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#276 Re: Human missions » Post central for information on CEV IV - Before thread #3 melts down » 2005-10-06 02:33:48

Grey's story reminds me of a passage in Macbeth, "A tale told by an idiot, full of sound and fury, signifying nothing."

He talks alot but it all basicly comes down to this.  Some (not necessary alot) redesign and testing are necessary before the Stick can go forward.

Well duh. roll

Who would have thought that some design and testing would be necessary in the creation of a new manned space vehicle.  The objects he raises are trivial and minor.    But I mean if NASA managed to pull of the construction of the Shuttle and what not in the first place, I bet they can manage the trivial adaptations.

#277 Re: Single Stage To Orbit » Realistic solutions to the difficulties of SSTO? » 2005-10-06 02:17:00

Dear God I hope Drexleresque nanotech isn't required, because we aren't having that... ever.  I would put good money on current and future impossibility of machine-phase matter or any other such nonsense.  Drexler is a smart guy, no doubt, but he doesn't know ^#(@ about chemistry.

I wouldn't worry to much about lighting strikes though.  The conductivity of the cable is not necessarily a nano scale phenominon, at least not when you are comparing the macro-cable to macro-lighting.  Proper-construction could insure that the cable was non-conductive to lightining strikes.  Ancoring the cable in a calm area and a system of lighting rods could also help.

As for mono-atomic oxygen I wouldn't worry to much about the corrosive effect.  It's very sparse and so could not eataway at the cable to quickly in any event.

-------

I think it's important to point out that the Macro-scopic cable can (and should) have very diffrent properties then a Microscopic nanotube.  The cable can encoporate diffrent materials into it's structure and can utilise diffrent typse of nanotubes to achive diffrent effects along it's length and cumutivly.

#278 Re: Interplanetary transportation » Ion Engines as Maneuvering Thrusters » 2005-10-04 10:32:10

The only place I could see an Orion using one would be if you had an ion-tug drag the vessle away from the planet before firing up it's engines due to enviromental concurnes.

That is exactly were I was going.  Please continue to explain this.

Well fireing of a nuke could potentialy cause problems for any nearby satilite and certianly trouble for the construction station.  So it make sense to move the thing away before firing.  This is where an ion engine might come in.  But it wouldn't make sense to incoporate it into the ship, as it wouldn't be needed for most of the rest of the journey.  It would be a first stage of sorts.  And since moving stuff around in orbit is something we are going to want to do eventualy, it makes sense to have a dedicated tug to do this with, eventualy.  Of course all this assumes the Orion was built in space, if you launched it from the ground, throw all this out the window.

I didn't mean maneuvering as in quick turns, but as in moving away from a planet or making a 180º rotation, slowly.  The ship could carry its own ion engines to do so, yes?

Well you see those two are really VERY diffrent kinds of manuvers.  A quick (or slow) rotation takes drasticly less Delta-V than changing the orbit does.  This is why the spaceshuttle carries two diffrent sorts of engines to acomplish these manuvers.  As I said before, ion engines have to little power/thrust and/or specific power to make them worth using as a RCS, and an Orion is to big to consider using them as a OMS.

Furthurmore, what type of thruster would needed for slightly quicker turns, for, e.g., dodging a small asteroid that is detected ahead of time to be on a collision course with the ship?

The only diffrence bettwen a quick and a slow rotation is the rate the energy is applied, ie. thrust.  The delta-V is exactly the same.  This amount of energy is so small in comparision to the ships mass, that it generaly doesn't make any sense to go with efficent but slow engines like an ion engine.

In terms of dodging asteriods, frankly you wont do it.  Space is BIG, and EMPTY.  So any asteriods that cross your orbit you are going to see coming a LONG way away.  In fact unless you specificly decied to pass by an asteriod, there is realy no chance that you are going to come into contact with one.

The only time this wouldn't be true is when traveling at fraction of C in bettwen solar systems.  Stuff IS probably out their (although we have no idea where and how much), and hitting it would be a bad idea even at some small fraction of C.  However at those speeds (and with a vessle the size of any interplantery spacecraft ie. >1000MT) doging is impracticle, and most studies have looked at protection and/or deflection/destruction of incoming particles.

