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- W2773874265 abstract "This paper presents how to model the gravity and atmospheric numerical models for simplifying the problem and decreasing the computing error in the orbit simulation process. The perigee aerobraking from 80 km to 100 km with and without a plane-change are included for comparing the results. The results show the complicated gravity (36 by 36) model can be simplied into 2 by 2 or J2 only under some special assumptions and several circumstances, with no resulting accuracy penalty. Using the simplified model into aerobraking trajectory for simulation, the results show the same good answer as the results of using full gravity model does. The Planetary Observer High Precision Orbit Propagator (POHOP) and the Planetary Observer Long-Term Orbit Propagator (POLOP) will be utilized for this task The atmosphere extremes are modified in POHOP's density model, so that below 90 km, the MSIS90 is adapted. A comparison is made using the POHOP simulation program to perform an aerobraking study in the perigee corridor range of 80 to 100 km." @default.
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- W2773874265 date "1995-12-01" @default.
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- W2773874265 title "Gravity and Aerodrag Sensitivity Analysis for Satellite Aerobraking Orbit" @default.
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