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2005
Journal article
Restricted
Survey of past on-orbit fragmentation events
Pardini C
Following the first on-orbit fragmentation, the explosion of the Transit 4A rocket body on June 29 1961, 165 breakups were recorded up until August 31 2001. So far, only three collisional breakups have been reasonably confirmed, while the remaining 162 fragmentations resulted from explosions. The aim of this paper is to assess the contribution of these on orbit fragmentation events to the cataloged and undetected orbital debris population. To do this, the largest pieces of fragmentation debris were extracted by the U.S. Space Command catalog of August 31 2001, and subsequently assembled for families or single events, then counted and graphically represented. The contribution to the undetected debris population was investigated using CLDSIM, a dedicated software system, in order to simulate and propagate the debris clouds produced by each fragmentation event. The characteristics and properties of the fragmentation debris population, obtained by merging the cataloged and undetected particles, were then analyzed.Source: ACTA ASTRONAUTICA, vol. 56 (issue 3), pp. 379-389
DOI: 10.1016/j.actaastro.2004.05.065
Metrics:
Pardini C
Following the first on-orbit fragmentation, the explosion of the Transit 4A rocket body on June 29 1961, 165 breakups were recorded up until August 31 2001. So far, only three collisional breakups have been reasonably confirmed, while the remaining 162 fragmentations resulted from explosions. The aim of this paper is to assess the contribution of these on orbit fragmentation events to the cataloged and undetected orbital debris population. To do this, the largest pieces of fragmentation debris were extracted by the U.S. Space Command catalog of August 31 2001, and subsequently assembled for families or single events, then counted and graphically represented. The contribution to the undetected debris population was investigated using CLDSIM, a dedicated software system, in order to simulate and propagate the debris clouds produced by each fragmentation event. The characteristics and properties of the fragmentation debris population, obtained by merging the cataloged and undetected particles, were then analyzed.Source: ACTA ASTRONAUTICA, vol. 56 (issue 3), pp. 379-389
DOI: 10.1016/j.actaastro.2004.05.065
Metrics:
See at:
Acta Astronautica 
| CNR IRIS | CNR IRIS
2009
Journal article
Restricted
Benefits and risks of using electrodynamic tethers to de-orbit spacecraft
Pardini C, Hanada T, Krisko P H
By using electrodynamic drag to greatly increase the orbital decay rate, an electrodynamic space tether can remove spent or dysfunctional spacecraft from low Earth orbit (LEO) rapidly and safely. Moreover, the low mass requirements of such tether devices make them highly advantageous compared to conventional rocket-based de-orbit systems. However, a tether system is much more vulnerable to space debris impacts than a typical spacecraft and its design must be proved to be safe up to a certain confidence level before being adopted for potential applications. To assess space debris related concerns, in March 2001 a new task (Action Item 19.1) on the "Potential Benefits and Risks of Using Electrodynamic Tethers for End-of-life De-orbit of LEO Spacecraft" was defined by the Inter-Agency Space Debris Coordination Committee (IADC). Two tests were proposed to compute the fatal impact rate of meteoroids and orbital debris on space tethers in circular orbits, at different altitudes and inclinations, as a function of the tether diameter to assess the survival probability of an electrodynamic tether system during typical de-orbiting missions. IADC members from three agencies, the Italian Space Agency (ASI), the Japan Aerospace Exploration Agency (JAXA) and the US National Aeronautics and Space Administration (NASA), participated in the study and different computational approaches were specifically developed within the framework of the IADC task. This paper summarizes the content of the IADC AI 19.1 Final Report. In particular, it introduces the potential benefits and risks of using tethers in space, it describes the assumptions made in the study plan, it compares and discusses the results obtained by ASI, JAXA and NASA for the two tests proposed. Some general conclusions and recommendations are finally extrapolated from this massive and intensive piece of research.Source: ACTA ASTRONAUTICA, vol. 64 (issue 5-6), pp. 571-588
