How to calculate the lowest possible altitude a satellite can orbit at due to aerodynamic heating if provided with a sufficient propulsion system?
What "unique control system" modulated GOCE's thrust to compensate for variable atmospheric drag? How did it know how to modulate it?
For using the acceleration due to drag formula, which coordinate frame should the satellite's position and velocity vectors be in?
Does it count as orbital flight if one reentered the atmosphere due to its drag after about 1 revolution?
What factors would contribute to a spacecraft's ability to maintain a very low orbit (VLEO) or at least orbits with very low perigees?
What is Direct Simulation Monte Carlo and why is it a good method for simulating spacecraft drag in VLEO?
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