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Quaoar, I can't say I have many details at this time; But presumably it would be something like a habitat on the bed of a large truck.
This does result in a conflict if you're looking to use solar panels because it will be tough to carry around all the panels that you'll need. But then again most of the power would actually be needed for propellant production and not as much for the routine mission/science operations. Propellant production can occur pretty much anywhere on the planet because the crew can just drive there.
I wouldn't expect them to actually circumnavigate the planet, but it certainly would be well within the crew's ability to do so.
Wich kind of engine: electric or LOX-LCH4 internal combustion?
Merry Xmas!
I tend to agree with the latter, but not so much with the former. It depends just how efficient your engine is, of course, but for example the Timberwind proposal (Isp 1000 s, T/W 30) seems like it would be well-suited to an SSTO, although it's very questionable if you would get much payload, safety, or reusability out of the vehicle that resulted.
I know very few about nuclear thermal rocket: NERVA or Timberwind based spaceships have to be orbit to orbit spaceships, with habitat and rocket separated by a long truss with propellant tanks, to reduce crew radiation exposure, or may be compact and able to perform atmospheric entry and landing?
As we rapidly approach the MarsDrive plan, it also occurs to me that even better than doing suborbital flights might be to simply put your hab on wheels and drive it around. If your driving speed is 15 km/hr you can travel 1000 km in a few days and then park for an arbitrarily long period of time. Even if you desire to circumnavigate the Martian globe, it would take less than 100 days (Circumnavigating Mars is 60 days of continuous driving at 15 kph, so I'm allowing for slow stretches and detours) out of your 550 day surface stay to do so.
Now that's mobility. And Zubrin's hab masses about ten tonnes, comparable to a medium-sized truck. What I'm trying to say is that if you can build yourself a reliable enough propulsion system, a hab-on-wheels design really isn't that bad of an idea. 100 days of continuous driving at 15 kph is 36,000 kilometers (22,000 miles). There are cars on the road doing just fine with ten times as many miles on them, and this kind of one-speed, slow driving isn't particularly bad for an engine.
It's seems fantastic: may I have more details on your rover-habitat?
Space burial will eventually result in cremation, but it might take a spacecraft with it...
The first two options are the only realistic ones - well, you could return the body, but why would they be on Mars if they didn't have a connection to the planet? If it's a colonist we're talking about, they'll be planning to be buried or cremated on Mars; if it's a crew member... well, what was the standard procedure from navies, before they could fly the body out?
It's not possible to return the body in a 180 days mission, unless the ERV is so big to have a morgue. Oxigen is too precious to waste it for burning. So two option:
1) buring him/her after sealing in a plastic bag
2) putting him/her in a compost tank and recycling to fertilize the crops of the green house.
I don't foresee deployment of PV panels as a problem. Another point - if you have pre-landings the fuel production could be run over several years, reducing the power requirement, I would have thought i.e. if you thought the fuel production would take a year, were we to run that over 8 years, we might need only 12-15 Kws equivalent of PV panel.
How long can you store LOX-LCH4 on Mars equatorial latitude?
Quaoar:
You just made my point.
Of course the sabatier reaction is well known science. Of course it has been used Earthside for a long time. None of that is machinery we can use on Mars. It was designed for Earthly conditions.
My point is that the actual machinery necessary to make it work on Mars has never been designed at all, much less prototyped and tested. That includes the power supply and whatever gas compression machinery they finally select (not at all a trivial problem with an inlet density 0.6% of that here). All those missing support items are part of my point.
I'm not saying at all that it cannot be done, because it so very clearly can. And I hope it is, and soon.
But, I am saying that the necessary things to make it work reliably on Mars are not underway at all. It has to work very reliably at Martian conditions before you ask astronauts to bet their lives on it. Proving that your specific design actually works reliably takes time, effort, and money. It's called "engineering development" work.
