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On the Computation of Secondary Electron Emission Models

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4 Author(s)
Clerc, S. ; Res. Dept., Alcatel Alenia Space, Cannes ; Dennison, J.R. ; Hoffmann, R. ; Abbott, J.

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 b1Eo n1 and a more general empirical double power law R(Eo)=b1Eo n1+b2E o n2. 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

Published in:

Plasma Science, IEEE Transactions on  (Volume:34 ,  Issue: 5 )

Date of Publication:

Oct. 2006

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