2004
Journal article
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BeppoSAX equatorial uncontrolled re-entry
Portelli C., Salotti L., Anselmo L., Lips T., Tramutola A.
The X-ray astronomy satellite BeppoSAX (Satellite per Astronomia X, ''Beppo'' in honor of Giuseppe Occhialini), is a project of the Italian Space Agency (ASI) with the participation of the Netherlands Agency for Aerospace Programs (NIVR). BeppoSAX was launched by an Atlas G-Centaur directly into a circular 600 km orbit at 3.9 inclination on April 30, 1996. The satellite is a three axis stabilized spacecraft with a total mass of about 1400 kg and main dimensions in flight configuration of about 2450 mm 8980 mm 3650 mm. The current (September 21, 2002) flight altitude is about 435 km and its uncontrolled re-entry is predicted late in 2002, or in 2003, with 26 kg of hydrazine on board that could not be vented or used for controlled re-entry due to the gyro package total failure. Due to the relatively high mass of BeppoSAX, it must be expected that parts of the satellite will survive the re-entry into the Earth atmosphere. The Italian Space Agency has committed a study to analyse of the destructive phase of the uncontrolled atmospheric re-entry by means of a dedicated European software tool (SCARAB). The expected outputs will be used in order to determine how much of the spacecraft and how many fragments of it will reach the ground on the equatorial earth zone. This paper will address the peculiarities of the spacecrafts initial status, its risks at end of life, and the SCARAB modeling as well as its six dimension flight dynamics re-entry analysis results also in terms of the destruction history tree. Consideration will be made of the ground dispersion and casualty area due to the very restricted equatorial zone impacted.Source: Advances in space research 34 (2004): 1029–1037. doi:10.1016/j.asr.2003.11.011
DOI: 10.1016/j.asr.2003.11.011
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Portelli C., Salotti L., Anselmo L., Lips T., Tramutola A.
The X-ray astronomy satellite BeppoSAX (Satellite per Astronomia X, ''Beppo'' in honor of Giuseppe Occhialini), is a project of the Italian Space Agency (ASI) with the participation of the Netherlands Agency for Aerospace Programs (NIVR). BeppoSAX was launched by an Atlas G-Centaur directly into a circular 600 km orbit at 3.9 inclination on April 30, 1996. The satellite is a three axis stabilized spacecraft with a total mass of about 1400 kg and main dimensions in flight configuration of about 2450 mm 8980 mm 3650 mm. The current (September 21, 2002) flight altitude is about 435 km and its uncontrolled re-entry is predicted late in 2002, or in 2003, with 26 kg of hydrazine on board that could not be vented or used for controlled re-entry due to the gyro package total failure. Due to the relatively high mass of BeppoSAX, it must be expected that parts of the satellite will survive the re-entry into the Earth atmosphere. The Italian Space Agency has committed a study to analyse of the destructive phase of the uncontrolled atmospheric re-entry by means of a dedicated European software tool (SCARAB). The expected outputs will be used in order to determine how much of the spacecraft and how many fragments of it will reach the ground on the equatorial earth zone. This paper will address the peculiarities of the spacecrafts initial status, its risks at end of life, and the SCARAB modeling as well as its six dimension flight dynamics re-entry analysis results also in terms of the destruction history tree. Consideration will be made of the ground dispersion and casualty area due to the very restricted equatorial zone impacted.Source: Advances in space research 34 (2004): 1029–1037. doi:10.1016/j.asr.2003.11.011
DOI: 10.1016/j.asr.2003.11.011
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Advances in Space Research 
| CNR ExploRA
2004
Journal article
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The european space debris safety and mitigation standard
Alby F., Alwes D., Anselmo L., Baccini H., Bonnal C., Crowther R., Flury W., Jehn R., Klinkrad H., Portelli C., Tremayne-Smith R.
