Accession Number : ADA542016


Title :   Mission Capability Gains from Multi-Mode Propulsion Thrust Variations on a Variety Spacecraft Orbital Maneuvers


Descriptive Note : Master's thesis; Technical paper


Corporate Author : AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIRECTORATE


Personal Author(s) : Rexius, Tiffany E


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a542016.pdf


Report Date : Mar 2011


Pagination or Media Count : 161


Abstract : Many spacecraft today have two separate propulsion systems: a chemical system for large maneuvers and an electric propulsion system for minor adjustments. The concept of coupling an electric and chemical propulsion system is not necessarily new but few studies have been published which discuss having an integrated chemical and electrical propulsion system. The utilization of a multi-mode propulsion (MMP) system could reduce the amount of propellant required for maneuvers in addition to lowering overall propulsion system mass. MMP refers to a propulsion system that couples an electric and chemical propulsion system which utilizes the same propellant tank and piping. A fully coupled system provides many advantages over a spacecraft with a single chemical or electric propulsion system. To help quantify the potential benefits in the utilization of a MMP system three separate spacecraft missions were analyzed. The missions were chosen to be representative of potential spacecraft missions. These missions include an altitude change mission, a phase change mission and a plane change mission. Each mission had a fixed propellant mass and time constraint. A variety of thrust profiles were investigated that utilized a combination of electric and chemical propulsion to complete the maneuver within the mission constraints. The optimal thrust profile for each mission was determined as the profile which completed the mission in the time constraint with the least amount of propellant. In all cases the utilization of the electric propulsion system decreased overall required propellant mass.


Descriptors :   *PROPULSION SYSTEMS , *SPACECRAFT , *MANEUVERS , *MULTIMODE , ELECTRIC PROPULSION , MILITARY CAPABILITIES , THRUST , CHEMICAL ANALYSIS , VARIATIONS , OPTIMIZATION , INTEGRATED SYSTEMS , COUPLING(INTERACTION) , MISSIONS


Subject Categories : Aerodynamics
      Operations Research


Distribution Statement : APPROVED FOR PUBLIC RELEASE