Development and Test of an Indium FEEP Micropropulsion Subsystem for LISA Pathfinder

Scharlemann, Carsten; Genovese, A.; Buldrini, N.; Schnitzer, René; Früholz, Helmut; Killinger, Rainer

doi:10.2514/6.2007-5251

Cited by 8 publications

(5 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Therefore it is important to obtain a proper knowledge basis of the major propulsion system parameters. This is true in particular for future science missions that rely on technologically novel micro-propulsion systems with very low thrust levels, such as field effective (Scharlemann et al 2007; Alta SpA 2008), or others (Hruby et al 2004). FEEP systems are currently being tested on ground.…”

Section: Background and Motivationmentioning

confidence: 97%

Identification Algorithms for Micro-Propulsion System Parameters Using Drag-Free Test Masses

Ziegler¹,

Fichter

2010

Space Sci Rev

View full text Add to dashboard Cite

Propulsion system characteristics determine to a large extent the dynamic behavior of a spacecraft. For many future science missions technologically novel micro-propulsion systems are required. In order to support its characterization, in-orbit experiments and subsequent data processing on ground can be an appropriate add-on to ground-based laboratory measurements. In this paper two identification methods for three major thruster parameters, thrust gain, thrust direction, and lever arm, are presented and compared. They are based on measurements of a precise inertial instrument that consists of two test masses, whose degrees of freedom are "mixed" with respect to its control principle, i.e. they are either drag-free controlled (free-flying) or suspension controlled (accelerometer mode). Using drag-free coordinates is a novel approach. It is related and compared to the more conventional approach using "accelerometer-like" measurements.

show abstract

Section: Background and Motivationmentioning

confidence: 97%

Identification Algorithms for Micro-Propulsion System Parameters Using Drag-Free Test Masses

Ziegler¹,

Fichter

2010

Space Sci Rev

View full text Add to dashboard Cite

show abstract

“…̇= ℎ̇ℎ ⁄ ( [21], [22]) where is a constant to be determined, ℎ is the indentation depth and the dot denotes differentiation with respect to time. In the creep regime the flow stress in the isotropic solid depends upon the axial strain rate via a power-law expression =̇ (1) where and are material constants for a given temperature, to be determined experimentally. The material hardness is defined as the average pressure under the indenter, proportional to the flow stress via = (2) where is suggested by Tabor for rate-independent metals (Tabor [23]).…”

Section: Indentation Of a Power-law Creeping Materialsmentioning

confidence: 99%

“…Indium has wide applications in the electronics industry and potential uses as a propeller in FieldEmission Electric Propulsion micro-thrusters; it was a strong contender for use in the ESA Pathfinder mission [1]. Pure polycrystalline Indium at room temperature is a soft and ductile metal with a low melting point (157°C) and strength of order of few MPa.…”

Section: Introductionmentioning

confidence: 99%

Measurements of the mechanical response of Indium and of its size dependence in bending and indentation

Iliev

Chen

Pathan

et al. 2017

Materials Science and Engineering: A

View full text Add to dashboard Cite

“…FEEP possesses several advantages, including high specific impulse, compact form factor and long service life, making it highly suitable for drag compensation, attitude control and orbit maintenance for nano-satellites [2]. According to the wetting properties of the propellant, FEEP can be categorized into needle, capillary, and porous types [3][4][5][6]. The solid needle-type FEEP features a micro-sized tungsten tip, which exhibits high electrical impedance, operates at a low firing voltage, and facilitates thrust clustering to generate substantial propulsion [7].…”

Section: Introductionmentioning

confidence: 99%

Simulation of liquid cone formation on the tip apex of indium field emission electric propulsion thrusters

SUN 孙,

DENG 邓,

LIU 刘

et al. 2024

Plasma Sci. Technol.

View full text Add to dashboard Cite

Field emission electric propulsion (FEEP) thrusters possess excellent characteristics such as high specific impulse, low power requirements, compact size, and precise pointing capabilities, making them ideal propulsion devices for micro-nano satellites. However, the detection of certain aspects, such as the evolution process of the liquid cone and the physical quantities at the cone apex, proves challenging due to the minute size of the needle tip and the vacuum environment in which they operate. Consequently, this paper introduces a computational fluid dynamics (CFD) model to gain insights into the formation process of the liquid cone on the tip apex of Indium FEEP. The CFD model is based on the electrohydrodynamic (EHD) equations and the volume of fluid (VOF) method. The entire cone formation process can be divided into three stages, and the time-dependent characteristics of the physical quantities at the cone apex are investigated. The influences of film thickness, apex radius size, and applied voltage are compared. The results indicate a gradual increase in the values of electrostatic stress and surface tension stress at the cone apex over an initial period, followed by a rapid escalation within a short duration. Apex configurations featuring a small radius, thick film, and high voltage exhibit a propensity for liquid cone formation, and the cone growth time decreasing as the film thickness increases. Moreover, some unstable behavior is observed during the cone formation process.

show abstract

Development and Test of an Indium FEEP Micropropulsion Subsystem for LISA Pathfinder

Cited by 8 publications

References 6 publications

Identification Algorithms for Micro-Propulsion System Parameters Using Drag-Free Test Masses

Identification Algorithms for Micro-Propulsion System Parameters Using Drag-Free Test Masses

Measurements of the mechanical response of Indium and of its size dependence in bending and indentation

Simulation of liquid cone formation on the tip apex of indium field emission electric propulsion thrusters

Contact Info

Product

Resources

About