Abstract While there are many challenges involved in planning human missions to Mars, the problems involved in launching, transporting, landing and returning large masses to and from these bodies appear to be perhaps the most formidable of these hurdles. Propulsion systems are utilized in trans-Mars injection from LEO, Mars orbit insertion, entry, descent and landing at Mars, ascent to Mars orbit, Trans-Earth injection, and entry, descent and landing at Earth. For any specific transfer there is an associated Δv. The propulsion system dry mass and specific impulse can be used to calculate the mass of propellants needed to transfer a payload for any Δv. Using an ideal model with circular Earth and Mars orbits, approximate values of Δv can be estimated for Earth departure and Mars orbit insertion. More realistic models were developed by JPL. Propellant requirements are estimated for various steps in a human mission to Mars using chemical propulsion or nuclear thermal propulsion. Gear ratios {(initial mass)/(delivered payload mass)} for each step are analyzed. Solar electric propulsion for Earth orbit-raising is reviewed. Ascent from the Mars surface is analyzed in detail. Propellant requirements for ascent are estimated in detail.
Getting There and Back
2nd ed. 2016
2015-10-30
73 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Springer Verlag | 2023
|Springer Verlag | 2024
|Online Contents | 2000
IuD Bahn | 2006
|Online Contents | 2004
|