para cada município e cada efeito de impacto. Num impacto de asteroides no oceano, longe das regiões costeiras, o depósito de ejeta e o abalo sísmico são os efeitos menos significativos e podem ser ignorados. A radiação tér mica tem um curto alcance e pode ser desconsiderada para os asteroides menores. A onda de pressão é experienciada para os três impactos, mas os seus danos são, na sua maioria, estruturais. O tsunami é de longe a maior ameaça dum impacto de asteroides no oceano. Palavraschave Asteroides, impactos, efeitos de impacto, municípios, vulnerabilidades e fatalidades.

The purpose of this work is to illustrate the operational phases that allow to realize the curve of rotation of the Milky Way, to map the spiral structure of the Galaxy in the I and II quadrant with a thin division and to determine the integral mass; all this is done through the study of the galactic hydrogen concentration. The data are obtained by the radio telescope Salsa Onsala in Sweden and the spectra of the radiation are studied by the software SalsaJ.

El Sistema Solar, dentro de las muchas partes que lo componen, alberga en su mayoría asteroides de pequeño tamaño y poco estudio a profundidad, que dentro de su composición u órbitas, pueden revelar pistas sobre cómo es que nuestro entorno planetario se formó, o incluso la existencia de la vida en la Tierra. Basado en ello, el presente trabajo centra su mira en analizar alguno de los cuerpos independientes del cinturón de asteroides, con el fin de observarlo desde un centro astronómico, para luego recolectar imágenes y procesarlas. Debido a la coyuntura sanitaria actual, la toma de datos tuvo que realizarse por parte del equipo del Instituto Astronómico de la Academia Rumana, en su observatorio Berthelot. Es así, que haciendo uso de fotometría diferencial y el programa de uso libre AstroImageJ, se buscará obtener curvas de luz del objeto y entender sus características más importantes, relacionadas a la magnitud, periodo, etc. El trabajo a continuación intenta a su vez contribuir con...

We observed asteroid (596) Scheila and its ejecta cloud using the Swift UV-optical telescope. We obtained photometry of the nucleus and the ejecta, and for the first time measured the asteroid's reflection spectrum between 290 - 500 nm. Our measurements indicate significant reddening at UV wavelengths (13 per 1000 Å) and a possible broad, unidentified absorption feature around 380 nm. Our measurements indicate that the outburst has not permanently increased the asteroid's brightness. We did not detect any of the gases that are typically associated with either hypervolatile activity thought responsible for cometary outbursts (CO+, CO2+), or for any volatiles excavated with the dust (OH, NH, CN, C2, C3). We estimate that 6 x 10^8 kg of dust was released with a high ejection velocity of 57 m/s (assuming 1 μm sized particles). While the asteroid is red in color and the ejecta have the same color as the Sun, we suggest that the dust does not contain any ice. Based on our observat...

Introduction: Asteroid (596) Scheila is a middle size asteroid (about 115-120 km) having very dark surface with an albedo of 0.037 [1, 2]. It was classified as a PD-type object [3], that is rather rare type for main belt asteroids but typical for the Hilda group asteroids and Jupiter Trojans. Previous photometric observations of Scheila were carried out by Warner [4, 5] in 2006. Warner [4, 5] determined its rotation period (15.848 hours) and measured the magnitudephase slope in the range of phase angles from 7 to 16 deg. An interest to this asteroid highly increased after discovery by Larson [6] its cometary-like activity in December 2010. Several groups of observers [7, 8, 9] performed observations of this asteroid in 2010-2011. Obtained images showed a dust shell around asteroid, but spectrum in the visible and infrared range did not show cometary bands of СO, CO2 and/or others volatile substance. The authors [7, 8] assumed a collision of (596) Scheila with a small object of 30100...

Extraterrestres na Caixa D'Água é um texto de apoio primeiramente distribuído em versão mimeo em cursos em nível de pós-graduação sobre recursos hídricos e educação ambiental no Oeste Paulista, desenvolvidos no biênio 2014-2015 no transcorrer do segundo Pós-Doutoramento do autor (PNPD-CAPES). Uma versão sintética deste material foi publicada pelo jornal O Imparcial, de Presidente Prudente (SP), edição de Quinta-feira, 28-05-2015, Seção Opinião, página 3a (fac-símile disponível on line no link que segue: < http://mw.pro.br/mw/MA_ColunaPR_Imparcial15.pdf >). A presente edição eletrônica de  Extraterrestres na Caixa D'Água foi masterizada em Junho de 2019 pela Editora Kotev (Kotev ©), para fins de acesso livre na Internet, sendo levemente ampliada e também, incorporando três imagens. O texto de Extraterrestres na Caixa D'Água incorpora revisão ortográfica com base nas regras vigentes quanto à norma culta da língua portuguesa, cautelas de estilo, repaginação standard e normatizações editoriais inerentes ao formato PDF, também permitindo consulta em aparelhos celulares. Retenha-se que Extraterrestres na Caixa D'Água é um material gratuito, sendo vedada qualquer forma de reprodução comercial e igualmente, de divulgação sem aprovação prévia da Editora Kotev. A citação de Extraterrestres na Caixa D'Água deve obrigatoriamente incorporar referências ao autor, texto e apensos editoriais conforme padrão modelar que segue: WALDMAN, Maurício. Extraterrestres na Caixa D'Água. Série Recursos Hídricos Nº. 10. São Paulo (SP): Editora Kotev. 2018.

For decades the evolutionary biology has made efforts to understand the meaning of "species" and explain the training process. Currently, there are over twenty different concepts of species. The use of different concepts leads to improper and misleading comparisons. On the other hand, catastrophic biologists for decades used the term "type" or "group" for what they consider categories of organisms not genetically related. Thus, each of the various categories of species, subspecies and varieties seen today were designed to diversify a basic common ancestor type. Morphological patterns around the genus taxon was identified with ancestral fossils buried in a catastrophic recent basic; this model tells us a story of a period of: 1) rapid speciation, 2) stay with high number of species in a stable environment (fossil replay without environmental evolutionary pressures), 3) disaster followed by massive burial of population alive evidenced by the repetition of the same fossil species (which detracts punctuality), 4) presence of several different species together in the fossil record, lots of vertebrate fossils (which features disaster of great magnitude and high rates of sedimentation), and 5) drastic environmental changes causing radiation of species in samples of recent layers and in millions of species in the current biodiversity.

In this paper we present results from photometric observations of (596) Scheila during its recent outburst. This one was the first time to observe the main-belt comet or a possible collision of two asteroids at the Skalnaté Pleso Observatory. The main aim of our observations was to determine whether and, if so, how much the rotational period and the amplitude were changed by the outburst or collision with respect to the published results by Warner in 2006.

Twenty-three solar system minor bodies were measured photometrically between 2005 February and 2011 July using robotic telescopes in North America, Europe, and Australia. From the data obtained we determine for these objects their basic physical proprieties, such as Johnson-Cousins BVRI colors, H-G parameters, diameters, and a Tholen taxonomic classification. We found that 70% of our near-Earth asteroid sample belong to S-, Q-, X-, and C-complexes; 2009 BH81 may be a candidate to a new A type asteroid; 2010 RF12 is an S-type and it has absolute magnitude H = 28.46 ± 0.05, G = 0.31 ± 0.06 and D = 6 ± 1 m; the possible dust envelope around (596)Scheila and P/2010 A2 have similar colors.