To tackle the space debris problem, members from ASI, BNSC, CNES, DLR and ESA set up a European Debris Mitigation Standard Working Group (EDMSWG). They propose a draft standard as one of the series of ECSS Standards intended to be applied for the management, engineering and product assurance in space projects and applications. The requirements in the draft standard are defined in terms of what must be accomplished, rather than in terms of how to organise and perform the necessary work. This allows existing organisational structures and methods within agencies and industry to be applied where they are effective, and for such structures and methods to evolve as necessary, without the need for rewriting the standards. The draft standard, which comprises management requirements, design requirements and operational requirements, is currently in the process of being introduced as a standard into ECSS.Source: Advances in space research 34 (2004): 1260–1263. doi:10.1016/j.asr.2003.08.043
DOI: 10.1016/j.asr.2003.08.043
Metrics:
Alby F., Alwes D., Anselmo L., Baccini H., Bonnal C., Crowther R., Flury W., Jehn R., Klinkrad H., Portelli C., Tremayne-Smith R.
To tackle the space debris problem, members from ASI, BNSC, CNES, DLR and ESA set up a European Debris Mitigation Standard Working Group (EDMSWG). They propose a draft standard as one of the series of ECSS Standards intended to be applied for the management, engineering and product assurance in space projects and applications. The requirements in the draft standard are defined in terms of what must be accomplished, rather than in terms of how to organise and perform the necessary work. This allows existing organisational structures and methods within agencies and industry to be applied where they are effective, and for such structures and methods to evolve as necessary, without the need for rewriting the standards. The draft standard, which comprises management requirements, design requirements and operational requirements, is currently in the process of being introduced as a standard into ECSS.Source: Advances in space research 34 (2004): 1260–1263. doi:10.1016/j.asr.2003.08.043
DOI: 10.1016/j.asr.2003.08.043
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Advances in Space Research | www.scopus.com | CNR ExploRA
2006
Journal article
Unknown
Guest editorial - Small Bodies in the Solar System
Worms J., Jorda L., Anselmo L.
Thematic Issue of Advances in Space Research, Commission B of COSPAR.Source: Advances in space research 38 (2006): 1903–2138.
Worms J., Jorda L., Anselmo L.
Thematic Issue of Advances in Space Research, Commission B of COSPAR.Source: Advances in space research 38 (2006): 1903–2138.
See at: CNR ExploRA
2005
Journal article
Unknown
Preface to Space Debris - Thematic Issue of Advances in Space Research.
Anselmo L.
During the past 15 years, apart from specific workshops, the IADC plenary meetings and the European Conferences on Space Debris organized at the ESA's European Space Operations Centre (ESOC), the main international forums for the presentation and discussion of current scientific and technical research concerning space debris have been the International Astronautical Congresses and the COSPAR Scientific Assemblies. The 35th COSPAR Scientific Assembly, held in Paris on 1825 July 2004, was not an exception, with a very fruitful and interesting scientific meeting (PEDAS1/ B1.6 Space Debris), organized by Walter Flury (Main Scientific Organizer) and Nicholas L. Johnson (Deputy Organizer). Sponsored by the European Space Agency (ESA), the International Academy of Astronautics (IAA), the International Astronautical Federation (IAF), the International Astronomical Union (IAU) and the United Nations Office for Outer Space Affairs, the scientific meeting on ''Space Debris'', held on 2224 July 2004, consisted of five sessions, four devoted to oral presentations and one to posters, chaired by T. Donath, P.W. Kervin, G. Drolshagen, J.-C. Mandeville, F. Alby, F. Schaefer, L. Anselmo, P. Anz-Meador and R. Jehn. Of a total of 39 oral presentations and 10 posters accepted in the final program, 37 oral presentations (including 12 solicited contributions) and five posters were actually presented at the meeting.Source: Advances in space research 35 (2005): 1195–1196.
Anselmo L.
During the past 15 years, apart from specific workshops, the IADC plenary meetings and the European Conferences on Space Debris organized at the ESA's European Space Operations Centre (ESOC), the main international forums for the presentation and discussion of current scientific and technical research concerning space debris have been the International Astronautical Congresses and the COSPAR Scientific Assemblies. The 35th COSPAR Scientific Assembly, held in Paris on 1825 July 2004, was not an exception, with a very fruitful and interesting scientific meeting (PEDAS1/ B1.6 Space Debris), organized by Walter Flury (Main Scientific Organizer) and Nicholas L. Johnson (Deputy Organizer). Sponsored by the European Space Agency (ESA), the International Academy of Astronautics (IAA), the International Astronautical Federation (IAF), the International Astronomical Union (IAU) and the United Nations Office for Outer Space Affairs, the scientific meeting on ''Space Debris'', held on 2224 July 2004, consisted of five sessions, four devoted to oral presentations and one to posters, chaired by T. Donath, P.W. Kervin, G. Drolshagen, J.-C. Mandeville, F. Alby, F. Schaefer, L. Anselmo, P. Anz-Meador and R. Jehn. Of a total of 39 oral presentations and 10 posters accepted in the final program, 37 oral presentations (including 12 solicited contributions) and five posters were actually presented at the meeting.Source: Advances in space research 35 (2005): 1195–1196.
