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A 10 nN resolution thrust-stand for micro-propulsion devices

Publications associées (11)

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Challenging space missions include those at very low altitudes, where the atmosphere is the source of aerodynamic drag on the spacecraft, that finally defines the mission's lifetime, unless a way to compensate for it is provided. This environment is named ...

2022

A 1.5D fluid-Monte Carlo model of a hydrogen helicon plasma

Ivo Furno, Alan Howling, Philippe Frédérique Bruno Guittienne, Rémy Jacquier, Riccardo Agnello

Helicon plasma sources operating with hydrogen or deuterium might be attractive for fusion applications due to their higher power efficiency compared to inductive radiofrequency plasma sources. In recent years, the resonant antenna ion device (RAID) has be ...

IOP Publishing Ltd2022

Negative Hydrogen Ions in a Helicon Plasma Source

Riccardo Agnello

There is nowadays a large interest to employ helicon plasmas as sources of negative ions for Neutral Beam Injectors (NBIs). Helicon plasma sources offer a number of advantages compared to current Inductive Couple Plasma (ICP) negative ions source, such as ...

EPFL2020

Ion heating and flows in a high power helicon source

Ivo Furno, Alan Howling, Rémy Jacquier, Riccardo Agnello, Gennady Plyushchev

We report experimental measurements of ion temperatures and flows in a high power, linear, magnetized, helicon plasma device, the Resonant Antenna Ion Device (RAID). Parallel and perpendicular ion temperatures on the order of 0.6 eV are observed for an rf ...

Amer Inst Physics2017

ACTIVE MODEL ROCKET STABILIZATION VIA COLD GAS THRUSTERS

Gautier Marie Pierre Rouaze, Anton Ivanov, Xavier Collaud, Raimondo Pictet, Danylo Malyuta, Mikael Martins Gaspar

This paper describes the development and testing of a reaction control system (RCS) for a model rocket named FALCO-4. The rocket uses cold gas jets to keep itself perfectly vertical at low speeds. We first describe the mechanical layout of FALCO-4 and the ...

2015

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Microfabricated electrospray thrusters could revolutionize the spacecraft industry by providing efficient propulsion capabilities to micro and nano satellites (1–100 kg). We present the modeling, design, fabrication and characterization of a new generation ...

Iop Publishing Ltd2014

Production of molecular sideband radioisotope beams at CERN-ISOLDE using a Helicon-type plasma ion source

In order to account for the increasing demand for strong molecular beams for nuclear physics experiments at ISOLDE, a new radioactive ion source concept based on an RE discharge in a magnetized plasma was developed at CERN. Experimental studies at the ISOL ...

Elsevier Science Bv2013

Design and fabrication of the thruster heads for the MicroThrust MEMS electrospray propulsion system

Herbert Shea, Caglar Ataman, Simon Dandavino, Subha Chakraborty

Microfabricated electrospray thrusters are widely acknowledged as one of the most promising technologies for the propulsion of small spacecraft. Their relative simplicity, high efficiency (> 70%), low footprint (M < 500g, V < 10cm3) and large potential spe ...

2013

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A reliable pyroMEMS igniter was successfully demonstrated based on shadow-mask evaporation of metal directly onto solid propellant drops. In this way, intimate contact between the fuel and the igniter was guaranteed. No visible degradation of the fuel was ...

2011

Performance of a micro-fabricated Colloid thruster system

Herbert Shea, Renato Krpoun

In order to fully characterize the performance of the colloid thruster system the electrospray (ES) beam must itself be fully characterized. This may be achieved by measuring various properties such as flow rate, current, droplet/ion charge to mass ratio a ...

2009