DOI: 10.1016/j.actaastro.2008.10.007
DOI: 10.2514/6.iac-06-b6.2.10
Metrics:
Pardini C, Hanada T, Krisko P H
By using electrodynamic drag to greatly increase the orbital decay rate, an electrodynamic space tether can remove spent or dysfunctional spacecraft from low Earth orbit (LEO) rapidly and safely. Moreover, the low mass requirements of such tether devices make them highly advantageous compared to conventional rocket-based de-orbit systems. However, a tether system is much more vulnerable to space debris impacts than a typical spacecraft and its design must be proved to be safe up to a certain confidence level before being adopted for potential applications. To assess space debris related concerns, in March 2001 a new task (Action Item 19.1) on the "Potential Benefits and Risks of Using Electrodynamic Tethers for End-of-life De-orbit of LEO Spacecraft" was defined by the Inter-Agency Space Debris Coordination Committee (IADC). Two tests were proposed to compute the fatal impact rate of meteoroids and orbital debris on space tethers in circular orbits, at different altitudes and inclinations, as a function of the tether diameter to assess the survival probability of an electrodynamic tether system during typical de-orbiting missions. IADC members from three agencies, the Italian Space Agency (ASI), the Japan Aerospace Exploration Agency (JAXA) and the US National Aeronautics and Space Administration (NASA), participated in the study and different computational approaches were specifically developed within the framework of the IADC task. This paper summarizes the content of the IADC AI 19.1 Final Report. In particular, it introduces the potential benefits and risks of using tethers in space, it describes the assumptions made in the study plan, it compares and discusses the results obtained by ASI, JAXA and NASA for the two tests proposed. Some general conclusions and recommendations are finally extrapolated from this massive and intensive piece of research.Source: ACTA ASTRONAUTICA, vol. 64 (issue 5-6), pp. 571-588
DOI: 10.1016/j.actaastro.2008.10.007
DOI: 10.2514/6.iac-06-b6.2.10
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Acta Astronautica | doi.org | CNR IRIS | CNR IRIS | www.sciencedirect.com | www.scopus.com
2006
Conference article
Restricted
Benefits and risks of using electrodynamic tethers to de-orbit spacecraft
Pardini C, Hanada T, Krisko P H
By using electrodynamic drag to greatly increase the orbital decay rate, an electrodynamic space tether can remove spent or dysfunctional spacecraft from low Earth orbit rapidly and safely. Moreover, the low mass requirements of such tether devices make them highly advantageous compared to conventional rocket-based de-orbit systems. However, tethers are usually very long and thin, providing increased opportunities for something to go wrong. In particular, a tether system is much more vulnerable to space debris impacts than a typical spacecraft and its design must prove to be safe to a certain confidence level before being adopted for potential applications. To assess the space debris related concerns, a new task (Action Item 19.1) on the 'Potential Benefits and Risks of Using Electrodynamic Tethers for End-of-life De-orbit of LEO Spacecraft' was defined by the Inter-Agency Space Debris Coordination Committee (IADC), in March 2001. Two tests were proposed to compute the fatal impact rate of meteoroids and orbital debris on space tethers in circular orbits, at different altitudes and inclinations, as a function of the tether diameter, and to assess the survival probability of an electrodynamic tether system during typical de-orbiting missions. IADC members of three agencies, the Italian Space Agency (ASI), the Japan Aerospace Exploration Agency (JAXA) and the US National Aeronautics and Space Administration (NASA), participated in the study and different computational approaches were specifically developed in the framework of this IADC task. This paper summarizes the content of the IADC AI 19.1 Final Report. In particular, it introduces the potential benefits and risks of using tethers in space, it describes the assumptions made in the study plan, it compares and discusses the results obtained by ASI, JAXA and NASA for the two tests proposed. Some general conclusions and recommendations are eventually highlighted as a result of a massive and intensive study.