#279 Re: Interplanetary transportation » Ion Engines as Maneuvering Thrusters » 2005-10-03 22:21:11

I suppose it depends upon what you mean by manuvering.  If you mean simply changing the orientation of the vessle such as what the shuttles Reaction Control System (RCS) do, then no ion engines are probably not the best choice.  Changing the facing and attitude of a spacecraft, even a large one such as an Orion takes a very small Delta V,  <1m/s.  Which is insignifigant when compared to the total Delta-V requirment of most space-mission ESPECIALY those that an Orion type vessle would undertake.  Thus other qualities of the engine become more important than it's ISP.  Specificly it's specific power or thrust/weight ratio and the specific power of it's fuel.  Chemical engines far out-perform ion engines in these respects, and that is why it is what all (to my knowledge) satilites and spacecraft have used them.  Although some satilites requirments for this sort of manuvering are so low that it can be handled entirely with gyroscopes.  Perhace an ion RCS would make sense on a VERY large spacestation of some sort,.  They could be used to help spin it up and what not which could take a fair amount of energy as well as more conventional manuvers, be we are talking 2001 Space-Oddessy sized staions here.  You would want to rock such a boat to fast either.

For minor (and not so minor) corrections in orbit inclination and what not, ion engines are a good choice, although probably not for a vessle the size of Orion.  These sorts of manuvers (which are handled by the space shuttles OMS) take considerably more delta-V.  Generaly >1m/s on up to escape velocity for the planet.  Most Orion type vessles are so large that it is probably worthwhile to fire off a couple nukes to achive any major changes in it's orbit.  Other more minor changes probably should be made as it is probably more worthwhile to bring any smaller objects to it rather than the other way around.  Also even with the larger Delta-V requirments of these manuverse most satilites still don't do enough of them for an ion engine to make any sense.

But for a satilites/probe that has to make alot of manuvers (such as one exploring some of the outer-system) or for a tug (which likewise has to make lots of orbit adjustments.  An ion engine is a good choice.  The only place I could see an Orion using one would be if you had an ion-tug drag the vessle away from the planet before firing up it's engines due to enviromental concurnes.

#280 Re: Interplanetary transportation » Why don't we go to space in one of these babies? » 2005-09-30 23:00:37

I read a story about a similar concept, suspending a gigantic railgun in the upper atmosphere and using it to deliver cargo into orbit.  Far-fetched I know, but presumably if you did build such a gigantic device it's own mass would probably be enough to dampen the majority of the recoil.  All the air-friction from the massive ballons would also help out.  To me the biggest conceptual problem (if you accept actually building something so large so high in the sky) would be keeping the gun stable for firing.

That and practical transportation of people, things, and (most importantly) power up to it as well.

#281 Re: Human missions » One man one way suicide mission... » 2005-09-27 18:59:08

Well I'm not quite so pesimistic.  I think a one-man one-way mission is quite possible.  Although if you want the person to stay their indefiently so resupply is going to be needed.  It's not just a matter of chemical degredation (although that is a part) it's a matter of mechanical failure.  The moving parts on your fan's/pumps and what not will eventualy fail.  It's no so much a matter of if, it's a matter of when.  The rest of the components likewise have limited lifetimes, the Rovers, your powersource, tankage, whatever.  They can be made tough, but they can't be made unbreakable.

So some resupply is going to be necessary.  You would want some anyways just incase some no-predictable accident happened, such as a pressure loss in your Greenhouse, killing all your plants, or whatever.

But I think the more important question is why?  That one person would probably have to spend the vast majority of his time doing maintance and what not necessary to his survival.  He would have little time to do any science.  Also the sanity of anyone who wants to sign up for such a suicide mission must be called into question.  Suicide is not a sane/logical course of action, and we definetly want our first man on mars to be both sane and logical.

#282 Re: Interplanetary transportation » Antimatter - More viable than fusion? » 2005-09-27 03:30:32

I don't know about all this.  Your solution of dragging the crewed portion behind the engines is inovative, and does have some advantages, such as possibly being able to use the engines as shield from some of the comsic radiation and debris you can encounter when crusing around a signifigant faction of C.

However you lose a serious amount of thrust/efficency and you have to have at least 3 engines instead of one.

---

In the end I think the best solution is what I recomended earlier, just seperate the crew from the engines as much as possible.  Any anti-matter/photon engine is going to put out an insignifigant amount of thrust, so putting the crew out on a boom along way from the engine should be that much of a challenge.  The hab is going to need some serious radiation shielding just due to the long amounts of time it is going to spend in space, and this should probably be sufficent.

