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1., The plan involves launching an unmanned Earth Return Vehicle (ERV) directly from Earth's surface to Mars using a heavy-lift booster (no bigger than the Saturn V used for the Apollo missions), containing a supply of hydrogen, a chemical plant and a small nuclear reactor.
==> Atomic reactor launchd to space? Try to sell that to the general public! Even the plutonium thermo-decay powered satellites are dangerous enough, we need not more chance for radioactive pollution through launch failures!
Jonathan Derwent Arthur Clarke (talk) 08:00, 29 November 2008 (UTC)The reactor stays on Mars[reply]
2., A second vehicle, the Mars Habitat Unit would be launched on a high-energy transfer to Mars carrying a crew of 4. This vehicle would take some 6 months to reach Mars. During the trip, artificial gravity would be generated by tying the spent upper stage of the booster to the Habitat Unit, and setting them both rotating about a common axis.
==> That's not artifical gravity, that is only good to make people crazy by constantly confusing their inner ear (the balance sensor of the brain). They will get nausea, curse Mr. Coriolis and vomit all the way to Mars and have faces greener than ufonauts upon arrival.
3., the Habitat Unit aerobraking into Mars orbit before soft-landing
==> Mars has only 1/100th dense athmosphere as the Earth. Big structures, like a crew carrier spaceship cannot aerobrake there, they will need huge retrorockets and you can afford that weight with current technology!
Jonathan Derwent Arthur Clarke (talk) 08:00, 29 November 2008 (UTC) A long thin vehicle is very effective as it generates more lift and can therefore aerobrake for longer.[reply]
4., The soviets wanted to make manned moon landing with multi-ship approach (2 Proton ELVs) but they abandoned it because the risks were too much due to complexity. Yankee should consider the 1979 iranian hostage rescue helicopter fiasco for a familiar story on how complexity skyrockets risks.
Jonathan Derwent Arthur Clarke (talk) 08:00, 29 November 2008 (UTC)The point being???[reply]
5., Mars Direct has several drawbacks: most importantly, Zubrin suggests that the ERV cabin has a mass similar to the Apollo capsule, yet it is expected to house four people for more than six months. Secondly, he wants to use aerocapture on a manned vehicle (the Habitat); aerocapture is potentially risky and has never been attempted yet, even on unmanned craft. Thirdly, he envisages launching hte crew onboard the habitat, thus depriving them of a launch abort system (this problem is easily solved by launching the crew separately, for example on an Orion spacecraft). I would like to add some of these to the main article but I haven't found suitable sources yet. Batoom
Jonathan Derwent Arthur Clarke (talk) 08:00, 29 November 2008 (UTC)The small size of the ERV was one reason why MD was rejigged as Mars Semi-Direct. Use of atmospheric breaking is no more inherently risky than any other metod of slowing down. Every Mars lander to date has used the atmospheric to brak with during entry. The original proposal did not include a launch escape facility for the crew, but this was entirely in keeping with the Shuttle philosophy of the time.[reply]
Jonathan Derwent Arthur Clarke (talk) 07:37, 29 November 2008 (UTC)The last section writes about a one-way proposal by a "Dean Unick". No reference is given, and I can find no mention of this proposal as a peer-reviewed study anywhere. I doubt its validity.[reply]
6., Just a thought: Should this page have a "Criticism" section? If so, what should go in it?
This article does not cite its references. --85.82.179.226 (talk) 00:58, 28 October 2008 (UTC)[reply]
The references are there in the links,but not at the bottom of the page. —Preceding unsigned comment added by Jonathan Derwent Arthur Clarke (talk • contribs) 04:37, 5 December 2008 (UTC)[reply]
Could the cost of the $55 billion be broken down? For example, is the cost of developing and building the Saturn V like lift vehicle included in the $55 billion, or is that a separate cost? Since we don't currently have that lift capability anymore, that will have to be developed, and that will not be cheap - projected cost to develope the Saturn V rockets was an estimated $46 billion in 2005 dollars . (The shuttle fleet is being decomissioned, and will not be available.) —Preceding unsigned comment added by 66.51.147.97 (talk) 20:26, 2 May 2010 (UTC)[reply]
Why does this article bring up "proponents of the design" in several paragraphs? Isn't it already clear that Mars Direct is a plan/proposal? Moreover, even those who are not "proponents" of Mars Direct might suggest some of the same strategies, such as creating artificial gravity. I am therefore removing the "Proponents of the design" throughout. Please feel free to contact me to discuss further if you desire. Besh (talk) 22:35, 29 March 2012 (UTC)[reply]
There is phrase about 6 month Low energy transfer fly from Earth to Mars
6-month long low energy transfer trajectory
But isn't it too fast to be a Low energy transfer? Hohmann transfer has similar total time, and the article Low energy transfer says:
The drawback of such trajectories is that they take longer to complete than higher energy (more fuel) transfers such as Hohmann transfer orbits.
`a5b (talk) 00:45, 24 December 2012 (UTC)[reply]
Hi,
Just noticed that the article refers to the imdb page of the Mars Underground movie, while the vide is up on youtube and looks like it is legal. Can I add this as source? http://www.youtube.com/watch?v=uDWvsdEYSqg
--K0zka (talk) 20:47, 19 August 2013 (UTC)[reply]
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