There is a vast difference between a lab device that demonstrates feasibility, and an engineering prototype that verifies this thing will really work reliably. It's called engineering development, and not many scientists understand its nature, or how big an effort it really is. They were not trained in it. That's what engineers are trained to do, which is why there are two distinct titles: scientist and engineer.
Typical development, properly done, is at least one order of magnitude more effort, time, and expense, as any scientific feasibility demo imaginable. Sometimes 2 or 3 orders of magnitude. But really talented engineering teams can do it for about 1 order of magnitude.
You don't really find talented, efficient teams like that employed by the "big space" firms. Those guys usually cost you the 2 or 3 orders of magnitude.
GW
You are right, but your arguments may be applied to the whoole mission: we have a lot of expirence in entry and landing, but we never lended on Mars something heavier than Curiosity. A landing habitat of 15-20 mT has also to be designed, prototiped and tested. Even the rover may be an issue: for a more than a year mission, astronauts need a long range pressurizzed rover with a powerfull internal combustion engine, but we never built a LOX-LCH4 internal combustion engine, able to work in Mars climate and thin atmosphere, where cooling may be very difficoult.
I'm not an expert, but I think R/S to develop mission hardware will take almost 10 year and a lot of money, but no space agency has planned such an investment.
I doubt it. The Mars mission plans NASA has aren't too be taken seriously anyway, so I don't see why they Would address the issue.
I don't think you would need to bury the bags, since there's not much in the way of surface disturbance on Mars like there is on Earth.
Something else I've thought of would be the inclusion of gold microparticles in everything, including food. They're biologically inert and geologically rare, so their presence would be a sign of human contamination which would allow for some estimate of whether or not organic compounds found on site are indigenous or simply result from the human presence.
Plastic bags may be depolimerized by UV. So I hypothized buring. Gold microparticle inclusion may be a nice idea.
My biggest concern would be that placing waste outside the planet could result in contamination of the area, leading to false positives when looking for the presence of various kinds of organic compounds. It might be worth bringing lightweight, sealable plastic bags (in effect) to prevent contamination of the outside environment.
Something like the little plastic bags we use for the dog's waste, sealed and buried. It's simple and it may work.
Has NASA some kind of plan for this issue?
It seems not so epic like spaceship propulsion, ISPP or aeroshell, but it may be an interesting issue of a Mars manned mission.
If the habitat has a compost tank, garbage and feces may be used to fertilize the crops of an aeroponic culture in a sealed closed cycle.
But I doubt the first mission will have and aeroponic green house.
If not, how it is planned to manage crew's west and garbage, without contaminating the planet?
The one item we have been discussing here with little-to-no history behind it (so far) is propellant manufacture on Mars. That is why it is risky: no history behind it. Zubrin's bench-top lab device is not a proper prototype for something we could test, nor are the other similar devices. We need to build and test those prototypes. Now. Yet, no space agency anywhere is doing more than academic lab stuff. That kind of thing just doesn't qualify as an engineering prototype test.
GW
Sabatier reaction is very well known and it's used by chemical industry for more than a century. I think it will be not difficoult to build a bigger device and test it in the Mars atmosphere simulator of German Space Agency. The bigger problem may be the energy to run the pump and drive the water electrolysis: small 100 KW nuclear reactor vs. film solar panel carpet. The first may get a lot of political trouble, the second may be very difficoult to deploy automatically: a solution may be and ADEPT like deployable aeroshell-landing gear, with the filmsy solar panels on the internal side of the deployable heat shield, that will be exposed to the sun after landing.
http://www.lpi.usra.edu/vexag/Nov2012/p … cinski.pdf
The real problem is the absence of interest.
Interesting location, and beautiful picture. I pointed this out to a friend, who printed a high-resolution colour image and framed it. It's on his wall. But it's too far north. For warmth, and to avoid winter all together, I would like to restrict the landing location to between the northern and southern tropic.