See at: CNR ExploRA
2008
Journal article
Restricted
Analytical and semi-analytical investigations of geosynchronous space debris with high area-to-mass ratios
Valk S., Lemaitre A., Anselmo L.
This paper provides a Hamiltonian formulation of the averaged equations of motion with respect to short periods (1 day) of a space debris subjected to direct solar radiation pressure and orbiting near the geostationary ring. This theory is based on a semi-analytical theory of order 1 regarding the averaging process, formulated using canonical and non-singular elements for eccentricity and inclination. The analysis is based on an expansion in powers of the eccentricity and of the inclination, truncated at an arbitrary high order. First, the dynamical evolution of space debris released near the geostationary ring, with area-to-mass ratios as high as 40 m2/kg is analyzed within the framework of mid-term evolution (1 year) as well as long-term evolution (several decades). This study is carried out, using both simplified analytical models to clarify some properties, as well as our complete semi-analytical theory which leads to an accurate understanding of the mid-term and long-term evolution of the eccentricity and of the inclination. We also analyzed the coupling equations between the eccentricity and the inclination, considering a doubly averaged analytical model. Second, we also focused our attention on the comparison of various direct radiation pressure approximations in order to assess their consequences. Last, this paper claims to be the continuation and the counterpart of previous papers dealing with geosynchronous orbits and radiation pressure, that is [Anselmo, L., Pardini, C. Orbital evolution of geosynchronous objects with high area-to-mass ratios. In: Danesy, D. (Ed.), Proceedings of the Fourth European Conference on Space Debris, ESA SP-587. ESA Publications Division, Noordwijk, The Netherlands, pp. 279-284, 2005] and [Valk, S., Lemaitre, A., Deleflie, F. Semi-analytical theory of mean orbital motion for geosynchronous space debris under gravitational influence, Advances in Space Research, submitted for publication].Source: Advances in space research 41 (2008): 1077–1090. doi:10.1016/j.asr.2007.10.025
DOI: 10.1016/j.asr.2007.10.025
Metrics:
Valk S., Lemaitre A., Anselmo L.
This paper provides a Hamiltonian formulation of the averaged equations of motion with respect to short periods (1 day) of a space debris subjected to direct solar radiation pressure and orbiting near the geostationary ring. This theory is based on a semi-analytical theory of order 1 regarding the averaging process, formulated using canonical and non-singular elements for eccentricity and inclination. The analysis is based on an expansion in powers of the eccentricity and of the inclination, truncated at an arbitrary high order. First, the dynamical evolution of space debris released near the geostationary ring, with area-to-mass ratios as high as 40 m2/kg is analyzed within the framework of mid-term evolution (1 year) as well as long-term evolution (several decades). This study is carried out, using both simplified analytical models to clarify some properties, as well as our complete semi-analytical theory which leads to an accurate understanding of the mid-term and long-term evolution of the eccentricity and of the inclination. We also analyzed the coupling equations between the eccentricity and the inclination, considering a doubly averaged analytical model. Second, we also focused our attention on the comparison of various direct radiation pressure approximations in order to assess their consequences. Last, this paper claims to be the continuation and the counterpart of previous papers dealing with geosynchronous orbits and radiation pressure, that is [Anselmo, L., Pardini, C. Orbital evolution of geosynchronous objects with high area-to-mass ratios. In: Danesy, D. (Ed.), Proceedings of the Fourth European Conference on Space Debris, ESA SP-587. ESA Publications Division, Noordwijk, The Netherlands, pp. 279-284, 2005] and [Valk, S., Lemaitre, A., Deleflie, F. Semi-analytical theory of mean orbital motion for geosynchronous space debris under gravitational influence, Advances in Space Research, submitted for publication].Source: Advances in space research 41 (2008): 1077–1090. doi:10.1016/j.asr.2007.10.025
DOI: 10.1016/j.asr.2007.10.025
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Advances in Space Research | CNR ExploRA
2008
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Foreword - Space debris
Anselmo L.
