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Papers by davide nicolini
AIAA SPACE 2016, 2016
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14th International Conference on Space Operations, 2016
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41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005
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ABSTRACT
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We present the main aspects related to effective and reliable ground testing of advanced Electric... more We present the main aspects related to effective and reliable ground testing of advanced Electric Propulsion Systems, with particular care at evidencing key issues which will need to be addressed in order to increase the reliability, confidence and actual application potential of such propulsion systems in space missions. The basic parameters which affect specific types of measurements and tests are addressed, and the many (often overlooked) pitfalls are evidenced: these clearly require the definition and enforcement of a series of standard test procedures and methods, both related to measurements to be performed on EPS's and to the unique identification of the test environment. Electric propulsion represents a key technology for present day space activities, and also among the most promising ones for future developments and space missions. Propulsion systems based on Hall Effect Thrusters (HET) and Gridded Ion Engines (GIE) are particularly interesting for spacecrafts with long...
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The paper presents the first exhaustive thrust measurement campaign on the field emission thruste... more The paper presents the first exhaustive thrust measurement campaign on the field emission thruster system (or FEEP system) developed for the LISA Pathfinder spacecraft. LISA Pathfinder is the first demonstration spacecraft of the joint ESA/NASA LISA (Laser Interferometer Space Antenna) mission. LISA Pathfinder is built by ESA and will fly as a payload the NASA Disturbance Reduction System. The core technologies under development at ESA and to be verified in orbit are the inertial sensor and the field emission thrusters. The thrust stand developed for these measurements is based on a dual pendulum force sensor where the pendulum deflection is measured by an interferometer. The thrust stand is installed on a multi-stage active-passive isolation system. The thruster tested was a flight-like LISA Pathfinder FEEP thruster driven by its flight-standard electronics. All performance parameters were measured and carefully characterized including noise down to sub-mHz frequencies.
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Since year 2005 a new neutraliser concept has been developed, to be used for neutralisation of th... more Since year 2005 a new neutraliser concept has been developed, to be used for neutralisation of the positive charges in the beam of FEEP thrusters. The unit design is now mature for the flight phases of both the European LISA PF and Microscope programs. The device is based on a small light and low power consumption Barium impregnated cathode operating without the need of Xenon gas. The neutraliser works in a biased diode configuration allowing the extraction of electrons and their acceleration to be independent processes separately controlled by the Power Supply Unit. The qualification activities have been successfully completed on both the two mentioned programs. Lifetime tests are presently concluded under the MICROSCOPE program (1000h) and ongoing under the LISA PF one (6000h expected, more than 3500h, presently achieved). During ground tests these devices have demonstrated the ability to emit the specified current levels asking for a negative bias of few tens of Volts. Then, it i...
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Results of an experimental test campaign dealing with the neutralization on FEEP technology are r... more Results of an experimental test campaign dealing with the neutralization on FEEP technology are reported together with simulations of the thermionic neutralizer chosen for the MICROSCOPE and LISA-Pathfinder missions. Stabilization of the floating potential is obtained instantaneously predicting a moderate charging of the spacecraft in a range of a hundred of Volts. Ion induced secondary electron emission negligible influence on neutralization process is demonstrated. Plasma parameters inside the vacuum chamber are roughly extrapolated from neutralizer performances and correlated with thruster propellant.
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36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000
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13th International Conference on Space Operations 2014, 2014
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40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004
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40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004
This paper presents and discusses some significant results from the acceptance test campaign of t... more This paper presents and discusses some significant results from the acceptance test campaign of the Cryosat cold-gas thrusters flight models, performed in the ESA Propulsion Laboratory at ESTEC. The tests were mainly dedicated to steady-state thrust, internal leakage and ...