Pardini C, Hanada T, Krisko P H
By using electrodynamic drag to greatly increase the orbital decay rate, an electrodynamic space tether can remove spent or dysfunctional spacecraft from low Earth orbit rapidly and safely. Moreover, the low mass requirements of such tether devices make them highly advantageous compared to conventional rocket-based de-orbit systems. However, tethers are usually very long and thin, providing increased opportunities for something to go wrong. In particular, a tether system is much more vulnerable to space debris impacts than a typical spacecraft and its design must prove to be safe to a certain confidence level before being adopted for potential applications. To assess the space debris related concerns, a new task (Action Item 19.1) on the 'Potential Benefits and Risks of Using Electrodynamic Tethers for End-of-life De-orbit of LEO Spacecraft' was defined by the Inter-Agency Space Debris Coordination Committee (IADC), in March 2001. Two tests were proposed to compute the fatal impact rate of meteoroids and orbital debris on space tethers in circular orbits, at different altitudes and inclinations, as a function of the tether diameter, and to assess the survival probability of an electrodynamic tether system during typical de-orbiting missions. IADC members of three agencies, the Italian Space Agency (ASI), the Japan Aerospace Exploration Agency (JAXA) and the US National Aeronautics and Space Administration (NASA), participated in the study and different computational approaches were specifically developed in the framework of this IADC task. This paper summarizes the content of the IADC AI 19.1 Final Report. In particular, it introduces the potential benefits and risks of using tethers in space, it describes the assumptions made in the study plan, it compares and discusses the results obtained by ASI, JAXA and NASA for the two tests proposed. Some general conclusions and recommendations are eventually highlighted as a result of a massive and intensive study.
2002
Conference article
Open Access
A Survey of the Past on Orbit Fragmentation Events through Their Contribution to the Orbital Debris Population
Pardini C
An abstract is not availableSource: SCIENCE AND TECHNOLOGY SERIES, vol. 105, pp. 75-76. Toulouse, France, 1-5 October 2001
Pardini C
An abstract is not availableSource: SCIENCE AND TECHNOLOGY SERIES, vol. 105, pp. 75-76. Toulouse, France, 1-5 October 2001
2003
Other
Open Access
De-orbiting spacecraft with electrodynamic tether devices
Pardini C
De-orbiting devices based on the use of conducting tethers have been recently proposed as innovative solutions to remove satellites and upper stages from low earth orbit when they have completed their missions. Studies of such devices are currently being planned, or are in the early development phase, in the US and Europe. A flight experiment to validate the performance of the bare electrodynamic tether in space and demonstrate its capability to produce thrust is planned by NASA in the first half of 2003. The main objective of this presentation will be to show the various electrodynamic tether systems recently proposed to de-orbit LEO spacecraft, and to emphasize their performances in terms of the orbital decay times.
Pardini C
De-orbiting devices based on the use of conducting tethers have been recently proposed as innovative solutions to remove satellites and upper stages from low earth orbit when they have completed their missions. Studies of such devices are currently being planned, or are in the early development phase, in the US and Europe. A flight experiment to validate the performance of the bare electrodynamic tether in space and demonstrate its capability to produce thrust is planned by NASA in the first half of 2003. The main objective of this presentation will be to show the various electrodynamic tether systems recently proposed to de-orbit LEO spacecraft, and to emphasize their performances in terms of the orbital decay times.
2003
Other
Open Access
Overview of space tether applications: state-of-the-art knowledge and tools
Pardini C
Based on current accessible and available literature and information from experts as well, this overview will outline the state-of-the-art knowledge and studies concerning the use of space tethers to de-orbit spacecraft. A short tutorial on some key aspects of space tether concepts and application perspectives will be provided, while introducing and discussing some theoretical and technical problems to be investigated and solved before such a debris mitigation strategy can be adopted and implemented.
Pardini C
Based on current accessible and available literature and information from experts as well, this overview will outline the state-of-the-art knowledge and studies concerning the use of space tethers to de-orbit spacecraft. A short tutorial on some key aspects of space tether concepts and application perspectives will be provided, while introducing and discussing some theoretical and technical problems to be investigated and solved before such a debris mitigation strategy can be adopted and implemented.