While the world was celebrating 50 years of space activity, the United Nations' Committee on the Peaceful Uses of Outer Space (COPUOS) approved, during the 6-15 June 2007 session, a set of space debris mitigation guidelines, formally endorsed by the General Assembly on 14 November 2007 (A/RES/62/217, issued on 10 January 2008). Derived from the Space Debris Mitigation Guidelines, issued in 2002 by the Inter-Agency Space Debris Coordination Committee (IADC), the COPUOS guidelines consist of a set of seven high level mitigation principles covering space system design, launch, operation and disposal. This testifies to the growing relevance of space debris outside the relatively small number of engineers and scientists directly involved in research. The circumterrestrial space is, in fact, a very precious environment of great scientific, economic and strategic importance. All reasonable efforts must be made to preserve it for future generations and appropriate strategies should be devised, developed and implemented to minimize the impact of space debris on future space missions. Several significant results have been obtained in recent years, but a lot remains to be done in terms of enhanced observations, in situ measurements, environment and impact modeling, protection and implementation of affordable mitigation practices.Source: Oxford: Elsevier Ltd, 2008
DOI: 10.1016/j.asr.2008.02.013
Metrics:
Anselmo L.
While the world was celebrating 50 years of space activity, the United Nations' Committee on the Peaceful Uses of Outer Space (COPUOS) approved, during the 6-15 June 2007 session, a set of space debris mitigation guidelines, formally endorsed by the General Assembly on 14 November 2007 (A/RES/62/217, issued on 10 January 2008). Derived from the Space Debris Mitigation Guidelines, issued in 2002 by the Inter-Agency Space Debris Coordination Committee (IADC), the COPUOS guidelines consist of a set of seven high level mitigation principles covering space system design, launch, operation and disposal. This testifies to the growing relevance of space debris outside the relatively small number of engineers and scientists directly involved in research. The circumterrestrial space is, in fact, a very precious environment of great scientific, economic and strategic importance. All reasonable efforts must be made to preserve it for future generations and appropriate strategies should be devised, developed and implemented to minimize the impact of space debris on future space missions. Several significant results have been obtained in recent years, but a lot remains to be done in terms of enhanced observations, in situ measurements, environment and impact modeling, protection and implementation of affordable mitigation practices.Source: Oxford: Elsevier Ltd, 2008
DOI: 10.1016/j.asr.2008.02.013
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2009
Journal article
Open Access
"Galileo Galilei" (GG) a small satellite to test the equivalence principle of Galileo, Newton and Einstein
Nobili A. M., Comandi G. L., Doravari S., Bramanti D. Kumar R., Maccarrone F., Polacco E., Turyshev S. G., Shao M., Lipa J., Dittus H., Laemmerzhal C., Peters A., Mueller J., Unnikrishnan C. S., Roxburgh I. W., Brillet A., Marchal C., Luo J., Van Der Ha J., Milyukov V., Iafolla V., Lucchesi D., Tortora P., De Bernardis P., Palmonari P., Focardi S., Zanello D., Monaco S., Mengali G., Anselmo L., Iorio L., Knezevic Z.
"Galileo Galilei" (GG) is a small satellite designed to fly in low Earth orbit with the goal of testing the Equivalence Principle-which is at the basis of the General Theory of Relativity-to 1 part in 1017. If successful, it would improve current laboratory results by 4 orders of magnitude. A confirmation would strongly constrain theories; proof of violation is believed to lead to a scientific revolution. The experiment design allows it to be carried out at ambient temperature inside a small 1-axis stabilized satellite (250 kg total mass). GG is under investigation at Phase A-2 level by ASI (Agenzia Spaziale Italiana) at Thales Alenia Space in Torino, while a laboratory prototype (known as GGG) is operational at INFN laboratories in Pisa, supported by INFN (Istituto Nazionale di fisica Nucleare) and ASI. A final study report will be published in 2009.Source: Experimental astronomy (Print) 23 (2009): 689–710. doi:10.1007/s10686-008-9128-3
DOI: 10.1007/s10686-008-9128-3
Metrics:
Nobili A. M., Comandi G. L., Doravari S., Bramanti D. Kumar R., Maccarrone F., Polacco E., Turyshev S. G., Shao M., Lipa J., Dittus H., Laemmerzhal C., Peters A., Mueller J., Unnikrishnan C. S., Roxburgh I. W., Brillet A., Marchal C., Luo J., Van Der Ha J., Milyukov V., Iafolla V., Lucchesi D., Tortora P., De Bernardis P., Palmonari P., Focardi S., Zanello D., Monaco S., Mengali G., Anselmo L., Iorio L., Knezevic Z.
