While there are many challenges involved in planning human missions to Mars, the problems involved in launching, transferring, landing, and returning large masses (including cryogenic loads) and crew to and from these bodies appear to be perhaps the most formidable (and costly) of these hurdles. Propulsion systems are utilized in trans-Mars injection from LEO, mid-course corrections, Mars orbit insertion, entry, descent and landing at Mars, ascent to Mars orbit, rendezvous and crew transfer in Mars orbit, Trans-Earth injection, mid-course correction, 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 estimate 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. Based on this type of analysis, the initial mass in Low Earth Orbit (IMLEO) can be estimated for any specific mission plan.
Getting There and Back
Springer Praxis Books(formerly: Springer-Praxis Series)
2023-01-02
73 pages
Article/Chapter (Book)
Electronic Resource
English
Springer Verlag | 2015
|Online Contents | 2000
British Library Online Contents | 2009
|IuD Bahn | 2006
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