See at:
CNR IRIS 
| ISTI Repository | CNR IRIS
2003
Other
Open Access
Potential benefits and risks of using electrodynamic tethers for end-of-life de-orbit of LEO spacecraft
Pardini C
By using electrodynamic drag to greatly increase the orbital decay rate, an electrodynamic space tether can remove spent or dysfunctional spacecraft from LEO rapidly and safely. Moreover, the low mass requirements of such tether devices make them highly advantageous compared to conventional rocket-based de-orbit systems. However, a tether shall be designed to assure its correct deployment and dynamical stability against the perturbing electrodynamic torque as well. In addition, a tether system is much more vulnerable to space debris impacts than a typical spacecraft and its design must prove to be safe to a certain confidence level before being adopted for a wise range of promising applications. Therefore, the aim of this presentation will be to assess and show the main potential advantages, difficulties and risks related to the use of electrodynamic tether to de-orbit spacecraft.
Pardini C
By using electrodynamic drag to greatly increase the orbital decay rate, an electrodynamic space tether can remove spent or dysfunctional spacecraft from LEO rapidly and safely. Moreover, the low mass requirements of such tether devices make them highly advantageous compared to conventional rocket-based de-orbit systems. However, a tether shall be designed to assure its correct deployment and dynamical stability against the perturbing electrodynamic torque as well. In addition, a tether system is much more vulnerable to space debris impacts than a typical spacecraft and its design must prove to be safe to a certain confidence level before being adopted for a wise range of promising applications. Therefore, the aim of this presentation will be to assess and show the main potential advantages, difficulties and risks related to the use of electrodynamic tether to de-orbit spacecraft.
See at:
CNR IRIS | ISTI Repository | CNR IRIS
2006
Other
Open Access
IADC AI 19.1 on 'Potential Benefits and Risks of Using Tethers for End-of-life De-orbit of LEO Spacecraft'. Final Results and Draft Report
Pardini C, Hanada T, Krisko P H
Despite a small number of full-scale experiments made so far using space tethers, the possibility of de-orbiting spacecraft by means of electrodynamic tethers has been on the drawing board of theorists for almost a decade. By using electrodynamic drag to greatly increase the orbital decay rate, an electrodynamic space tether can remove spent or dysfunctional spacecraft from low Earth orbit rapidly and safely. However, a tether system is much more vulnerable to space debris impacts than a typical spacecraft and its design must prove to be safe to a certain confidence level before being adopted for potential applications. To assess the space debris related concerns, a task on the benefits and risks of using electrodynamic tethers to de-orbit spacecraft was defined by the Inter-Agency Space Debris Coordination Committee (IADC), in March 2001. The task was assigned to the IADC Working Group 2, on 'Environment and Data Base', and a study plan was formulated with the main objective of investigating the potential risk to the tether system integrity due to impacts with space debris. IADC members of three agencies (ASI, JAXA and NASA) participated in the study and different computational approaches were specifically developed in the framework of this IADC task. This presentation introduces the potential benefits and risks of using tethers to de-orbit satellites, presents the assumptions made in the study plan,compares and discusses the results obtained by ASI, JAXA and NASA for the tests proposed.
Pardini C, Hanada T, Krisko P H
Despite a small number of full-scale experiments made so far using space tethers, the possibility of de-orbiting spacecraft by means of electrodynamic tethers has been on the drawing board of theorists for almost a decade. By using electrodynamic drag to greatly increase the orbital decay rate, an electrodynamic space tether can remove spent or dysfunctional spacecraft from low Earth orbit rapidly and safely. However, a tether system is much more vulnerable to space debris impacts than a typical spacecraft and its design must prove to be safe to a certain confidence level before being adopted for potential applications. To assess the space debris related concerns, a task on the benefits and risks of using electrodynamic tethers to de-orbit spacecraft was defined by the Inter-Agency Space Debris Coordination Committee (IADC), in March 2001. The task was assigned to the IADC Working Group 2, on 'Environment and Data Base', and a study plan was formulated with the main objective of investigating the potential risk to the tether system integrity due to impacts with space debris. IADC members of three agencies (ASI, JAXA and NASA) participated in the study and different computational approaches were specifically developed in the framework of this IADC task. This presentation introduces the potential benefits and risks of using tethers to de-orbit satellites, presents the assumptions made in the study plan,compares and discusses the results obtained by ASI, JAXA and NASA for the tests proposed.
