Secondary electron emission is a critical contributor to the charge particle current balance in spacecraft charging. Spacecraft charging simulation codes use a parameterized expression for the secondary electron (SE) yield delta (Eo) as a function of the incident electron energy Eo. Simple three-step physics models of the electron penetration, transport, and emission from a solid are typically expressed in terms of the incident electron penetration depth at normal incidence R(Eo) and the mean free path of the SE lambda . In this paper, the authors recall classical models for the range R(Eo): a power law expression of the form b1Eon1 and a more general empirical double power law R(Eo)=b1Eon1+b2Eon2. In most models, the yield is the result of an integral along the path length of incident electrons. An improved fourth-order numerical method to compute this integral is presented and compared to the standard second-order method. A critical step in accurately characterizing a particular spacecraft material is the determination of the model parameters in terms of the measured electron yield data. The fitting procedures and range models are applied to several measured data sets to compare their effectiveness in modeling the function delta (Eo) over the full range of energy of incident particles.
On the computation of secondary electron emission models
IEEE Transactions on Plasma Science ; 34 , 5, pt.2 ; 2219-2225
2006
7 Seiten, 19 Quellen
Aufsatz (Zeitschrift)
Englisch
Modeling Secondary Electron Emission Experiment
AIAA | 2011
|MODELING SECONDARY ELECTRON EMISSION EXPERIMENT
British Library Conference Proceedings | 2011
|Secondary Electron Emission From Thin Diamondlike Films
Online Contents | 1997