"Galileo Galilei" (GG) is a small satellite designed to fly in low Earth orbit with the goal of testing the Equivalence Principle-which is at the basis of the General Theory of Relativity-to 1 part in 1017. If successful, it would improve current laboratory results by 4 orders of magnitude. A confirmation would strongly constrain theories; proof of violation is believed to lead to a scientific revolution. The experiment design allows it to be carried out at ambient temperature inside a small 1-axis stabilized satellite (250 kg total mass). GG is under investigation at Phase A-2 level by ASI (Agenzia Spaziale Italiana) at Thales Alenia Space in Torino, while a laboratory prototype (known as GGG) is operational at INFN laboratories in Pisa, supported by INFN (Istituto Nazionale di fisica Nucleare) and ASI. A final study report will be published in 2009.Source: Experimental astronomy (Print) 23 (2009): 689–710. doi:10.1007/s10686-008-9128-3
DOI: 10.1007/s10686-008-9128-3
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Experimental Astronomy 
| Experimental Astronomy | Archivio istituzionale della ricerca - Alma Mater Studiorum Università di Bologna | www.springerlink.com | CNR ExploRA
2010
Journal article
Restricted
Impact risk analysis for a spacecraft in Cosmo-Skymed orbit
Giacomuzzo C., Francesconi A., Anselmo L.
This paper presents a case study of Micrometeoroids and Orbital Debris risk assessment for a spacecraft flying in an orbit close to that of the Italian Cosmo-Skymed constellation. The aim of the analysis was to calculate the failure flux impinging on the satellite external shell, taking into account both geometry and materials of satellite surfaces. Furthermore the analysis included the evaluation of the contribution to debris population at the selected orbit of the fragments produced by a Chinese Anti-SATellite experiment, which caused the catastrophic break-up of the satellite Fengyun 1C in January 2007. A first computation was carried out using ESABASE2/Debris v.1.4.2. This software made it possible to perform geometrical analysis of a satellite subjected to a given debris environment, but the most up to date available models, ORDEM2000 and MASTER2001, gave significantly different results. An independent procedure for risk assessment analysis was implemented to further analyse such issue and to provide damage equation adequate to represent the behaviour of the selected structural aluminium honeycomb sandwich panels covered by Multi-Layer Insulation. Debris fluxes were calculated applying MASTER2005 and ORDEM2000 environment models, then results were compared to those of ESABASE2. Failure fluxes were calculated implementing special damage equations for honeycomb structures available from the open technical literature. The expected flux contribution of catalogued debris from the Chinese Anti-SATellite (ASAT) experiment was estimated independently using the code SDIRAT (Space Debris Impact Risk Analysis Tool) developed at the Institute of Information Science and Technologies (ISTI).Source: Advances in space research 46 (2010): 846–858. doi:10.1016/j.asr.2010.04.018
DOI: 10.1016/j.asr.2010.04.018
Metrics:
Giacomuzzo C., Francesconi A., Anselmo L.