See at:
CNR IRIS | ISTI Repository | CNR IRIS
2001
Contribution to conference
Open Access
A survey of the past on orbit fragmentation events through their contribution to the orbital debris population
Pardini C
An abstract is not available.
Pardini C
An abstract is not available.
2001
Contribution to conference
Open Access
2001
Contribution to conference
Metadata Only Access
Long-term effects of spacecraft breakups on the geostationary ring as a function of the end-of-life re-orbiting altitude
Pardini C
An abstract is not available.
Pardini C
An abstract is not available.
See at:
CNR IRIS
2001
Contribution to conference
Restricted
Sdirat: a new method for orbital debris collision risk assessment
Pardini C
An abstract is not available.
Pardini C
An abstract is not available.
2004
Other
Open Access
Benefits and Risks of using Electrodynamic Tethers to De-Orbit Spacecraft - Space Tether Survivability Concerns
Pardini C
The status of the Action Item 19.1 of the Inter-Agency Space Debris Coordination Committee was reported. Three agencies, to date, participated in the study,: ASI, JAXA, and NASA. The fatal impact rate of meteoroids and orbital debris on single strand tethers of different widths and at different orbital altitudes and inclinations was estimated. Results were highly dependent on the chosen meteoroid and orbital debris background models used by each group. The survivability analysis of single and double strand electrodynamic tethers during a de-orbiting mission was also reported. The existing results agreed in kind, that double strand tethers with the highest number of knots were the most likely to survive intact through the decay process. Additional work on this action by the agencies involved is required before a final consensus and report can be completed. This work will continue this year.
Pardini C
The status of the Action Item 19.1 of the Inter-Agency Space Debris Coordination Committee was reported. Three agencies, to date, participated in the study,: ASI, JAXA, and NASA. The fatal impact rate of meteoroids and orbital debris on single strand tethers of different widths and at different orbital altitudes and inclinations was estimated. Results were highly dependent on the chosen meteoroid and orbital debris background models used by each group. The survivability analysis of single and double strand electrodynamic tethers during a de-orbiting mission was also reported. The existing results agreed in kind, that double strand tethers with the highest number of knots were the most likely to survive intact through the decay process. Additional work on this action by the agencies involved is required before a final consensus and report can be completed. This work will continue this year.
See at:
CNR IRIS | ISTI Repository | CNR IRIS
2004
Other
Open Access
Dynamical Evolution of Debris Clouds in GEO
Pardini C
With the goal of helping the optical observers in identifying and characterizing some debris clusters in GEO, three fragmentations of a typical communications satellite have been modeled in GEO using CLDSIM with varying DV distributions (nominal, nominal/5, nominal/10), and the resulting fragments were propagated for 72 years, saving the results at intermediate time steps. The evolution of 10 cm and larger fragments shows that, as expected, the lower the DV case the lower the overall debris dispersion over time. Moreover in all cases the debris clouds remained clearly recognizable throughout the period considered and they occupy a relatively small and compact area of the i-W plot for most of the time.
Pardini C
With the goal of helping the optical observers in identifying and characterizing some debris clusters in GEO, three fragmentations of a typical communications satellite have been modeled in GEO using CLDSIM with varying DV distributions (nominal, nominal/5, nominal/10), and the resulting fragments were propagated for 72 years, saving the results at intermediate time steps. The evolution of 10 cm and larger fragments shows that, as expected, the lower the DV case the lower the overall debris dispersion over time. Moreover in all cases the debris clouds remained clearly recognizable throughout the period considered and they occupy a relatively small and compact area of the i-W plot for most of the time.
