Moonguy Posted July 16, 2021 Share Posted July 16, 2021 Consider an unmanned lunar cargo lander that delivers 5,000 kg to the lunar surface. The delta-v for landing from a low lunar orbit is 2,100 m/sec. and the Moon's gravity is .16 Earth's. Now, consider that same lander used to land a payload on Mercury from a low Mercury orbit where the delta-v involved is 3,200 m/sec. Mercury's gravity is .38 Earth's. All of the physical characteristics of the lander must remain the same, only the payload mass can be altered. How much payload must be off-loaded to accomplish the landing? Thank you. . . Link to comment Share on other sites More sharing options...
Enthalpy Posted July 31, 2021 Share Posted July 31, 2021 You need a little bit more data : The Isp of the engine The inert mass of the lander Then, you apply Tsiolkovsky's equation: Mbegin / Mend = exp (deltaV / Isp) where Isp and deltaV use the same unit, and M includes the inert mass (and the remaining propellant to be accurate). Landing isn't the big difficulty for Mercury. Arriving on Mercury orbit takes a huge delta V, normally done by many flybys at Venus and Earth. Or you use a better propulsion: scienceforums and following messages, with a hectares solar sail My sunheat engine would be good too. A more efficient script meanwhile to leave Earth: scienceforums Thermal design on Mercury is a huge difficulty too. Better land during nighttime and leave or have finished everything before daytime. Link to comment Share on other sites More sharing options...
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