This paper presents a case study of Micrometeoroids and Orbital Debris risk assessment for a spacecraft flying in an orbit close to that of the Italian Cosmo-Skymed constellation. The aim of the analysis was to calculate the failure flux impinging on the satellite external shell, taking into account both geometry and materials of satellite surfaces. Furthermore the analysis included the evaluation of the contribution to debris population at the selected orbit of the fragments produced by a Chinese Anti-SATellite experiment, which caused the catastrophic break-up of the satellite Fengyun 1C in January 2007. A first computation was carried out using ESABASE2/Debris v.1.4.2. This software made it possible to perform geometrical analysis of a satellite subjected to a given debris environment, but the most up to date available models, ORDEM2000 and MASTER2001, gave significantly different results. An independent procedure for risk assessment analysis was implemented to further analyse such issue and to provide damage equation adequate to represent the behaviour of the selected structural aluminium honeycomb sandwich panels covered by Multi-Layer Insulation. Debris fluxes were calculated applying MASTER2005 and ORDEM2000 environment models, then results were compared to those of ESABASE2. Failure fluxes were calculated implementing special damage equations for honeycomb structures available from the open technical literature. The expected flux contribution of catalogued debris from the Chinese Anti-SATellite (ASAT) experiment was estimated independently using the code SDIRAT (Space Debris Impact Risk Analysis Tool) developed at the Institute of Information Science and Technologies (ISTI).Source: Advances in space research 46 (2010): 846–858. doi:10.1016/j.asr.2010.04.018
DOI: 10.1016/j.asr.2010.04.018
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Advances in Space Research | www.sciencedirect.com | CNR ExploRA
2002
Journal article
Unknown
Chi non muore si rivede: la natura di J002E3
Anselmo L.
No abstract avaibleSource: L'Astronomia (Milano, 1987) 237 (2002): 16–18.
Anselmo L.
No abstract avaibleSource: L'Astronomia (Milano, 1987) 237 (2002): 16–18.
See at: CNR ExploRA
2004
Journal article
Unknown
Mars express in orbita marziana, perso il Beagle 2
Anselmo L.
Description of the first European missions for the exploration of MarsSource: L'Astronomia (Milano, 1987) 25 (2004): 10–11.
Anselmo L.
Description of the first European missions for the exploration of MarsSource: L'Astronomia (Milano, 1987) 25 (2004): 10–11.
See at: CNR ExploRA
2004
Journal article
Unknown
Opportunity e la saga dell'acqua su Marte
Anselmo L.
Comments to the discovery of a wet past on MarsSource: L'Astronomia (Milano, 1987) 26 (2004): 16–17.
Anselmo L.
Comments to the discovery of a wet past on MarsSource: L'Astronomia (Milano, 1987) 26 (2004): 16–17.
See at: CNR ExploRA
2004
Journal article
Unknown
Il nuovo programma spaziale di Bush: lezioni del passato e prospettive future
Anselmo L.
Comments to the Space Exploration Program proposed by President G.W. Bush in January 2004Source: L'Astronomia (Milano, 1987) 26 (2004): 54–56.
Anselmo L.
Comments to the Space Exploration Program proposed by President G.W. Bush in January 2004Source: L'Astronomia (Milano, 1987) 26 (2004): 54–56.
See at: CNR ExploRA
2004
Journal article
Unknown
Stardust e Spirit: la NASA inaugura con successo il 2004
Anselmo L.
Description of the NASA's missions STARDUST and SPIRIT.Source: L'Astronomia (Milano, 1987) 25 (2004): 6–9.
Anselmo L.
Description of the NASA's missions STARDUST and SPIRIT.Source: L'Astronomia (Milano, 1987) 25 (2004): 6–9.
See at: CNR ExploRA
2005
Journal article
Unknown
Cassini-huygens: l'ora della verità
Anselmo L.
Description of the Cassini Orbiter and Huygens Probe missions in the Saturn system.Source: Le Stelle (Roma, 2002) 4-25 (2005): 30–45.
Anselmo L.
Description of the Cassini Orbiter and Huygens Probe missions in the Saturn system.Source: Le Stelle (Roma, 2002) 4-25 (2005): 30–45.
See at: CNR ExploRA
2001
Journal article
Unknown
Venere: il gemello mancato
Anselmo L.
Descrizione del pianeta Venere sulla base delle osservazioni della sonda Magellan lanciata dalla Terra il 4 Maggio 1989Source: L'Astronomia (Milano, 1987) 23 (2001): 18–35.
Anselmo L.
Descrizione del pianeta Venere sulla base delle osservazioni della sonda Magellan lanciata dalla Terra il 4 Maggio 1989Source: L'Astronomia (Milano, 1987) 23 (2001): 18–35.
See at: CNR ExploRA
2003
Conference article
Unknown
A European Standard for Space Debris
Alby F., Alwes D., Anselmo L., Baccini H., Bonnal C., Crowther R., Flury W., Rudiger J., Klinkrad H., Portelli C., Tremayne-Smith R.