See at:
CNR IRIS | ISTI Repository | CNR IRIS
2005
Other
Open Access
Benefits and risks of using electrodynamic tethers to de-orbit spacecraft - results of the AI 19.1 study plan
Pardini C
Over nine thousand satellites and other large objects are currently in orbit around the Earth, along with many smaller particles. As the low Earth orbit is not a limitless resource, some sort of debris mitigation measures are needed to solve the problem of unusable satellites and spent upper stages. It has been suggested that every satellite deployed should carry extra propellant to bring it down once completed its mission. On the other hand, electrodynamic tethers, potentially able to rapidly remove unwanted satellites and upper stages from low Earth orbits with a low mass requirement, have been recently proposed as an alternative solution. Nevertheless, electrodynamic tethers introduce unusual problems when viewed from the space debris perspective. In particular, because of their small diameter, tethers of normal design may have a high probability of being severed by impacts with relatively small meteoroids and orbital debris. The Inter-Agency Space Debris Coordination Committee (IADC) recognized this demanding task and a new action item (AI 19.1) was opened, in 2001, to investigate the potential benefits and risks of using tethers in space. This action item was successively focused on electrodynamic tethers to de-orbit spacecraft, while a study proposal was addressed to assess the tethers survivability concerns. The institute ISTI of the Italian National Research Council (CNR), together with the Kyushu University, in Japan, and NASA participated in the IADC study. Different models and techniques were developed and applied to compute the fatal impact rate of meteoroids and orbital debris on space tethers in circular orbits, at different altitudes and inclinations, as well as to assess the survival probability of electrodynamic tether systems during some baseline de-orbiting missions. This work compares the results obtained at ISTI with those computed at the Kyushu University and NASA concerning the vulnerability to debris impacts of a specific electrodynamic tether during some typical de-orbiting missions. Besides the single line tether design, double line solutions were analysed as well to reduce the tether vulnerability. The orbital debris and meteoroid fluxes models adopted included ORDEM 2000, MASTER 2001, DAS 1.5.3 and Grun 1985. The results obtained were similar for a single line tether, confirming that the survivability concern is fully justified and that no de-orbiting mission, from the altitudes and inclinations considered, is possible if the tether diameter is smaller than a few millimetres. The survival probability may significantly increase for a double line configuration with a sufficiently high number of loops. The results strongly depend on the debris environment model adopted. The more pessimistic results were obtained with ORDEM 2000. The MASTER 2001 and DAS 1.5.3 fluxes resulted in comparable survival probabilities higher than ORDEM 2000.
Pardini C
Over nine thousand satellites and other large objects are currently in orbit around the Earth, along with many smaller particles. As the low Earth orbit is not a limitless resource, some sort of debris mitigation measures are needed to solve the problem of unusable satellites and spent upper stages. It has been suggested that every satellite deployed should carry extra propellant to bring it down once completed its mission. On the other hand, electrodynamic tethers, potentially able to rapidly remove unwanted satellites and upper stages from low Earth orbits with a low mass requirement, have been recently proposed as an alternative solution. Nevertheless, electrodynamic tethers introduce unusual problems when viewed from the space debris perspective. In particular, because of their small diameter, tethers of normal design may have a high probability of being severed by impacts with relatively small meteoroids and orbital debris. The Inter-Agency Space Debris Coordination Committee (IADC) recognized this demanding task and a new action item (AI 19.1) was opened, in 2001, to investigate the potential benefits and risks of using tethers in space. This action item was successively focused on electrodynamic tethers to de-orbit spacecraft, while a study proposal was addressed to assess the tethers survivability concerns. The institute ISTI of the Italian National Research Council (CNR), together with the Kyushu University, in Japan, and NASA participated in the IADC study. Different models and techniques were developed and applied to compute the fatal impact rate of meteoroids and orbital debris on space tethers in circular orbits, at different altitudes and inclinations, as well as to assess the survival probability of electrodynamic tether systems during some baseline de-orbiting missions. This work compares the results obtained at ISTI with those computed at the Kyushu University and NASA concerning the vulnerability to debris impacts of a specific electrodynamic tether during some typical de-orbiting missions. Besides the single line tether design, double line solutions were analysed as well to reduce the tether vulnerability. The orbital debris and meteoroid fluxes models adopted included ORDEM 2000, MASTER 2001, DAS 1.5.3 and Grun 1985. The results obtained were similar for a single line tether, confirming that the survivability concern is fully justified and that no de-orbiting mission, from the altitudes and inclinations considered, is possible if the tether diameter is smaller than a few millimetres. The survival probability may significantly increase for a double line configuration with a sufficiently high number of loops. The results strongly depend on the debris environment model adopted. The more pessimistic results were obtained with ORDEM 2000. The MASTER 2001 and DAS 1.5.3 fluxes resulted in comparable survival probabilities higher than ORDEM 2000.
