By Anthony K. Hyder

This article is dedicated to the applied sciences serious to the advance of spacecraft electricity platforms. The technology and engineering of sun, chemical and nuclear platforms is tested including the limitations imposed by way of the gap and thermal environments during which the structures needs to function. information of expertise and the heritage that resulted in the state of the art are provided at a degree acceptable for the scholar as a textbook or the practicing engineer as a reference.

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This minimum occurs because at the very low pressures an electron will traverse the entire gap distance without ionizing any hydrogen atom and without initiating an avalanche (breakdown of the gas). At higher pressures, the mean free path between collisions of the electron with a hydrogen atom is so short that the electron cannot gain enough energy between collisions to ionize the atom. At the minimum, less than 300 volts in this example, avalanche ionization occurs and arcing is initiated between the electrodes.

As Purvis (1993) points out, in the more energetic substorm plasmas, the Debye length, the scale length over which charge neutrality is established and equilibrium ex- ists, is very large compared to the size of the spacecraft- Thus, space-charge effects can be neglected, system voltages remain small compared to the plasma energies, and the plasma environment determines the electrical interactions. Furthermore, the plasma current density is of the order 10~10 A/cm2 which is comparable to the photoelectron current density for a sunlit surface making the photocurrent an important factor.

Spacecraft Design and Sizing, in Space Mission Analysis and Design (Second Edition), Larson, W. J. and Wertz, J. R. , Torrance, California, and Kluwer Academic Publishers, Dordrecht, 1992), 285-337. Stark, J. P. , Fortescue, P. , and Tatnall, A. R. , Introduction, in Spacecraft Systems Engineering (Second Edition), Fortescue, P. and Stark, J. ), (Wiley and Sons, Chichester, 1995), 2-9. , D. ), Space Log 1994, (TRW, Redondo Beach, California, 1994). , Utility Aspects of Space Power: Load Management versus Source Management (NASA Technical Memorandum 108496, 1995).

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