A Comprehensive Investigation Using the Mie Scattering Theory of Micron and Submicron Lunar Ejecta Dynamics in Selenocentric, Cislunar and Geocentric Space.
The complete set of forces acting on a particle traveling in selenocentric, cislunar and geocentric space are studied in detail. Force tables are calculated and presented using varying particle sizes and densities as well as two particle potentials. The radiation pressure force is treated independently under a geometric, Raleigh and the full Mie scattering theory approximation. Comparisons of the beta values under all of the above are calculated and analyzed in detail. A computer model which calculates and categorizes orbits for particles originating on the lunar surface and traveling in selenocentric, cislunar and geocentric space is presented. The results using the data from over 1.9 million individual orbits calculated under varying initial conditions for the earth, moon and particle are given. The radiation pressure force term in the above mentioned computer model is again calculated under all the approximations listed previously. A correlation between the particle's complex index of refraction and its probability of intersection with the EMPS is shown. Evidence is presented to show that particles with radii below 0.1 mu can indeed attain a near-earth orbit under the proper conditions. A method whereby the origin of particles in near-earth orbit can be determined is discussed.
- Pub Date:
- Physics: Astronomy and Astrophysics, Geophysics;
- Computer Programs;
- Computerized Simulation;
- Loads (Forces);
- Lunar Surface;
- Mie Scattering;
- Radiation Pressure;
- Tables (Data);
- Lunar and Planetary Exploration