GCRN is also right that for some of the extreamly high energy photon's given off by the engine no shielding tricks or fancy shapes of any reasonable mass are going to impeed these particles.  However, if you move far enough away, it won't matter.  Enough distance will allow you to doge the majority of them.  Yes the crew and hab will still get hit by the high-energy photon, but just one or two of these is not a problem, as they body (and equipment) can adjust and correct whatever ionizing effects it might have.

#283 Re: Single Stage To Orbit » Realistic solutions to the difficulties of SSTO? » 2005-09-26 05:33:19

Cyclic ozone shows alot of promise, but it's still quite aways out.  I do remember reading a paper that that detecting the presences fo cyclic ozone, proving that the theoritcal molecule may indeed be possible.  But we are still along way from producing it ourselves, much less on the scale necessary to put a rocket in orbit.  Which, I might add, are to very diffrent things.

------------

My favorite idea for a TSTO concept is to have the carrier plane to be similar to the shuttle external tank.  That is, the vehicles main rocket engines are actualy placed on the second stage, with the primary stage serving primarily as a large fuel tank.  Operation would be something like this:

#1.  TSTO craft takes off underpower from the main stages air-breathing turbojet engines.  If practicle these might be fuled by liquid hydrogen to eliminate the need for tankage for more conventional jet fuel.  It then accelerates and rises to the out edge of their envelope.
#2.  At this point the secound stage's rocket engines take over, with their fuel provided primarily the large tanks on the first stage.
#3.  At the appropriet time at the edge of space the two stages seperate, with the first stage returning to earth to make an un-manned powered landing with it's conventional engines, and the second stage continuing untill it reaches escape velocity, powered by it's rocket engines and fueld from it's own (smaller) tank.

This scheme alows a TSTO to orbit craft to get most of the benifits of staging without having to carry along extra engines.  Unfortunatly it subjects the first stage to hypersonic flight and possibly a mild re-entery.  And it doesn't necessarily make the turn-around time any better.

#284 Re: Terraformation » Provide the Moon with atmosphere - oxygen one » 2005-09-22 01:38:06

While I agree that the plan to add an oxygen atmosphere to the moon is an ambitious and exotic one, that doesn't necessarily mean it is impossible.  It is to simplistic to look at the current day-night cycle of temperature on the moon and the reject the idea as impossible.    This is the everyday logic which Karov was referring to.

For one the addition of an atmosphere will add a huge heat sink to the planet which it currently does not posses.  A large oxygen atmosphere will do a much better at retaining heat and maintaining a common temperature than the ground will.  This is due to both it's superior Specific and Volumetric heat capacity AND because the solar radiation will be spread out across a much larger amount of mass then it is currently.

Also, an atmosphere is obviously not constrained to remaining in one location as the ground is.  As gasses are heated they expand and cooled they contract.  The expansion (which results in a rise in pressure) will force the hotter gases over to the cooler side of the planet, which will create weather on the planet, which has a moderating effect on overall temperature.  Although these storms may be sevear without rotation and the coriolis effect, there will be no hurricanes on the moon.

The movment of air also allows heat to be transmited by convection which is by and large the most effective method of heat transfer.  Currently on the moon heat is only transmited by conduction, which is not very great in dirt.  The action of an atmosphere will certianly be several orders of magnitude greater.

It should also be rembered that the moon's much smaller diameter ~3500km, about 1/4 of Earth's, makes for a much smaller area for the heat to be transfered in.

All of these reasons make you simplistic reasoning inadiquate for the challange at hand.  And we have not even begun the discussion of artifical methods that could be employed (such orbital mirrors and shades).  Most certianly this is an exotic and ambitious project that we wouldn't be looking at doing for the next milliniea at the earliest.  But nearly all terraformation projects are so, since they are on a scale so much larger than what we have done before.  And rejecting it out of hand (much less making fun of someone's spelling) is uncalled for.

#285 Re: Interplanetary transportation » WARP DRIVE, AHEM! » 2005-09-22 00:45:38

Hmm... alot of points to respond to her.

#1.  Alternitive law of electromagnetisim (Dook)
What you propose might be intresting, but all expermintal evidence points to electromagnetic wavelengths existing along a spectrum (a line) not a circle.  Wavelengths increase with a limit at positive infinity, and decrease with a limit at zero.  In any case even if it was not so, it's not mathmaticaly possible to progress from beyond positive infinity back around to zero or negative infinity.  And again there is no conclusive evidence of negative energy even existing.

