Engineering topics
Publications and source records attributed to Brophy, J..
Deep Space 1 is the first interplanetary spacecraft to use an ion propulsion system for the primary delta-v maneuvers. The purpose of the mission is to validate a number of technologies, including ion propulsion and a high degree of spacecraft autonomy, on a flyby of an asteroid and two comets.
A major component in validating ion propulsion for use on future deep space and earth orbital missions is demonstrating that the engines have sufficient service life capability.
Described is a Particle-in-Cell with Monte Carlo Collision code developed to perform detailed three-dimensional ion thruster simulations. To capture the full kinetic behavior of ion thruster plumes, both the electrons and ions are treated as test particles. Simulation results are given of the NSTAR ion thruster under ground test and in space conditions. Numerical results are compared.
Full three-dimensional numerical models based on partical-in-cell with Monte Carlo collisions (PIC-MCC) simulations are developed to study ion thruster plasma interactions. 3-D simulation results for the NSTAR ion thruster plasma environment are presented.
Ion thrusters are valued as a high-specific impulse class of space propulsion system.
Ion thrusters are valued as a high-specific impulse class of space propulsion system.
This paper describes the results of a preliminary evaluation of a 1.35 kW anode layer thruster. Data on performance and plume characteristics will be presented. Data on thruster characteristics such as thrust, plume current densities, discharge voltage, discharge current, and mass flow rate along with the results of a 500-hour endurance test wear will be presented.