Everyday Space Drives

[DDE]

14 hours ago, ChrisSpace said:

A solid-core NTR using Methane propellant would only need a mass ratio of about 2.21.

But at the same time it’s significantly beyond what one would entrust to an Average Joe.

[wumpus]

16 hours ago, ChrisSpace said:

I should point out something (sorry for taking so long btw)

A quick check of the delta-v needed to get to various orbits on this chart makes it obvious that it is taking the Oberth effect into account.  Side trips to EML-2 and similar make a lot more sense if you are using low acceleration means to get there and won't get significant help from Oberth.

[ChrisSpace]

10 hours ago, DDE said:

But at the same time it’s significantly beyond what one would entrust to an Average Joe.

I was just using that as an example. Here's the mass ratio required with other methods discussed here:

Rocketdyne solar thermal engine: 1.89

Solar Moth: 1.75

High-Isp solar thermal engine: 1.67

Hydrolox chemical propulsion: 3.00

Laser thermal: 1.14

9 hours ago, wumpus said:

A quick check of the delta-v needed to get to various orbits on this chart makes it obvious that it is taking the Oberth effect into account.  Side trips to EML-2 and similar make a lot more sense if you are using low acceleration means to get there and won't get significant help from Oberth.

Correct. I assume that low-thrust propulsion wouldn't be necessary, but if it is, then not only do travel times increase, but so does Dv. For example, to get from LEO to EML-1 on a low-thrust trajectory requires 7km/s of Dv. As a mass ratio, here's what that would look like with the methods mentioned here:

VASIMR: 1.03-1.28

MPD/Pulsed Plasmoid Thruster: 1.10

High-Isp MPD: 1.03

Arcjet/Hall Effect Thruster: 1.43

High-Isp Arcjet: 1.42

Ion: from 1.03 to 1.26, depending on design

Solar Sail: Not Applicable

[PB666]

On 9/28/2017 at 2:17 PM, regex said:

Not sure if this belongs in The Lounge or not? Anyway, I've been daydreaming for the past couple of days, playing around with COADE and reading too much Atomic Rockets (probably), and I got to thinking about how people would get around the solar system in the future. I'm not talking about potential future research/project spaceships created by large government/corporate entities, I'm talking about the most realistically feasible "rocketpunk" propulsion systems we might see; those in commercial and individual hands in a future where the solar system has been populated to some extent. Things like a drive with a reactor + shadow shield and some tankage on a pole with a Bigelow on the other end, or whatever. Those little ships of the solar system.

My thoughts are:

Early on ion, MPD, and other electrics if fission reactor energy density is high enough with closed-cycle NTRs for high-thrust tasks. We'd probably always see "lower-tech" electrics in the inner system, and even out to the asteroid belt. After that, maybe nothing unless fusion drives become possible. MPDs given enough power can achieve some amazing stats but by the time you're pumping that much power into them you're either paying too much for reactor mass or you might as well use the reactor byproducts for an exhaust. I'm not keen on FFRs, NSWRs, or Orion/Medusa drives for the average schmoe; that makes zero sense to me. Maybe in a military/large government sort of project. I also tend to shy away from specialized fuel systems like lithium fusion liners, for instance; I don't think that's accessible to the "everyperson" and would trend towards things like PJMIF instead (although energy density is always a concern).

Anyway, I'm interested in your thoughts. Is specialized fuel not a huge concern? Would we see an incredible diversity of propulsion systems for different tasks? Is some sort of fusion drive going to overwhelm everything else?

That future, I don't believe is far away. I am interested in Mercury, it has potential that others seem to ignore.

There are two basic lines of electric propulsion systems.
The first line are the solar driven systems. I expect that the application systems will slowly creep up in efficiency and plateau off around 60%. The research systems will always lead these in efficiency but they are generally not applicable for a variety of reasons, what follows the leading edges are non-OP systems that are better than application but are more reliable, durable or productive than the best efficiency models. At some point we may reach a performance of 1 kw/meter.

This really does not solve the overriding problem with ION drives. Here it is . . .the reason to use ION drives is because for the dV that they can produce over their lifetimes both the units and their fuel is very light weight. The problem is that the power supplies are not light weight, and the more fuel efficient the drive the heavier the panels have to be. The second problem with ION drive also is related to their fuel efficiency, that is the issue of linear drop in thrust with increased ISP, that problem can be solved by increasing the number of drives. Some critiques about VASIMR are correct, the high power (35 kw) ION drives can have about the same fuel efficiency as VASMIR, but you need alot more of them (6) and these drives start to have a wide foot print. To have 210 kw of ION drive now you need 630 m2 of solar panels at more than 1kg per square meter. There are spatial limitations on the application of solar panels.