#2.  Gravity waves (Dook)
Indeed we should be able to detect the Gravitational "waves" produced by massive objects, or objects traveling at very high speeds.  Their presences has been proven  indirectly at least, by measurment the orbits of binary pulsars and the like.  The problem here is that Gravity is such a weak force it takes extreamly massive/fast moving objects to create effects that are detectible, and thankfully such objects are far from our Earth.  So far all direct attempts at detecting it have been failures.  It is currently an open question as to the speed at which these "waves" propigate from their source, but most reaserach points to their speed being very close if not equal to C.  Even if they did travel FTL, utilising them would be difficult given the massive energies necessary in creating detectible waves at great distances.  Of course this is the part of GR that is in most conflict with Quantum mechanics and research is still progressing.

#3.  Zero Point Energy
The concept of zero point energy arrises from the uncertian principle.  If we accuratly measure the energy inside a volume to be zero, then the uncertianty in it's position must be infinite, placing it outside the box.  To avoid this paradox quantum mechanics dictaes that this energy must be greater than zero, hence zero point energy.  This energy is NOT negative as that would create a whole new paradox.  There is some slim hope that energy may be extracted from this phenominon, but I wouldn't hold my breath.  Likely it will take as much or more energy to extract the energy as you get.  Local imbalances in this force may be the cause of some effects such as the Casmir effects.

#4.  Virtual Particles
Virtual particles are temporary stages in the interaction of elementry particles.  They generaly can be thought of as a means of transmiting the information of these interactions.  Quantum Mechanics predicts a field of these anti-particles swarming across our universe.  In order to perserve the baryon number these particles always come in particle anti-particle pairs.  In some cases these two particles can be seperated and become "real" however this always requires the expenditue of at least an equal amount of energy.  And again the imbalances in this force may be the cause of some effects such as the Casmir effects.

------------

It's very important to note that all of this stuff is on the forfront of Quantum and Theoritcal physics, and our models and understanding of it may change.  However there are quite a few things that probably will NOT change. 
No FTL travel.  Special Realitivity has gobs of experimental evidence backing it up and so it's postiulates are not likely to fall.  The nature of the grandfather paradox's this creates isn't likely to go away either.
Concervation of Energy.  Another concept with even more backing behind it.  We are not likely to get energy from nothing (or from ZPE or Virtual Particles or anything else).  The laws of thermodynamics are pretty solid.

That said, work in Quantum, Theoritcal, and even String Physics may shake things up alot on the sub-atomic scale.  General Realtivity may even be disproven or replaced in a general sense.  But I agree with most respected physicits and doubt there will be any major shake ups to the above two vital principles.

#286 Re: Human missions » NASA's Moon Mission » 2005-09-21 22:02:11

Well the biggest problem with using our current methods of Titanium refining on the moon is probably not lack of Hydrogen or Chlorine to carbochlorinate the mix, since it can likely be recycled, but the Coke which supplies both the heat energy and the carbon cannot easily be recycled.  The heat we could replace, but reduced form of Carbon is harder to come by, especialy on the moon.

It's the same story with nearly all current metal refining techniques which nearly all rely upon some form of Pyrometallurgy, namely roasting the impure Ore's with coke.  Coke's role as a source of a Carbon reducing agent is primary in nearly universial in metal refining process, which is unfortunate since Coke is not likely to be found on extra-terrestial enviroments.

In the case of Titanium however, there is some promise.  The two earliest methods of refining Titanium the Hunter and the Kroll process, both rely upon pyrometalurigal techniques and so are not very usefull to us in space.  However, the new FFC Cambridge Process does hold much promise for use on the moon.  This electrochemical method uses less energy, is more efficent, and faster then the current Kroll process.  And like most electrochemical process, it is possible to recycle nearly all of it's important chemical componets.  The only element that is potentialy wasted is the evolved oxygen which on the moon will can be captured as a usefull gas.

#287 Re: Interplanetary transportation » WARP DRIVE, AHEM! » 2005-09-17 04:43:40

To be honest I'm not sure I'm completely understanding all that you are trying to say but I'll reply to the points I understand.

