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Research paper thumbnail of VEnUS program status

AIAA SPACE 2016, 2016

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Research paper thumbnail of Proposal and Testing of a New Hybrid Pressure-Density Based Algorithm for MPD-Thruster Simulations

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Research paper thumbnail of The Ground Segment and Operations of ESA's Intermediate eXperimental Vehicle (IXV)

14th International Conference on Space Operations, 2016

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Research paper thumbnail of MicroNewton Proportional Thruster Test Results

41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005

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Research paper thumbnail of Micro-Thrust Balance Testing and Characterization

ABSTRACT

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Research paper thumbnail of muN Propulsion Subsystem Developments for Drag-Free Spacecraft

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Research paper thumbnail of A Survey of the 'New Grid Systems for Ion Engines' Technology Project

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Research paper thumbnail of μN Propulsion Subsystem Developments for Drag-Free Spacecraft

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Research paper thumbnail of Experimental Studies Related to Field Emission Thruster Operation: Emission Impact on Solar Cell Performances and Neutralization Electron Backstreaming Phenomena

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Research paper thumbnail of Xenon resistojets as secondary propulsion on EP spacecrafts and performance results of resistojets using Xenon

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Research paper thumbnail of Basic Issues in Electric Propulsion Testing and the Need for International Standards

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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Research paper thumbnail of Direct Thrust and Thrust Noise Measurements on the LISA Pathfinder Field Emission Thruster

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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Research paper thumbnail of Neutraliser for FEEPs: review on the development status

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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Research paper thumbnail of Experimental Study of the Neutralization Process in Field- Emission Electric Propulsion

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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Research paper thumbnail of A large space simulator for electric propulsion testing - Design requirements and engineering analysis

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000

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Research paper thumbnail of Vega Launch Operations and Ground Facilities

13th International Conference on Space Operations 2014, 2014

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Research paper thumbnail of FEEP Dynamic Characterization with Flight-Standard Power Control Unit

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004

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Research paper thumbnail of Thrust Characterization of Cryosat Cold-gas Propulsion System

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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Research paper thumbnail of 3-D plume characterization of a FEEP thruster

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000

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Research paper thumbnail of Endurance test of the micronewton FEEP thruster

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000

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Research paper thumbnail of VEnUS program status

AIAA SPACE 2016, 2016

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Research paper thumbnail of Proposal and Testing of a New Hybrid Pressure-Density Based Algorithm for MPD-Thruster Simulations

Bookmarks Related papers MentionsView impact

Research paper thumbnail of The Ground Segment and Operations of ESA's Intermediate eXperimental Vehicle (IXV)

14th International Conference on Space Operations, 2016

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Research paper thumbnail of MicroNewton Proportional Thruster Test Results

41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005

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Research paper thumbnail of Micro-Thrust Balance Testing and Characterization

ABSTRACT

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Research paper thumbnail of muN Propulsion Subsystem Developments for Drag-Free Spacecraft

Bookmarks Related papers MentionsView impact

Research paper thumbnail of A Survey of the 'New Grid Systems for Ion Engines' Technology Project

Bookmarks Related papers MentionsView impact

Research paper thumbnail of μN Propulsion Subsystem Developments for Drag-Free Spacecraft

Bookmarks Related papers MentionsView impact

Research paper thumbnail of Experimental Studies Related to Field Emission Thruster Operation: Emission Impact on Solar Cell Performances and Neutralization Electron Backstreaming Phenomena

Bookmarks Related papers MentionsView impact

Research paper thumbnail of Xenon resistojets as secondary propulsion on EP spacecrafts and performance results of resistojets using Xenon

Bookmarks Related papers MentionsView impact

Research paper thumbnail of Basic Issues in Electric Propulsion Testing and the Need for International Standards

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

Research paper thumbnail of Direct Thrust and Thrust Noise Measurements on the LISA Pathfinder Field Emission Thruster

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

Research paper thumbnail of Neutraliser for FEEPs: review on the development status

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

Research paper thumbnail of Experimental Study of the Neutralization Process in Field- Emission Electric Propulsion

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

Research paper thumbnail of A large space simulator for electric propulsion testing - Design requirements and engineering analysis

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000

Bookmarks Related papers MentionsView impact

Research paper thumbnail of Vega Launch Operations and Ground Facilities

13th International Conference on Space Operations 2014, 2014

Bookmarks Related papers MentionsView impact

Research paper thumbnail of FEEP Dynamic Characterization with Flight-Standard Power Control Unit

40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004

Bookmarks Related papers MentionsView impact

Research paper thumbnail of Thrust Characterization of Cryosat Cold-gas Propulsion System

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

Research paper thumbnail of 3-D plume characterization of a FEEP thruster

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000

Bookmarks Related papers MentionsView impact

Research paper thumbnail of Endurance test of the micronewton FEEP thruster

36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2000

Bookmarks Related papers MentionsView impact