IT can be done if you find a significantly high space port to launch from, if your launches lower MaxQ and delay passing the sound barrier (i.e. wasting about 1000dV of fuel 'hoovering' over the launch pad) delay the gravity turn. This means that such a space craft really needs to use its ION drive early in its life to poke its way into deep space. Once it gets inside the orbit of Venus such ships can shine with power the other ships don't have, but close to Mercury the panels need to be turned to prevent over heating. Solar power ION drive are really optimal for ship nonperishable between planets in which if it takes 5 years to deliver supplies in low orbit about Mars, no-ones going to have a heart attack.

The other line is nuclear based propulsion. While NTGs can feed excess power to ION drives these generators are few and far between now. The fission based reactors (classic steam based design) are not very reliable, and more they are optimized for space applications (less-weight) the less reliable they become. They never have produced much power in space, they have leaked. Some have proposed using thermocouples instead of a steam/water cycle. This in not very efficient and there is alot of waste heat lost. If you need a source of heat for another reason it might be worth it. We could see something like a fast breeder reactor or waste fuel heat generators (Purified reactor waste) using thermocouples, you really are no better off than solar panels. From all the fission reactors I've seen I've never seen a composite generator that was better than a contemporary solar based power generation.  There may be a need for electric power in the outer solar system, in which case fission is the only viable ION drive power source. The problem with fission in the US is that scientific institutions are running like mad from application of radioactivity in the research and engineering areas. The NRC has gone overkill in many aspects making the users lives especially difficult. The problem is in the on ground implementation of a fission reactor. It would almost have to be done by the US-DOD research arm (which Bush the second basically gutted for the two Wars) and plopped into a rocket, as a module, just before lift-off (Plug and prey astrotechnology).

Then finally there is fusion. I don't think fusion will be light weight system under any circumstance. A space ready fusion module would at least need a Falcon heavy to get it into space, no accounting for the remainder of the rocket, such a device would need many ion Drive (100s) at 35 kw to push the massive reactor through space. The beauty of fission reactors is that they are completely non-radioactive until you flip the 'on' switch. Then they become a neutron factory. The bad part about fusions is that its longest living vapor-ware product of the modern age. Everyone seems to be waiting for the neeto-trick innovation that makes it works flawlessly. I wont be alive when that happens, but lets hope that they can get something working. A fusion reactor can drive all aspects of the ship, from ion driven RCS to main engines to computers to science, etc. An altnerative is fusion pulse engine in which you basically don't try to sustain a fusion reaction, just get it going for a moment, throw in the ejecta, let it all blast out and cool and repeat. This may be where the next century of spaceflight finally brings fusion in. All the Mars dreamers will be left figuring out how to fulfill themselves using solar panels.

This is why I always have to ask the question, what is your power-supply for extracting water from Mars, or smelting metal in space, these operations may take more weight in solar-panels than just bring water from Earth to Mars. My   Personal opinion is that near and mid future space is gonna be all about making panels lighter, work better and greater efficiency on the application side.

@YNM, there is a ion drive metal that is very cheap to store and found in great abundance in asteriods (magnesium). You can basically have screws sticking out of a pole and twist the metal onto the screws and use a robot to remove magnesium and feed it into the ION drive. This solves many problems, it does not solve the problem of how to get robots and smelters to asteroids and how to power them once they get there.

@ChrisSpace That 7000 dV assumes continuous thrust, if you pulse the ion drive as it passes through pE you can get it up with much less, the problem is that you waste alot of time. For such a system to work well we need a higher power density battery. It may be the case the graphene based batteries of the future can provide that storage density.

 

@wumpus IT serves a ship well to have some chemical propellant to pulse dV going through oberth. But the whole thing about ION drives is that their ISP is so high you might not choose to use oberth. Oberth effects are really for rockets using monopropellent (hideously low ISP).

[ChrisSpace]

2 hours ago, PB666 said:

I don't think fusion will be light weight system under any circumstance.

I think it could be, but not for a very long time.

2 hours ago, PB666 said:

This is why I always have to ask the question, what is your power-supply for extracting water from Mars, or smelting metal in space, these operations may take more weight in solar-panels than just bring water from Earth to Mars.

This isn't as much of a problem if planels can be built on-site using locally acquired materials.

2 hours ago, PB666 said:

That 7000 dV assumes continuous thrust, if you pulse the ion drive as it passes through pE you can get it up with much less, the problem is that you waste alot of time.