#1.  Causality not necessary.
I don't know how you can claim this, causality, the principle that things happen in response to things that cause them is absolutly vital to a logial understanding of the universe.  Causality is litteraly the undminning of not just science and physics, but logic in general going all the way back to Aristotal.  I'm not sure how you could have a any sort of ration system without it.  I mean how can you analyse a universe in which the effects (the things that you measure) actualy create the cause.  A universe in which the future creates the past?  In any case it certianly does not match our emperical understanding of the universe.

#2.  Casmir effect is negative energy.
Many people are confused by this, but it simply is not true.  The Casimir effect is caused by presure diferentual of the virtual particle-anti-particle pairs bettwen two plates.  The plates restrict the wavelengths of the virtual particles inbettwen them, allowing greater amounts of energy to be built up on the outside.  This creats a pressure imbalance which creates the attractive force.  Some have called this "negative energy" but it is not so.

#288 Re: Interplanetary transportation » Solid core NTR with thermoelectric cooling? » 2005-09-16 13:07:02

A GCNR is going to be to hot for any conventional form of cooling.  Their operating temperatures (5000 - 20000 K) are well beyond the melting point for metals and even normaly heat-resistant silcates.  So structual material simply cannot be alowed to come in contact with the working medium of a GCNR, it must be contained either in a magnetic field or by a constantly replenished film of super chilled high specific heat substance which is constanly cycled (liquid helium or hydrogen).  Realisticly at these temperatures there is realy only one practical cooling option, dumping lots of liquid hydrogen into the chamber which is heated and exhausted.  Thankfully this is exactly what a GCNR does smile

#289 Re: Interplanetary transportation » WARP DRIVE, AHEM! » 2005-09-15 07:11:06

I've read the paper before, and while it's a nice thought experiment, it doesn't change the cold hard facts of the real world.

#1.  Information CANNOT be transmited FTL.  Why?  Because if it also causes some information to be transmited backwards in time to some observers, causing causality violations.  Note that these observers are not necessarily limited to those actualy traveling FTL.  Warp bubbles and what not cannot overcome this effect because it is an effect of the universe at large, not just some subset with a "bubble."  Put bluntly any FTL travel causes the possibility for someobservers to recive a message before it was actualy sent.  And I don't know about you, but in my universe CAUSE must always precced EFFECT.  See my previous post for a worked out example.

#2.  A warp drive must invoke "exotic matter" and "negative energy" in order to work.  There is just one problem.  These things do not exist.  There is no theoretical support for their existance and absolutly no experimental or emperical evidence of their existance.  Part of the problem here is applying mathmatical concepts to our real world.  Once must remember that while math provides a great modle for our universe it is NOT our universe.  Mathmatical constructs such as imaginary numbers, negative numbers, irrational numbers and so on simply do not exist in the physical universe where in the end everything must be finaly measured and counted somewhere.  You can't give me -1 apples, and you find me a string sqrt(-1) inches long.

#3. Even if for some reason such a device was possible, the energy necessary to construct it would be huge!  I have seen some estimations indicating it would need 10 times as much energy as present in the entire universe.  So not only is the warp drive impossible it's inpracticle as well.

I realy don't know why I am bothering to reply to this junk anyways, I should just ignore you and turn my attention to serious discusions about Mars.

#290 Re: Interplanetary transportation » WARP DRIVE, AHEM! » 2005-09-15 03:41:17

We can all be thankfull that special realtivity percludes such things then eh?

Also, what is the deal, are you to guys VTTFSH_V and VTTFSH_T diffrent people or what?

#291 Re: Interplanetary transportation » WARP DRIVE, AHEM! » 2005-09-14 03:35:49

Not supprisingly we have discussed this before to.  The disscusion was here.

Even if we do some handwaving and create things such as "exotic matter" and "negative energy" it still does not overcome the fundemental problem with FTL in our relativistic universe, the problem of causality violation and pardox.

All FTL methods of communicaton/travel can cause the grandfather paradox when the situation is right.

An exert describing how and why.

"We can describe this effect by idealizing FTL to be "instantaneous", and describing how the more familar time dilation implies this effect. But remember, the same points apply to any FTL speed, you just have more messy arithmetic to grind through.

Consider a duel with tachyon pistols. Two duelists, A and B, are to stand back to back, then start out at 0.866 lightspeed for 8 seconds, turn, and fire. Tachyon pistol rounds move so fast, they are instantaneous for all practical purposes.

So, the duelists both set out --- at 0.866 lightspeed each relative to the other, so that the time dilation factor is 2 between them. Duelist A counts off 8 lightseconds, turns, and fires. Now, according to A (since in relativity all inertial frames are equally valid) B's the one who's moving, so B's clock is ticking at half-speed. Thus, the tachyon round hits B in the back as B's clock ticks 4 seconds.