Do you prefer to avoid winter because solar panels output may be to low to feed ISPP?
One issue is that subsurface water is plentiful close to the poles, rare close to the equator. But you want to be close to the equator. So how do you find both? Elysium Planetia is the bottom of the dried up ocean basin. Most of that basin is in the northern hemisphere, but Elysium Planetia is where it extends south and actually crosses the equator. The pack ice is just 5° north.
http://www.space.com/812-ice-packs-meth … -life.htmlThe ice exists in a block that resemble polar ice on Earth, according to the research team. It measures about 497 by 559 miles (800 by 900 kilometers) and averages up to 150 feet (45 meters) deep.
I should point out, I complained there was no location that met all of my criteria. Then members of NewMars reminded me of the pack ice. Ok. That's now my favourite location.
It may be interest to know how deep is the water pack under the regolith terrain. If it is few meters, it will be possible to project an ERV with a drill probe to melt ice and get water for ISPP. It dosn't need to bring LH2 from home.
The proposed Red Dragon mission will have a drill to probe the soil, for water searching?
Well, I could see there being an effect whereby the force that pushes the plume away from the centerline of the heatshield generates an increased pressure on its face. I can't say for certain, of course. Especially because of the supersonic flow conditions. I don't know whether that would be considered a good thing or a bad thing, either.
What do you think of the idea of canting the engines inward instead of outward, to increase the pressure on the heatshield?
According to the work quoted above, canting the rocket inward will cause the plume to act like an aerospike, reducing the drag: good for a take-off, not for a landing.
JoshNH4H wrote:I'm quite surprised that the mini-magnetospheric plasma propulsion idea hasn't gotten a lot more press/funding in general. It seems to me that it has the ability to have a higher thrust per unit power than any other form of electric propulsion.
And that's the problem. The only researchers to get funding have attempted to produce a magnetic sail. Instead of radiation shielding, they're trying to produce propulsion. But any sort of "sail" will always be very low acceleration, very slow. And when you talk to congress, as soon as you say the word "sail" they'll think of wooden sailing ships. But space is supposed to be high-tech, not old and slow low-tech. That is what they think. I haven't met any US congressmen in person, but I've gotten to know a lot of Canadian politicians. If you pitch this as a Star Trek force field that can protect against radiation, then you will get funding.
force field = funding
propulsion = dead
The most promising approach is to use the m2p2 not alone, but in assotiation with classical chemical rocket, like a sort of space motorsailer: chemical rocket insert the spaceship in a classical low energy transfer orbit and m2p2 enlarge the orbit shortening the transit.
http://www.lpi.usra.edu/publications/re … wash01.pdf
But the work above assume that m2p2 thrust is constant and indipendent from solar wind speed: the magnetic bubble would enlarge in low wind and contract in strong wind acting like a furling jib. But we dont know if it will happen really, and there will be some risk of missing the planet. So I think that in the first mission m2p2 will be used only as a shield for cosmic rays.
Hi to all,
I've found some interesting article on landing on Mars: supersonic retropropulsion may be good if the rockets fire not straight but inclined at 30° from the thrust axis, just like the Dragon Rider escape rockets, that may be perfect suited to land on Mars. In supersonic retropropultion the angled rockets slow the air flow around the shield moltiplicating the drag and acting like an air augmented rocket.
http://adl.stanford.edu/papers/JSR_Bakhtian.pdf
Another simulation based study shows that, for spacehip up to 40 mT and 10 m diameter heat shield, it is possible to land on Mars with direct entry and supersonic retropropulsion. Heavier spaceships has to do first an aerocapture and after an orbital entry.
Mars Direct, devised by Dr. Robert Zubrin and Dr. Baker, used a 180 day transit, 425 day surface stay, and 180 days back. Also bring empty sand bags and a shovel. Astronauts would fill them with Mars dirt and pile them on the roof. It would only be one layer deep, not 2 metres, but still provide some radiation shielding.