See at:
CNR IRIS | ISTI Repository | CNR IRIS
2008
Other
Restricted
Status of ISO NWI: space systems - determining orbit lifetime
Oltrogge D, Klinkrad H, Finkleman D, Benech J, Da Silva A, Fujita G, Pardini C, Stryzhak Y
This international standard specifies a process to estimate orbital lifetime of LEO crossing orbits, appropriate estimation methods and their respective regions of applicability in support of adherence to IADC orbit lifetime guidelines for spacecraft and their associated debris objects.
Oltrogge D, Klinkrad H, Finkleman D, Benech J, Da Silva A, Fujita G, Pardini C, Stryzhak Y
This international standard specifies a process to estimate orbital lifetime of LEO crossing orbits, appropriate estimation methods and their respective regions of applicability in support of adherence to IADC orbit lifetime guidelines for spacecraft and their associated debris objects.
2006
Other
Metadata Only Access
IADC Action Item 19.1: Potential Benefits and Risks of using Electrodynamic Tethers for End-of-life De-orbit of LEO Spacecraft
Pardini C, Hanada T, Krisko H P
Over nine thousand satellites and other trackable objects are currently in orbit around the Earth, along with many smaller particles. As the low Earth orbit is not a limitless resource, some sort of debris mitigation measures are needed to solve the problem of unusable satellites and spent upper stages. De-orbiting devices based on the use of conducting tethers have been recently proposed as innovative solutions to mitigate the growth of orbital debris. However, tethers in space introduce unusual problems when viewed from the space debris perspective. They present a much greater risk to operating spacecraft due to their considerably large collision cross-sectional area. Because of their small diameter, tethers of normal design may have a high probability of being severed by impacts with relatively small meteoroids and orbital debris, while the resulting tether fragments may pose additional risks to operating spacecraft. Such space debris related concerns prompted the Inter-Agency Space Debris Coordination Committee (IADC) to recognize this demanding task and to open, at the 19th IADC meeting held in Cologne, Germany, from 22 to 23 March 2001, a new Action Item (AI 19.1) with the purpose of investigating the potential benefits and risks of using tethers in space. The task was assigned to Working Group 2 (Environment and Data Base) and a WG 2 member, Gerhard Drolshagen of the European Space Agency, volunteered to collect information on the existing and under development tools to analyse the dynamics of tethers in space and to estimate the collision risk of tethers with space debris and operative spacecraft. The preliminary status of the task was presented by G. Drolshagen at the 20th IADC meeting held in Guilford, Surrey, England, from 9 to 12 April 2002. Afterwards, another WG 2 member, Carmen Pardini for the Italian Space Agency, volunteered to coordinate this study and, at the 21st IADC meeting held in Bangalore, India, from 10 to 13 March 2003, C. Pardini informed the IADC WG 2 members on the advanced status of the Action Item giving three presentations: 1. Overview of space tether applications: state-of-the-art knowledge and tools; 2. De-orbiting spacecraft with electrodynamic tether devices; 3. Potential benefits and risks of using electrodynamic tethers for end-of-life de-orbit of LEO spacecraft. At the same meeting, following thought-provoking discussions, the specifics of the task were formulated and a proposal to address the Electrodynamic Tether (EDT) systems survivability concern was advanced inside WG 2. The original AI designation, i.e.