Now B (according to relativity) has every right to consider A as moving, and thus, A is the one with the slowed clock. So, as B is hit in the back at tick 4, in outrage at A's firing before 8 seconds are up, B manages to turn and fire before being overcome by his fatal wound. And since in B's frame of reference it's A's clock that ticks slow, B's round hits A, striking A dead instantly, at A's second tick; a full six seconds before A fired the original round. A classic grandfather paradox.

Note, this is NOT a matter of when light gets to an observer, it is NOT an optical illusion. It is due to the fact that, in SR, the question of what occurs at the "same time as" something else is observer dependent.

As A fired that first shot at tick 8, the bullet effectively teleported from A's gun to B's back instantly --- instantly according to A. But for B, who was moving at 0.866 lightspeed WRT A, B was hit in the back by the bullet 4 seconds BEFORE the bullet was fired. And again note, this is NOT due to the optical illusion of lightspeed delay in viewing A's turn-and-shoot; the light form that event wouldn't reach B until MUCH later, not tick 4."

As you can see the problems with causality and simultaneity at a distance don't specificly lie with the FTL travel, but the rest of the universe. Any FTL situation could cause a grandfather paradox similar to the one above.

#292 Re: Human missions » Facilitating Ground Rendezvou » 2005-09-13 23:54:48

One thing that has worried me about both Mars Direct and DRM is the possibility of an off target landing making it difficult for the crew to meet up with their supplies.  Aerocapture and re-entery are certianly tricky and a failure here can put the crew hundreds of kilometers away from there supplies and return vehicle.  Even if the failure is not so great (only tens of kilometers) it is still very inconvient.

However once the landing vehicle is down, moving it is tricky.  It weighs several tons, even on Mars, and the surface bettwen it and it's destination is unimproved and unmapped.  While it may be possible to slowly drag/haul it with a rover, the terrain might be impassible to vehicles, so what to do?

Reading some of Rob's excelent fiction contains an excelent idea.  The lander is going to have an engine on it, both for some orbital manuvering and for the final stage of it's decent.  So why not use it?  If fuel is avaliable at the base (and it should be) it might be possible to refuel the lander and FLY it over to the rest of the base camp.

Just some brainstorming, what do you guys think?

#293 Re: Human missions » Spacesuits - personal spaceship » 2005-09-03 21:15:50

I should first apologise, I didn't read this forum as throughly as I should have, or I would have seen that some of my suggestions had already been listed.  I still think the images help provide a vivid visual example of what might be involved (even if the astronaut is a wolf).

While I agree with the utility of a secondary, more traditional airlock.  The ability to do away with it could save vital space and mass.  While this would be nice for the Hab, it could prove even more vital for a Rover.  The rover is very constrained in tems of the mass and space it has avaliable, much more so than the Hab is.  The is also limited in the amount of  power it can provide to it's equipment.  High powered vacume pumps and air-filters might not be possible.  Some designs forgo an airlock entirely and simply depressurise the entire Rover, venting the air into space.  Indeed space may be so tight on the Rover that the simple ability to store the suite outside may be of some benifit.

---

I like the doggy door concept, but it strikes me as less than foolproof, and an airlock has to be foolproof.  It might be acceptable on the Rover where loss of cabin pressure isn't necessarily a total disaster.

#294 Re: Human missions » Spacesuits - personal spaceship » 2005-09-03 04:26:26

I wonder if anyone had ever considered this solution:

fv00981.gif
fv00982.gif
fv00985.gif
fv00986.gif
fv00996.gif

Sorry for all the images, but I think it illustrations help out.  Basicly the suit is docked to the outside hull of the ship/rover/hab/whatever possibly with another airlock bettwen it and the outside.  The astronaut climbs into the suit through a small hatch.  His lifesupport pack is then secured behind him and the suit is sealed.  The docking door is then likewise sealed and then  the astronaut is free to move out.

This sort of solution has its advantages. 
#1. It makes dust control much easier as the suit never enters into the main hab/rover, and the it's exposure to the inside atmosphere is extreamly limited.
#2. It might be possible to do away with the outer airlock saving large amounts of space and mass.
#3. The suit and the hab/rover share basicly the same atmosphere, with little to no need to vent the atmosphere in the airlock, making the process much more efficent.
#4. Climbing into a single unit, pre assembled unit is probably faster than dressing in a conventional suit.
#5. The suit would have fewer pressure seals (one) lowering the chance that one of these might fail (also fewer seals to check).