My criteria for location: low altitude (more radiation shielding), near equator (warmer, no winter), flat and smooth (safe to land), and identified subsurface water ice. Definately below the datum, the lower the better. Some valleys have water, but landing in a canyon is very dangerous. The only location that meets all this criteria is Elysium Planetia. Hellas Basin is deeper, but not within the tropics.
What about this nice place in vastitas borealis? http://www.space.com/1371-ice-lake-mars.html
Radiation exposure during transit can be reduced by launching during a year of solar minimum. Radiation in space measured by Mars Odyssey was 2/3 that measured by Curiosity. That's because Curiosity launched during solar maximum.
I have posted before about the mini-magnetosphere. Also posted a link to the University of Washington. But you're a medical doctor, so more qualified than me.
Elyseum Planetia may be very good: it's 1500-2000 meter below the MOLA 0 ( http://www.pianetamarte.net/mappature_p … _marte.htm ) and this is fine for landing and according to the Mars radiation map ( http://journalofcosmology.com/Mars130.html ) it's only 15 REM/yr. So the whole dose for a mission will be 35 REM/tr vs 33 REM/yer of Hellas Basin (without habitat screening).
Do you fear the winter because solar panels energy output may be to low for ISPP?
Hi Quaoar:
What I had in mind was a ship composed of docked-together modules, most of them propellant modules. The ship will be lighter on the return, and will need fewer propellant modules than it did outbound, but it will still need a lot of propellant. By stacking them up properly, one should still get a baton on the order of 150 m long.
Go see the mission plan I just posted over at http://exrocketman.blogspot.com a couple of days ago. Fig 19 shows a sketch of what I had in mind. Bear in mind that my design proposal recovers and reuses the manned vehicle in Earth orbit at the end of the mission. It's not a one-shot free return design.
Isn't Quaoar the name of a dwarf planet discovered recently in the Kuiper belt? It sounds familiar.
GW
Hi, your ship is very interesting.
Yes, Quaoar is the dwarf planet discovered by Chad Trujillo, who named it after a Tongva native american god, who create the world singing and dancing.
We normally talk about 180 day transits, rather than 120. The reasoning for this is that 120 day transits have excessively high delta-V requirements which makes them more-or-less unfeasible.
In this study ( http://www.marsjournal.org/contents/200 … 7_0002.pdf ) in 2020 an Earth departure delta-V is 3.76 km/s for a 180 days transfert orbit and 4.19 km/s for a 120 days transfert orbit: using a direct entry with aerobraking (entry velocity 7.8 km/s) and an ISPP for the return travel, I think it can be done.... with a ERV with LOX-LCH4 rocket with 3.7 km/s of exaust velocity and mass ratio of 7 instead of 5.5... Yes, You are right: it's more difficoult on the return travel.
a 180 days transfer is easier: it's also a safer free return mission: 180 EM travel + 425 stay + 180 ME travel : 30 + 11.8 + 30 REM = 71.8 REM/785 days = 33.38 REM/year
We are still below the 50 REM/year limit even with a 180 days transfer. Considering also that the 11.8 REM on Mars surface will be very less because the astronauts will leave in a habitat screened with Mars regolith.
Having said that, are these claims of radiation effect alleviation stemming from legitimate medical research, or are they proffered by the same people who are pushing "Homeopathic 'Medicine'", "Herbal Supplements", "'Alternative' 'Medicine'", or any of that nonsense?
Gingko is under study on protecting neoplastic patient of side effect of radiotherapy. Preliminary data may suggest in a future it can also be used on the astronauts, to mitigate the effect of comsic ray, but naturally it has to be prooved.
Because we won't have time to go through extensive trials, drugs that counter radiation strike me as something to use (if they can be determined to be non-harmful) on top of radiation protection measures that are adequate by themselves. Having said that, if there are harmless anti-radiation pills that we have good reason to believe will help the astronauts, then by all means!
