Optimization of the propellant reorientation process can provide increased payload capability and extend the service life of spacecraft. The use of pulsed propellant reorientation to optimize the reorientation process is proposed. The ECLIPSE code was validated for modeling the reorientation process and is used to study pulsed reorientation in small-scale and full-scale propellant tanks. A dimensional analysis of the process is performed and the resulting dimensionless groups are used to present and correlate the computational predictions for reorientation performance.
Modeling of Pulsed Propellant Reorientation
1989
19 pages
Report
No indication
English
Rocket Propellants , Fluid Mechanics , Mathematical models , Propellant transfer , Reduced gravity , Fluid management , Fuel control , Impulses , Computer programs , Cryogenic rocket propellants , Fluid dynamics , Liquid sloshing , Orbit transfer vehicles , Program verification (Computers) , Propellant tanks
Modeling of pulsed propellant reorientation
AIAA | 1989
|Modeling of pulsed propellant reorientation
NTRS | 1989
|Modeling of pulsed propellant reorientation
NTRS | 1989
|