Considering the need to take preventive measures to limit the production of debris in space, five European Agencies (ASI, BNSC, CNES, DLR and ESA) have set up a working group called EDMSWG (European Debris Mitigation Standard Working Group) with the objective to prepare the European standard on space debris. The requirements in the Standard are defined in terms of what must be accomplished, rather than in terms of how to organise and perform the necessary work. This allows existing organisational structures and methods within agencies and industry to be applied where they are effective, and for such structures and methods to evolve as necessary, without the need for rewriting the standards. The Standard comprises management requirements, design requirements and operational requirements. The main requirements are relative to the limitation of debris production during the operational lifetime and to end of life practices to ensure the protection of useful regions.Source: Europe and Space Debris, pp. 1–6, Toulouse, 27-28 November 2002
Alby F., Alwes D., Anselmo L., Baccini H., Bonnal C., Crowther R., Flury W., Rudiger J., Klinkrad H., Portelli C., Tremayne-Smith R.
Considering the need to take preventive measures to limit the production of debris in space, five European Agencies (ASI, BNSC, CNES, DLR and ESA) have set up a working group called EDMSWG (European Debris Mitigation Standard Working Group) with the objective to prepare the European standard on space debris. The requirements in the Standard are defined in terms of what must be accomplished, rather than in terms of how to organise and perform the necessary work. This allows existing organisational structures and methods within agencies and industry to be applied where they are effective, and for such structures and methods to evolve as necessary, without the need for rewriting the standards. The Standard comprises management requirements, design requirements and operational requirements. The main requirements are relative to the limitation of debris production during the operational lifetime and to end of life practices to ensure the protection of useful regions.Source: Europe and Space Debris, pp. 1–6, Toulouse, 27-28 November 2002
See at: CNR ExploRA
2004
Conference article
Unknown
Inaugural address. opening plenary session
Anselmo L.
Inaugural Address at the Opening Plenary Session of the 22nd Plenary Meeting of the Inter-Agency Space Debris Coordination Committee.Source: 22nd Plenary Meeting of the Inter-Agency Space Debris Coordination Committee (IADC), Teatro Congressi 'Pietro d'Abano', Abano Terme (PD), Italy, 19-22 April 2004
Anselmo L.
Inaugural Address at the Opening Plenary Session of the 22nd Plenary Meeting of the Inter-Agency Space Debris Coordination Committee.Source: 22nd Plenary Meeting of the Inter-Agency Space Debris Coordination Committee (IADC), Teatro Congressi 'Pietro d'Abano', Abano Terme (PD), Italy, 19-22 April 2004
See at: CNR ExploRA
2001
Conference article
Unknown
EDOARD: an electrodynamic tether device for efficient spacecraft de-orbiting
Bruno C., Anselmo L., Bussolino L., Cioeta M., Iess L., Licata R., Marchetti M., Schirone L., Somensi L., Ulivieri C.
EDOARD (Electrodynamic De-Orbiting And Re-entry Device) exploits the basic concepts of electrodynamic drag on conductive tethers to de-boost LEO spacecraft efficiently and reliably. The system is jointly developed by Alenia Spazio and by University "La Sapienza" in view of potential commercial exploitation. An innovative engineering approach has tackled four critical issues: 1) the deployment mechanism, which ensures a purely passive extension of the tether under extremely small gravity gradients; 2) the tether structure and configuration, which guarantees a very high survivability to impacts from artificial and natural debris; 3) the inflatable passive electron collector, which increases the efficiency of the system while reducing the tether length to 4-5 km and 4) the electrodynamic control of the tether librations, which limits the effects of inherent dynamical system instability, while preserving high de-orbiting efficiencies. The configuration ensures de-orbiting times per unit mass of about 0.09 day/kg from a circular, 1500 km altitude, 55 degree inclination.Source: Third European Conference on Space Debris - ESA/ESOC, pp. 707–712, Darmstadt (D), March 2001
Bruno C., Anselmo L., Bussolino L., Cioeta M., Iess L., Licata R., Marchetti M., Schirone L., Somensi L., Ulivieri C.