I've wondered at times about using pressurized CO2, in its liquid form, at ambient Martian temperatures as radiation shielding while on-planet. Because the CO2 is everywhere the only mass you need to bring is a container and a pump!
Gingko is safe: its seeds are eaten for centuries by Japanese, and there are also gingko tablets like these in commerce ( http://www.saninforma.it/Sezione.jsp?id … neRif=2543 ).
Liquid CO2 is interesting: it may also be used as a coolant for the rover engine.
I'have found in this article an interesting Mars radiation evironment map: http://journalofcosmology.com/Mars130.html
On the Hellas Basin radiation are 10 REM/yr, so a fast transit mission (120 days travel + 600 days stay + 120 days travel) will have 20 + 16.6 + 20 = 56.6 REM/840 days = 24.2 REM/yr: well below the 50 REM/yr limit and only just a bit more of 20 REM years of ISS astronauts
From what I read, the galactic cosmic radiation (GCR) varies with sunspot cycle, every 11 years. Minimum GCR at solar max is 24 rem/year, and maximum GCR at solar min is 60 rem/year. NASA astronauts currently have a limit of 50 rem/yr.
We don't violate that limit by very much at all, worst case, and stay well under it most of the cycle. Close to max exposure, one starts bumping into career limits with younger astronauts if the mission runs over 2.5 years. And that doesn't take into account the half-sky shielding effect of the planet for the approximately 1-year stay at Mars, nor the slight shielding effects of spacecraft structures (admittedly very slight). Nor does it consider atmospheric shielding at Mars, which is more effective than any of us had hoped. But, the crew that makes this trip doesn't need to fly one like it again.
Radiation that kills is more likely a big solar flare event. The worst of these only needs about 20 cm of water for an effective shield. Any craft on a 2.5 year voyage will have water and wastewater tanks. You just wrap them around your designated shelter zone. The smart designer would make that the flight control station.
Radiation as a reason not to go to Mars is an canard and an excuse. We've known what has to be done for a few decades now. And we have known how to do it for those same decades now.
GW
Another strategy is to use some kind of drug that may protect cell from radiation. It's interesting to note that Ginkgo Biloba trees are very, very resistant to radiation (in Nagaski I've seen many ginkgos that have survived to the atomic bombing). Now ginkgo's very strong anioxidant properties are under study, and there are some evidences that may suggest it can be also used as a protection treatment for the astronauts against cosmic rays.
http://www.ncbi.nlm.nih.gov/pubmed/21716624
I find it disturbing that NASA still thinks it can send people into a 2.5+ year mission without at least some artificial gravity. Besides the zero-gee transits, each of which is near the demonstrated max exposure time, there is no data at all (of any reliability) to suggest that 0.38 gee for that 1+ year on the surface of Mars is "enough". If bed rest studies were so good, then our bones would soften and decalcify in bed down here the way they do in space. They don't.
You do not have to build giant Battle Star Galactica's no one could afford, or resort to Rube Goldberg cable-connected contraptions of questionable safety at best, to provide artificial gravity by spin. It is easily integrated into a practical vehicle design, even at one full gee, which requires 56 m radius at the tolerable 4 rpm spin rate. GW
As a physician, I also agree that in 4-8 month space travel, a spaceship must have some form of artificial gravity. The gee load during the atmospheric entry may be from 5 to 10 gee: too much for a deconditioned crew. On Mars the astronauts cannot go to a rehabilitation clinic to get physiotherapy: they must be in perfect physical condition to explore an alien world. Mulscolar hypotrophy and bone loss are not the only problems in microgravity: there are also the fluid shift that can cause sight loss for ocular deformation and optic nerve damage, anemy many other cardiovascular, ormonal and methabolic alterations. An alternative to spinning or tumbling the whole ship may be the short arm centrifuge, but we still have not reliable data on this kind of device.