Some of the downsides I see are.
#1. Difficult to impossible to suit up by oneself.
#2. One-peice suit may be heavier and bulkier than other designs.
#3. Mechanical pressure suit is probably impossible via this method.
#4. Sharing atmosphere with the hab/rover could be difficult if a diffrent mix is prefered for EVA's (ie. pure O2 as opposed to a O2/NO2 mix).

#295 Re: Human missions » Long duration Human space missions - Can we survive them? » 2005-08-13 18:20:37

There's no need to throw around personal insults, they are not conductive to good debate.

Again the main issue with you proposition is the issue of specific power.  Nuclear reactors offer excelent specific power.  Much better than any solar option and competitive with most chemical sources of energy, but of course far superior when you consider the lifetime of a nuclear source.  However, they still fall short of what is required to power a energy hungry VASIMR engine.  They simply mass to much.  The specific power, or the amount of energy per unit of mass is CRITICAL to the performance of any space reactor.  You haven't given any details as to how this reactor performs in this crucial catagory, and I am hard pressed to belive that this liquid sodium cooled reactor could achive performance radicaly diffrent than that of any others.

The other issue I'm not sure if you are clear on is the issue of cooling.  As I'm sure you know there are only three ways to transfer heat, Conduction, Convection, and Radiation.  Terrestrial reactors rely primarily upon conduction and convection to disipate there heat.  This is because the Earth is full of matter with high specific heats.  Terrestrial reactors are litteraly swimming in it.  So it is fairly easy to dump the heat off to the enviroment, even if the temperature gradiate is not as great.  Space on the otherhand is as vacuum, so there is nothing to dump the heat off in.  Space, despite it's often very cold temperature is a very effective insulator.  The only way to lose the heat is to radiate it away.  The number of coolent loops betwen the reactor and any turbine doesn't change this fact.


Again.  What matters here is MASS.  How much the reactor weighs.  As far as I know no reactor to date, be it cooled by water, heavy water, sodium, or even CO2 achives quite the specific power necessary to make a realy outstanding VASMIR type system possible.  Some sort of next generation system, be it fusion, GCNR, or perhapce lead cooled reactor will be necessary.

#296 Re: Human missions » Long duration Human space missions - Can we survive them? » 2005-08-13 01:29:20

I posted a similar reply on your other topic, but I'll briefely repeat and expand here.  What is the specific power of this reactor?  The only statistics I could find for a similar sort of reactor were 200W/kg.  And this reactor was not apparently designed for space, with the heavy radiators necessary for such an enviroment taken into acount.  It's specific power is good, but not revolutionary.  Other space reactors currently on the drawing board already have this level of performance if not better.  In fact IIRC it is about what I have used as a refrence for most Nuclear powered space reactors.

This would mean you would need a 50mt reactor of this type to power a typical 10MW VASIMR engine for the quick trip to Mars.  This is in addition to mass of the VASMIR engine itself and the hydrogen propelent you would use as fuel.  Thus such a system is impracticle for intial use on any Mars Voyage.  Although it might be usefull powering a larger ship such as a cycler.  But extensive in-orbit construction would be required.  Realy though, reactors with much higher specific power are necessary to make such missions practical, such as GCNR or fusion reactors both of which would probably have specific powers >1kW/kg are required to make VASMIR practicle.  Of course the question then is, if you have such powerful reactors, why not use them directly for propulsion instead of VASMIR?

I also wouldn't be so hastly to assume that everyone here has regected the use of liquid metal cooled reactors of various types in our planning.  We have.  In fact not to long ago GCRNevenger and I debated the merits of a nuclear power/vrs solar thermal for powering the extraction of oxygen from moon rocks.  I belive he brought up just the system you propose due to it's sacrifice of electric specific power for better thermal specific power.  (I still advocate Solar Thermal BTW)

#297 Re: Interplanetary transportation » For all you space nuclear reactor naysayers! » 2005-08-13 01:00:04

You leave out one of the most CRUCIAL issues for any space reactor it's Mass.  I'm not sure what figures you have been looking at, but a brief Googling of the subject led me to a Los Almos paper about a reactor similar to the one you are discussing.  It produces 50-MW electric but masses 250 Metric tons.  This gives a power to weight ratio of 200W/Kg.  Good, but hardly spectacular, and there was no indication that this reactor was desigend for space use, with the heavy and bulky radiators necessary.  I'm curious as to what figures you are looking at that make you so happy.

