The existence of an optimum altitude for maximum lifetime and the effect of vehicle parameters on this altitude are investigated by varying the parameters within realistic limits and plotting the results on satellite lifetime versus orbital altitude coordinates. Only circular orbits are considered. For a chemical rocket sustaining system, maximum lifetime is achieved when the satellite is placed as high as possible. For an ion propulsion sustaining device, a maximum value of total lifetime results when the satellite is placed in orbit in the neighborhood of 10 nautical miles below the maximum altitude attainable. The maximum value is of the order of only one percent greater than the value of total lifetime that results when the satellite is placed as high as possible. For both sustaining systems, a significant increase in total lifetime at lower altitudes can be achieved. (Author)
Orbital Altitude for Maximum Lifetime of a Satellite Capable of Sustained Thrust
1965
2 pages
Report
No indication
English
SATELLITES (ARTIFICIAL) , ORBITAL TRAJECTORIES , LIFE EXPECTANCY , HIGH ALTITUDE , VELOCITY , ROCKETS , ION ENGINES , DRAG , ATMOSPHERE , EQUATIONS , THEORY , THRUST , PROPULSION , DENSITY , WEIGHT
Earth orbital satellite lifetime
TIBKAT | 1964
|Earth-orbital lifetime and satellite decay.
NTRS | 1968
|Earth-orbital lifetime and satellite decay
Engineering Index Backfile | 1968
|