Yeah, using low-thrust engines in the first place seems a bit inefficient for manned crew/colony vessels, unless the distances travelled are interplanetary. I've read the report that sparked the "Mars in 39 days" VASIMR frenzy, and while that specific scenario makes some very optomistic assumptions, a travel time of under 3 months certainly seems possible.

[DDE]

7 hours ago, PB666 said:

The fission based reactors (classic steam based design) are not very reliable, and more they are optimized for space applications (less-weight) the less reliable they become. They never have produced much power in space, they have leaked. Some have proposed using thermocouples instead of a steam/water cycle. This in not very efficient and there is alot of waste heat lost.

Hold up. This is where I have to ask you to do your homework.

There has never been a spaceborne turboelectric design.

BES-5 (about thirty flown) had a thermocuple converter; 3 kWe.

Topaz (two flown, both mated to plasma thrusters as part of Plasma-A experiment) had a thermionic converter, 6.6 kWe at less than half the fuel mass.

Yenisei (two reactors last seen in US SDI storage) featured an integrated fuel rod-thermionic power converter design, 5 kWe.

Given that these reactors were pretty damned small, this sounds like a good start.

Furthermore, the leakage seems to be primarily associated with the ejection system and not normal operation.

Edited November 11, 2017 by DDE
Spelling

[wumpus]

13 hours ago, PB666 said:

IT serves a ship well to have some chemical propellant to pulse dV going through oberth. But the whole thing about ION drives is that their ISP is so high you might not choose to use oberth. Oberth effects are really for rockets using monopropellent (hideously low ISP).

Oberth effects are for use with any rocket with sufficient thrust to complete a burn in a small fraction of an orbit.  This means any chemical rocket and probably most nuclear ones as well.  If you really need to abuse it, you can go for a mangalyaan maneuver (pe kicking in KSP) which only requires a restartable engine (which might mean hypergolics, but still doesn't require monoprollent).  Apollo did use a parking orbit (instead of the slightly more efficient direct shot), but it was remarkably low to still get that Oberth while using hydrolox rockets (NASA wanted to make sure the command module was ready before sending on a trip that couldn't return in less than a week).

ION propulsion (and any other low thrust system) is typically incompatible with Oberth for the simply problem in that they can't afford the 'duty cycle' needed.  The thrust is so low that they need to simply "burn" all the time in order to get anywhere.  With VASIMR, there is at least the possibility of "charge during the orbit and burn at Pe", but that is only thanks to higher thrust.  I'd expect ION systems to have chemical rockets on board to maneuver into a gravity-based push that they couldn't reach on ions alone.  This may well be out of range of Oberth, but pe is typically a good place to burn.  ION systems take years to get anywhere.  Using Oberth could make it decades.

[PB666]

10 minutes ago, wumpus said:

Oberth effects are for use with any rocket with sufficient thrust to complete a burn in a small fraction of an orbit.  This means any chemical rocket and probably most nuclear ones as well.  If you really need to abuse it, you can go for a mangalyaan maneuver (pe kicking in KSP) which only requires a restartable engine (which might mean hypergolics, but still doesn't require monoprollent).  Apollo did use a parking orbit (instead of the slightly more efficient direct shot), but it was remarkably low to still get that Oberth while using hydrolox rockets (NASA wanted to make sure the command module was ready before sending on a trip that couldn't return in less than a week).

ION propulsion (and any other low thrust system) is typically incompatible with Oberth for the simply problem in that they can't afford the 'duty cycle' needed.  The thrust is so low that they need to simply "burn" all the time in order to get anywhere.  With VASIMR, there is at least the possibility of "charge during the orbit and burn at Pe", but that is only thanks to higher thrust.  I'd expect ION systems to have chemical rockets on board to maneuver into a gravity-based push that they couldn't reach on ions alone.  This may well be out of range of Oberth, but pe is typically a good place to burn.  ION systems take years to get anywhere.  Using Oberth could make it decades.

There are many reasons why ION does not work with Oberth.

1. Typical power supply is solar, for most oberth effects of planets outside the earths orbit:
a. The planet is between the bottom of the hyperbola and the sun. (no Light)
b. there is not alot of light to use to begin with.
c. there is generally not enough battery or NPG on board to have a significant effect.

