Continuous and discrete forms of the propellant longevity equation are derived. Expressions for the propellant mass decrement equation are developed for both spherically symmetrical and oblate diurnal atmospheres. The result for the oblate diurnal atmosphere is applied to the discreet form of the propellant longevity equation to provide numerical examples illustrating their application to several areas of mission planning.
Low-Altitude Earth Satellite Propellant Longevity Prediction with Application to Flight Profile Trade-Off Analysis
1983
23 pages
Report
No indication
English