EDOARD (Electrodynamic De-Orbiting And Re-entry Device) exploits the basic concepts of electrodynamic drag on conductive tethers to de-boost LEO spacecraft efficiently and reliably. The system is jointly developed by Alenia Spazio and by University "La Sapienza" in view of potential commercial exploitation. An innovative engineering approach has tackled four critical issues: 1) the deployment mechanism, which ensures a purely passive extension of the tether under extremely small gravity gradients; 2) the tether structure and configuration, which guarantees a very high survivability to impacts from artificial and natural debris; 3) the inflatable passive electron collector, which increases the efficiency of the system while reducing the tether length to 4-5 km and 4) the electrodynamic control of the tether librations, which limits the effects of inherent dynamical system instability, while preserving high de-orbiting efficiencies. The configuration ensures de-orbiting times per unit mass of about 0.09 day/kg from a circular, 1500 km altitude, 55 degree inclination.Source: Third European Conference on Space Debris - ESA/ESOC, pp. 707–712, Darmstadt (D), March 2001
See at: CNR ExploRA
2001
Conference article
Unknown
The European space debris safety and mitigation standard
Alby F., Alwes D., Anselmo L., Baccini H., Bonnal C., Crowther R., Flury W., Klinkrad H., Portelli C., Tremayne-Smith R.
A standard has been proposed as one of the series of ECSS Standards intended to be applied together for the management, engineering and product assurance in space projects and applications. The requirements in the Standard are defined in terms of what must be accomplished, rather than in terms of how to organise and perform the necessary work. This allows existing organisational structures and methods within agencies and industry to be applied where they are effective, and for such structures and methods to evolve as necessary, without the need for rewriting the standards. The Standard comprises management requirements, design requirements and operational requirements. The standard was prepared by the European Debris Mitigation Standard Working Group (EDMSWG) involving members from ASI, BNSC, CNES, DLR and ESA.Source: Third European conference on space debris - ESA/ESOC, pp. 817–820, Darmstadt (D), 19-21 March 2001
Alby F., Alwes D., Anselmo L., Baccini H., Bonnal C., Crowther R., Flury W., Klinkrad H., Portelli C., Tremayne-Smith R.
A standard has been proposed as one of the series of ECSS Standards intended to be applied together for the management, engineering and product assurance in space projects and applications. The requirements in the Standard are defined in terms of what must be accomplished, rather than in terms of how to organise and perform the necessary work. This allows existing organisational structures and methods within agencies and industry to be applied where they are effective, and for such structures and methods to evolve as necessary, without the need for rewriting the standards. The Standard comprises management requirements, design requirements and operational requirements. The standard was prepared by the European Debris Mitigation Standard Working Group (EDMSWG) involving members from ASI, BNSC, CNES, DLR and ESA.Source: Third European conference on space debris - ESA/ESOC, pp. 817–820, Darmstadt (D), 19-21 March 2001
See at: CNR ExploRA
2001
Conference article
Unknown
The long-term evolution of the space debris environment
Anselmo L.
A review of the problem of the long-term uncontrolled growth of man-made objects in earth orbit is presented. After a discussion of the main underlying concepts, the relative effectiveness of the adoption of some mitigation measures over 100 - 200 years is analysed, including the minimisation of mission related objects release, the on-orbit explosion avoidance and the de-orbiting of spacecraft and upper stages in low earth orbit. It is shown that only the implementation of the full set of mitigation measures discussed would be able to guarantee the long-term approximate stabilisation of the population of large objects, maintaining at acceptable levels the growth of millimetre and centimetre sized debris.Source: Third European Conference on Space Debris - ESA/ESOC, pp. 333–340, Darmstadt, Germany, 1 October 2001
Anselmo L.
A review of the problem of the long-term uncontrolled growth of man-made objects in earth orbit is presented. After a discussion of the main underlying concepts, the relative effectiveness of the adoption of some mitigation measures over 100 - 200 years is analysed, including the minimisation of mission related objects release, the on-orbit explosion avoidance and the de-orbiting of spacecraft and upper stages in low earth orbit. It is shown that only the implementation of the full set of mitigation measures discussed would be able to guarantee the long-term approximate stabilisation of the population of large objects, maintaining at acceptable levels the growth of millimetre and centimetre sized debris.Source: Third European Conference on Space Debris - ESA/ESOC, pp. 333–340, Darmstadt, Germany, 1 October 2001
See at: CNR ExploRA