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36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000
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36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000
Bookmarks Related papers MentionsView impact
AIAA SPACE 2016, 2016
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Bookmarks Related papers MentionsView impact
14th International Conference on Space Operations, 2016
Bookmarks Related papers MentionsView impact
41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005
Bookmarks Related papers MentionsView impact
ABSTRACT
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
Bookmarks Related papers MentionsView impact
We present the main aspects related to effective and reliable ground testing of advanced Electric... more We present the main aspects related to effective and reliable ground testing of advanced Electric Propulsion Systems, with particular care at evidencing key issues which will need to be addressed in order to increase the reliability, confidence and actual application potential of such propulsion systems in space missions. The basic parameters which affect specific types of measurements and tests are addressed, and the many (often overlooked) pitfalls are evidenced: these clearly require the definition and enforcement of a series of standard test procedures and methods, both related to measurements to be performed on EPS's and to the unique identification of the test environment. Electric propulsion represents a key technology for present day space activities, and also among the most promising ones for future developments and space missions. Propulsion systems based on Hall Effect Thrusters (HET) and Gridded Ion Engines (GIE) are particularly interesting for spacecrafts with long...
Bookmarks Related papers MentionsView impact
The paper presents the first exhaustive thrust measurement campaign on the field emission thruste... more The paper presents the first exhaustive thrust measurement campaign on the field emission thruster system (or FEEP system) developed for the LISA Pathfinder spacecraft. LISA Pathfinder is the first demonstration spacecraft of the joint ESA/NASA LISA (Laser Interferometer Space Antenna) mission. LISA Pathfinder is built by ESA and will fly as a payload the NASA Disturbance Reduction System. The core technologies under development at ESA and to be verified in orbit are the inertial sensor and the field emission thrusters. The thrust stand developed for these measurements is based on a dual pendulum force sensor where the pendulum deflection is measured by an interferometer. The thrust stand is installed on a multi-stage active-passive isolation system. The thruster tested was a flight-like LISA Pathfinder FEEP thruster driven by its flight-standard electronics. All performance parameters were measured and carefully characterized including noise down to sub-mHz frequencies.
Bookmarks Related papers MentionsView impact
Since year 2005 a new neutraliser concept has been developed, to be used for neutralisation of th... more Since year 2005 a new neutraliser concept has been developed, to be used for neutralisation of the positive charges in the beam of FEEP thrusters. The unit design is now mature for the flight phases of both the European LISA PF and Microscope programs. The device is based on a small light and low power consumption Barium impregnated cathode operating without the need of Xenon gas. The neutraliser works in a biased diode configuration allowing the extraction of electrons and their acceleration to be independent processes separately controlled by the Power Supply Unit. The qualification activities have been successfully completed on both the two mentioned programs. Lifetime tests are presently concluded under the MICROSCOPE program (1000h) and ongoing under the LISA PF one (6000h expected, more than 3500h, presently achieved). During ground tests these devices have demonstrated the ability to emit the specified current levels asking for a negative bias of few tens of Volts. Then, it i...
Bookmarks Related papers MentionsView impact
Results of an experimental test campaign dealing with the neutralization on FEEP technology are r... more Results of an experimental test campaign dealing with the neutralization on FEEP technology are reported together with simulations of the thermionic neutralizer chosen for the MICROSCOPE and LISA-Pathfinder missions. Stabilization of the floating potential is obtained instantaneously predicting a moderate charging of the spacecraft in a range of a hundred of Volts. Ion induced secondary electron emission negligible influence on neutralization process is demonstrated. Plasma parameters inside the vacuum chamber are roughly extrapolated from neutralizer performances and correlated with thruster propellant.
Bookmarks Related papers MentionsView impact
36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000
Bookmarks Related papers MentionsView impact
13th International Conference on Space Operations 2014, 2014
Bookmarks Related papers MentionsView impact
40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004
Bookmarks Related papers MentionsView impact
40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004
This paper presents and discusses some significant results from the acceptance test campaign of t... more This paper presents and discusses some significant results from the acceptance test campaign of the Cryosat cold-gas thrusters flight models, performed in the ESA Propulsion Laboratory at ESTEC. The tests were mainly dedicated to steady-state thrust, internal leakage and ...
Bookmarks Related papers MentionsView impact
36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000
Bookmarks Related papers MentionsView impact
36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000
Bookmarks Related papers MentionsView impact