On Mars, during the EVA, an astronaut with a spacesuit has almost the same weight on the Earth in normal clothes, so walking in spacesuit may give a good muscolar and bone load. To counteract the fluid shift caused to the Mars lower gravity, a promising strategy may be to give some 5°-20° of inclination to the beds where the astronauts will slip, with the feet in a lower position than the head.
You shape your vehicle of docked modules as a baton that spins end-over-end, with the habitat at one end. This is an inherently stable configuration, as anyone who has ever seen the baton twirlers at a football game can testify. It integrates well with staged-off empty tanks: your baton just gets slimmer. There's no need for a truss, just connect the tanks axially and laterally.
I really have to question why otherwise-intriguing mission designs (of all types and from many sources) so often continue to ignore this medically-devastating issue, yet an issue so easily resolved.
GW
Are you speaking about tumbling some kind of modular space ship like Grant Bonin's ship of Mars for Less?
If so, this may be very good for the MTV. But the ERV have to relay on the classical cable beetween the capsule and the bourned stage or on internal short arm centrifugue.
Ice worms were first discovered in 1887 on Muir Glacier in southeast Alaska by George Frederick Wright, a glacial geologist (who doubled as a theologian) in 1887. However, the discovery was more or less ignored for most of the 20th century. Only very recently has any real effort been made to subject them to thoroughgoing scientific enquiry.
The coastal glaciers that serve as ice worm habitat extend from Mount Rainier in Washington State to Alaska.
Ice worms, which are a relative of the common earthworm, have no eyes, so they don't see images, but they respond to light and dark. At a little less than an inch long (one to two centimeters), they are often described as looking like pieces of dark thread in the ice.
They have big mouths, said Shain, and their primary food source is the red algae that grows on glaciers. Their ideal temperature is zero degrees Celsius (32 degrees Fahrenheit); at 5 degrees Fahrenheit they start to disintegrate.
They spend their days burrowing up and down through the ice. Biologist Dan Shain remarks that "They definitely operate on some kind of Circadian rhythm, moving up when it's dark and down when it's light."
Ice worms propel themselves using setae, extremely small bristles that protrude from the sides of their bodies. Wriggling through fractured ice and snow crystals, they burrow as deep as three to six feet (one to two meters) beneath the surface of the ice. They have mysterious head pores which might be producing some sort of lubricant to help them move through the ice.
They can live in colonies of a few hundred thousand to 20 million, covering an area as large as 30 acres. No one knows how long they live. Beyond the occasional bird or two, the only threat to their existence may be global warming.
Although temperatures on Mars are probably too cold for our cosseted Earth-bound ice worms, one can imagine that something like an ice worm might be able to live out life in the huge Martian glaciers. If so, then once again it is unlikely that our presence will threaten them. It is probably a case of ourselves having to exercise a degree of caution in choosing our water sources and in filtering and sterilising the water.
Mars Express has found an ice lake http://www.space.com/1371-ice-lake-mars.html
It may be intriguing to hypothize some kind of martian ice worms, that breath a little amounth of oxigen produced via radiolysis or are anaerobian.
Hi Quaoar. Welcome to Newmars! I hope we see a lot of you in the future
Thanks a lot and excuse me for my poor English.
In fact, my take on the Curiosity results is that Radiation is not very big of a concern. What we've seen from the radiation results from the RAD instrument is that the radiation derived from a trip to Mars is an increased cancer risk of a few, perhaps 5%. I'd imagine that any astronaut would be willing to go for that, and for a mission of this groundbreaking nature a 5% increased cancer risk isn't even particularly significant.
