Spacecraft Charging.
Abstract
If a spacecraft is exposed to steady stream of current density, the charge of which is deposited on the surface of a cylindrical conducting spacecraft, internal electromagnetic fields are generated. If the internal fields are of sufficient strength, undesirable electronic noise or damage may result. This thesis presents three approaches for calculating the induced Electric field: Separation of variables, variational calculus, and the use of Green's functions. The spacecraft is modeled as a hollow, infinite cylinder. The fields are calculated for the case in which the incoming current is incident perpendicularly to the longitudinal axis of the cylinder. Basic electro-static theory reveals that the governing equation for the potential is Laplace's Equation, subject to Neumann boundary conditions. This equation is first solved by separation of variables. The electric field predicted for representive values in incoming current density are on the order of 10 to the minus 7th power volts/meter. The Green's function approximations of the potential distribution were consistent with analytic results to at least two significant figures.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1978
- Accession Number
- ADA064754
Entities
People
- Richard A. Passow
Organizations
- Air Force Institute of Technology