2. RL is not KSP. (mu is the celestial's specific gravitational parameter)

a. An OP 35kw high power light weight producing a piddly isp of 3500 generates this  2 * 35,000 w * .8 [efficiency]/ (3500 * 9.8) = 1.6 Newtons.
b. If we assume an ION drive that has unlimited power passes at the minimum safe orbit it has a velocity close to that escape velocity. For Jupiter that would be ~60,000 m/s (see below). If we also assume that burn can be no longer than 20 degrees, thats about 400 seconds at that velocity. 500 seconds at 1.6N. 800N can be generated (at the cost BTW of 17,500,000 Joules of electricity)
c. lets assume our space craft weighs a ton, that translates into 0.8 dV.
d. So lets assume we reach jupiters SOI with 2000 m/s of velocity. this equals SKE of 2E6 J/kg. The potential energy is 2*mu/r_orbit,min = 3.539E9 (this is the amount of energy that is borrowed and needs to be returned on exit). The exact velocities at minimum are: 59393 which is slower than the escape velocity because we are approaching Jupiter from a minimum safe orbit and not the designated surface (which is ephemeral at best). Lets say that our dV is added at 70% efficiency relative to adding all dV at 59392 this means we go from 59392.1352923818 + 0.56 = 59392.6952923818 velocity (the decimal places are kind of important. This translates to SKE at maximum velocity of about 1763746127.04686 and 1761712867.29429 is returned to Ju[iter as SPE as the ship leaves.

You might be surprised that the space craft is now traveling 2016.35 m/s, 16.35 m/s faster. However this is not reality- land. As the ship passes behind jupiter is it using (most probably its NPG) at around 500 w for 500 seconds is 250,000 j. Thats about 1/80th the power it would need and it more or less would gain a fifth of a meter per second. So lets say the spacecraft had a 100lb nickel metal hydride battery capable of 2000kW of power production max for 500 seconds (again thats a fantasy, the battery would drain more quickly).  at 1 million joules it would only run that ION drive at full for 28.751sec. HOw about the theoretical 40,104,000 J/kg https://en.wikipedia.org/wiki/Lithium–air_battery a theoretical discard over 500 seconds that does not destroy the battery (unlikely) would have enough power for 2.5 ION drives (25kg instead of 10, 15 kg more) increasing the amount of velocity imparted to  2049.6 on exit a gain of 50 m/s.

Lets compare the same situation with a 10kg RCS thruster and 90 kg of fuel and ISP of 200. That generates a dV of 188. Using the same parameters of efficiency that RCS thruster would impart 2432 dV of exit addition bringing the rocket to 4432 m/s.

This is the reason you don't use ION drives for Oberth. If you have RCS thrusters on board the dV you gain in the end beats the very high ISP of ION drive. That does not negate the other uses of ION drives (as demonstrated in the exploration of Ceres). It is also the reason they don't carry mega-OP batteries on board. The critical issue of ION drives is that the use a high density power source (nuclear) or external power (solar) to increase ISP such that the straitline dV for burns (such as at a systemic pe) can take days or weeks within that 20' burn window you can have very high ISPs and conserve alot of fuel (3 to 20 times as much fuel as the best chemical rocket engine). The very thing that makes ION drives useful for interplanetary travel station keeping makes them useless for Oberth effects. Here is the logic. THat oberth effect around Jupiter achieved 2234 dV, a good ION driven setup can have 10000 or 15000 more dV than a comparably weighted RCS based propulsion system. How many oberths does the RCS need to achieve before it reaches its destination, 7 or 8, this is unlikely. OTOH that rcs system does not need solar to run and does not have to deal with declining power in NPGs.

 

 

 

 

7 hours ago, DDE said:

Hold up. This is where I have to ask you to do your homework.

There has never been a spaceborne turboelectric design.

BES-5 (about thirty flown) had a thermocuple converter; 3 kWe.

Topaz (two flown, both mated to plasma thrusters as part of Plasma-A experiment) had a thermionic converter, 6.6 kWe at less than half the fuel mass.

Yenisei (two reactors last seen in US SDI storage) featured an integrated fuel rod-thermionic power converter design, 5 kWe.

Given that these reactors were pretty damned small, this sounds like a good start.

Furthermore, the leakage seems to be primarily associated with the ejection system and not normal operation.

1-10 kW is nothing when if comes to ION powered systems. Its trivial power product and not worth the added effort relative to solar If solar is available. I have read up on the russian fission based systems. More or less they abandoned the systems. To many problems relative to solar.

Again a 35 kw system at the low end of 3500 ISP _only_ produces 1.6 N of power, at the high end of ISP produce only 0.55 N of power. This is the reason people are not taking VASIMR seriously, it does not have a power supply. Plain and simple. Alot of weight and nothing to power it.

[DDE]

2 hours ago, PB666 said:

More or less they abandoned the systems. To many problems relative to solar.

There hasn't been a single Roscosmos electric-propelled deep-space probe, and if we take them at their word they're swimming knee-deep in nuclear-electric propulsion and fission rocket designs.

Edited November 11, 2017 by DDE

[DAL59]

Solar Moth

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

 

Why does that keep happening to me???