Another issue is the use of MHD as a means of power conversion.  MagnetoHydroDynamics is still in it infancy and typicaly has a much lower efficency typicaly only 10-20%, much lower than that of a turbine.  However a MHD system may weigh less then a turbine, making it more attractive for a space based system.

#298 Re: Interplanetary transportation » Building your own Starship » 2005-08-09 21:27:51

Wait for another ship to come by?  Untill some REALY high ISP options come online we are talking about more than a year bettwen transits.  You life support won't last that long.

And even if/when those high ISP options come online if you bail out of a space craft you are still traveling at the same speed that craft was moving at.  That means that a rescue ship has not only to reach you (and you are likely to millions of miles away from anywhere out in the middle of space) but also has to match your velocity.  This means a rescue ship coming from your point of departure has to overtake you, and ship leaving from your destination has to at some point halt of it's forward velocity and try and match yours.  The amount of propellent this requires is extream, and probably impraticle.

#299 Re: Human missions » Mission One: a one way ticket to Mars? » 2005-08-09 20:22:56

Despite it's cold temperature, the rarified atmosphere probably acts as fairly effective  insulation.  So heat dispation may be a \n issue for a green house/hot house.

#300 Re: Human missions » The Cost of Going to Mars - A cost estimate of Colonization » 2005-08-06 01:18:43

RobS has hit on most of my points, so I'll just elaborate.

#1.  Travel time limiting cargo choices for solar sails.
I don't see why this should be true.  While a person probably isn't going to be to happy sitting in space for 16 months+ a bulldozer isn't going to care.  I don't see why the duration of the trip would prevent Mars colonisation plans either.  It isn't unheard of or even unusual for a buisness (esp. one involving some sort of heavy industry) to wait such a length of time for some new process or peice of machinery to come online.

The development times for new peices of equipment are still likely to be as long or longer than even the solar sail transit times.  So you realy aren't able to avoid these sorts of issues.  So you better have figured out when you are going to need some new peice of equipment much earlier than 6 months before hand.  Not to mention their construction and the construction of the launch and transit vehicle.  All space programs are going to involve alot of planning of when we are going to need new equipment/supplys and coping with the plans when/if these needs can't be met.  Planning out years in advance is not a silly as it might appear.  In any case these issues are only going to get worse as we go farther out, so we might as well learn to deal with them now.

And since solar sails are the only option that allows year round launching without a payload penalty use of a solar sails could mean cargo delivery happening all year round instead of bunched up at once.

#2.  Radiation/cold/vacume limiting cargo choices for solar sails.
I also don't see why this is true.  The extension of transit time from ~6 months to over a year doesn't realy change the dangers the cargo faces.  Electronics may require some protection from the cold and radition, but they are going to have to be hardened to face such hazards on Mars as well.  It isn't going to make much diffrence to the majority to the mass of any cargo.  As RobS pointed out it's going to be just as cold for the cargo on a 6 month transit as it is for a longer one.

Radiation exposure is greater, but I always understood this to be an issue of magnitude of exposure, not duration.  Either the radiation is strong enough to fry the chip, or it isn't.  In this case a longer mission runs an increased risk of exposure to solar flares, but no more so to background radiation.  Even if the hardened electronics are vunerable, some shielding and proper packing (ie putting the vunerable parts in the middle) should help eliminate this issue.

#3.  Solar sails being tricky to design.
No doubt their are some serious challanges in designing a solar sail, much less one intended for re-use.  But of course challanges exists in designing ANY interplanetary vessel, especialy one for re-use.  However the problems a solar sail vehicle faces apear to be much simpler than those faced by virtualy any other propulsion technology, especialy those reliant upon nuclear power.

---------

GCRN, I was wondering if you had read this paper http://www.lascruces.com/~mrpbar/staifpaper.html] here:  it lists delta-V requirments for a conjuction class fast mission at ~25Km/s one way when you include the breaking requirments.  This sort of mission has a mass fraction of 20% about double that of a tradional hohmann chemicaly fueld transit.  Very good, but if that same 3000 isp engine was used on a more conventional mission the mass fraction might be over 90%!

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