I agree. 25 mSv/h on the Mars surface are almost the same than in LEO, but the astronaut can use regolith to screen the habitat (or ice if the will land in a place like this http://www.space.com/1371-ice-lake-mars.html ), so they surely will take less radiation than people on the ISS. Even the habitat of the rover may be screened putting the water and the LOX-LCH4 tanks on the roof and during the EVA the astronauts may use heavier isovolumetric suits, made in the same matherials of Bigelow habitats, having a quite good protection against 200 MeV solar protons. Curiosity landed at -4000 m of altitude but if the astronauts will land in a lower place (like Hellas Basin at -8000) where the athmosphere is denser, they will teke much less radiation.
Intelligently designing the habitat by putting the places where the crew will spend the largest amounts of their time in the middle, where there is the most shielding, and otherwise putting mass between the crewmembers and the directions from which radiation will be coming (The Sun in particular but also everywhere in general, depending what kind of radiation we're talking about).
In space, the magnetospheric idea is certainly a good one, if it could be done with low power expenditure. I wouldn't expect the technology to be ready for a first mission, and that's not particularly an issue, so far as I'm concerned. However, it would be nice for follow-up missions and routine transportation (when we get to that point) to be able to reduce the radiation experienced by members of the crew. I think it's a solid idea. I think it's also probably safer and lower mass than an electrostatic field.
I'm sure that magnetosphere is very promising and it eventually will work, if we will do R&D on it. But even without it we have a lot of strategy in cosmic rays mitigation: a double walled habitat with the water tank in the middle; building the habitat with long chain polyethilene based matherial ( http://science.nasa.gov/science-news/sc … paceships/ ). And we can also choose a fast transit mission: spending a litte more propellant, we can go to Mars in 4 month instead of 8, reducing the exposure of the astronauts ( http://www.marsjournal.org/contents/200 … 7_0002.pdf ).
Using all theese strategy, during the whoole mission, the astronauts will take less radiation than Valeri Poliakov, who spent 678 days in LEO and is still alive.
You shape your vehicle of docked modules as a baton that spins end-over-end, with the habitat at one end. This is an inherently stable configuration, as anyone who has ever seen the baton twirlers at a football game can testify. It integrates well with staged-off empty tanks: your baton just gets slimmer. There's no need for a truss, just connect the tanks axially and laterally.
GW
It is possible to sobstitute the rigid baton with an enflatable Bigelow like long boom, that may be stored in the MTV nose during the launch, and can be connected to the bourned stage after the transfer orbital inserction?
Theoretically speaking, it is possible to apply the same architecture of Mars Semi-direct to Venus: a floating habitat enter in Venus athmosphere ad floats at 50 km of altitude: it produces the LOX-CH4 propellant for a little ascender, using the atmospheric CO2 and the hydrogen of H2S clouds, while the crew explore the surface of Venus via robots or directly, utilizing a modified atmospheric diving suit, with a Sterling cycle cooling system, or a via a special aerostat with an actively cooled atmospheric pressure habitat.
When the next synodic period arrives, the crew leaves the floating habitat using the ascender and rendez-vous with the orbiting ERV.
This mission is very expensive, more and more than a Mars Direct Mission, and has a lot of technical challenge to overcame. I think nothing is impossible, but it is wiser to go Mars first.
Hi to all, I'm Quaoar,
I'm an Italian physician and amateur SF writer, very interested in space exploration.
Surfing in many space forums I found a lot of people posting that a manned mission to Mars is almost impossible for cosmic ray hazard, as found by Curiosity.
Cosmic rays hazard is real, but there are also solutions: http://earthweb.ess.washington.edu/spac … elding.pdf
the devicie proposed in the article by Dr. Robert Winglee is an electromagnet with an elicon antenna inside and a gas injector. The elicon antenna ionizes the gas, that inflates the magnetic field of the electromagnet, creating a kilometer size plasma bubble, that protect the spaceship from solar and galactic cosmic ray. The devicie has the dimension of a water melon, a weight of almost 30 Kg, and needs a pulsatile power of 100 KW, that can be easly suppiled by 6-8 KW solar panel. So it can be easly implemented in a manned Red Dragon.
I don't know why it is not considered for a Mars reference mission.