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Nanosatellites, and especially CubeSats, at low earth orbits (LEOs) are a lowcost option for monitoring atmospheric and environmental conditions aroundEarth. For instance, data for weather forecast reports can be obtainedperiodically with these kind of small satellites. Therefore, to academicinstitutions, universities, etc., this fact makes nanosatellites a veryattractive way for researching with a moderate budget.  In this project we compute orbital lifetimes (or simply lifetimes) forhypothetical missions involving nanosatellites at LEO, focusing our attentionon exploring regions along the equatorial line. Thus, in the framework oforbital mechanics, we show the viability for these kind of missions in a longand a short term. Applications are projected for countries in northern SouthAmerica, central Africa and islands/countries in southern Asia.  To compute lifetimes, we take into account three effects: i) gravitational,ii) Earth deformations and iii) atmospheric density. These effects are includedin the motion equation for a nanosatellite around Earth. After solving thisequation for initial altitudes in 200-800 km above mean sea level (AMSL), wecompute and report flight times to arrive at 150 km AMSL. These results aredefined here as lifetimes and they are calculated for differentatmospheric-density profiles according to experimental data and estimations.  In conclusion, we find lowest and highest lifetimes for hypothetical missionsinvolving small satellites at LEO orbiting along the equatorial line, andpropose upper limits for density relative uncertainties in order to estimatereliable lifetimes.

Atmospheric density uncertainty effects on the orbital lifetime estimation for CubeSats at LEO