Pardini C, Hanada T, Krisko H P
Over nine thousand satellites and other trackable objects are currently in orbit around the Earth, along with many smaller particles. As the low Earth orbit is not a limitless resource, some sort of debris mitigation measures are needed to solve the problem of unusable satellites and spent upper stages. De-orbiting devices based on the use of conducting tethers have been recently proposed as innovative solutions to mitigate the growth of orbital debris. However, tethers in space introduce unusual problems when viewed from the space debris perspective. They present a much greater risk to operating spacecraft due to their considerably large collision cross-sectional area. Because of their small diameter, tethers of normal design may have a high probability of being severed by impacts with relatively small meteoroids and orbital debris, while the resulting tether fragments may pose additional risks to operating spacecraft. Such space debris related concerns prompted the Inter-Agency Space Debris Coordination Committee (IADC) to recognize this demanding task and to open, at the 19th IADC meeting held in Cologne, Germany, from 22 to 23 March 2001, a new Action Item (AI 19.1) with the purpose of investigating the potential benefits and risks of using tethers in space. The task was assigned to Working Group 2 (Environment and Data Base) and a WG 2 member, Gerhard Drolshagen of the European Space Agency, volunteered to collect information on the existing and under development tools to analyse the dynamics of tethers in space and to estimate the collision risk of tethers with space debris and operative spacecraft. The preliminary status of the task was presented by G. Drolshagen at the 20th IADC meeting held in Guilford, Surrey, England, from 9 to 12 April 2002. Afterwards, another WG 2 member, Carmen Pardini for the Italian Space Agency, volunteered to coordinate this study and, at the 21st IADC meeting held in Bangalore, India, from 10 to 13 March 2003, C. Pardini informed the IADC WG 2 members on the advanced status of the Action Item giving three presentations: 1. Overview of space tether applications: state-of-the-art knowledge and tools; 2. De-orbiting spacecraft with electrodynamic tether devices; 3. Potential benefits and risks of using electrodynamic tethers for end-of-life de-orbit of LEO spacecraft. At the same meeting, following thought-provoking discussions, the specifics of the task were formulated and a proposal to address the Electrodynamic Tether (EDT) systems survivability concern was advanced inside WG 2. The original AI designation, i.e.
See at:
CNR IRIS
2006
Other
Open Access
Benefits and risks of using electrodynamic tethers to de-orbit spacecraft
Pardini C, Hanada T, Krisko P H
The document summarizes the content of the Inter-Agency Space Debris Coordination Committee (IADC) Final Report on Action Item 19.1 (Potential Benefits and Risks of using Electrodynamic Tethers for End-of-life De-orbit of LEO Spacecraft). It describes the potential benefits and risks of using tethers in space, and discusses the results obtained by ASI, JAXA and NASA for the tests proposed in the AI 19.1 study plan.
Pardini C, Hanada T, Krisko P H
The document summarizes the content of the Inter-Agency Space Debris Coordination Committee (IADC) Final Report on Action Item 19.1 (Potential Benefits and Risks of using Electrodynamic Tethers for End-of-life De-orbit of LEO Spacecraft). It describes the potential benefits and risks of using tethers in space, and discusses the results obtained by ASI, JAXA and NASA for the tests proposed in the AI 19.1 study plan.
See at:
CNR IRIS | ISTI Repository | CNR IRIS
2001
Other
Open Access
2011
Other
Restricted
Comparison of the ballistic parameter distribution of the Cosmos 2251 and Iridium 33 cataloged fragments
Pardini C, Liou J C, Sorge, M
At the 28th IADC meeting in Trivandrum, India (9-12 March 2010), it was agreed to exchange information on the area-to-mass distribution of the Iridium 33 and Cosmos 2251 fragments. Three members of the IADC WG2 participated in the study: Liou, Jer-Chyi (NASA - NASA Delegation); Pardini, Carmen (ISTI/CNR - ASI Delegation); Sorge, Marlon (Aerospace Corporation - NASA Delegation). The ballistic parameter (B = CdA/M) distributions of the Cosmos 2251 and Iridium 33 cataloged fragments were compared, based on three independent approaches. The results obtained revealed a very good agreement.
Pardini C, Liou J C, Sorge, M
At the 28th IADC meeting in Trivandrum, India (9-12 March 2010), it was agreed to exchange information on the area-to-mass distribution of the Iridium 33 and Cosmos 2251 fragments. Three members of the IADC WG2 participated in the study: Liou, Jer-Chyi (NASA - NASA Delegation); Pardini, Carmen (ISTI/CNR - ASI Delegation); Sorge, Marlon (Aerospace Corporation - NASA Delegation). The ballistic parameter (B = CdA/M) distributions of the Cosmos 2251 and Iridium 33 cataloged fragments were compared, based on three independent approaches. The results obtained revealed a very good agreement.