MHD Aerobraking and Thermal Protection Part III: Aerobraking and Aerocapture

While using electromagnetic effects for atmospheric reentry and thermal protection is interesting, it’s only one of several promising options that have been proposed over the years.  There is another application though, where exploiting magnet-hydrodynamic effects could be a much bigger “game changer” — aerobraking and aerocapture for reusable in-space vehicles.

Traditional Aerobraking and Aerocapture
One of the challenges of orbital mechanics is that it takes just as much energy to descend into a gravity well as it does to ascend out of it. One technique that has been used for lowering the propellant cost of descent into the gravity well of a planet with an atmosphere is aerobraking. Aerobraking is the process of taking a spacecraft in an ellpitical orbit around a planet with an atmosphere, and using atmospheric drag at the lowest altitude portion of its trajectory to slowly decrease the altitude of the high end of the elliptical orbit. This process has been used now on about a half-dozen planetary missions, in some cases reducing the propulsion requirements by 1km/s or more, over the course of a couple hundred passes. Aerobraking has been traditionally been done by satellites that aren’t explicitly shaped like a reentry vehicle–in fact most of the drag for typical aerobraking vehicles is produced by using the spacecraft’s solar panels as massive drag brakes!

Artists Impression of MRO Aerobraking (credit JPL and Wikipedia)

Artist's Impression of MRO Aerobraking (credit JPL and Wikipedia)

A more aggressive maneuver called aerocapture takes a spacecraft in a hyperbolic (interplanetary) orbit and in a single pass decelerates that vehicle into an elliptical orbit around a planetary body.  Typically the term refers to maneuvers where the ending orbit has an apoasis near the altitude of a circular orbit, though it could also be used to describe a maneuver that uses a single pass through the atmosphere to replace the “capture braking burn” that would normally be used. Aerocapture is a lot more challenging, since the deceleration has to take place a lot lower in the atmosphere in order to provide the required deceleration in such a short distance. This implies much higher forces and heat-fluxes, which require some sort of aeroshield/TPS system.

Here are a few of the main challenges of aerobraking and aerocapture:

  1. Dynamic Pressure Loads: Dynamic pressure is the pressure felt on the vehicle by the impingement of the atmospheric molecules.  The equation for dynamic pressure is q = 1/2 * rho * V^2, where lower case q is the dynamic pressure, rho is the instantaneous atmospheric density, and V is the instantaneous relative velocity.  For MRO, the dynamic pressure limits were set at 0.35 Pascals, which correlates to moving at about .76m/s at sea level (ie a slow walking pace).  To give you an idea of how this compares with orbital reentrythe peak dynamic pressure of say a Soyuz in its emergency ballistic reentry mode, is over 40,000 Pa of dynamic pressure, and even a low-G lifting reentry is still in the 10kPa+ range.  Direct entry into the Venusian atmosphere from a hyperbolic interplanetary orbit gets you into the 1MPa range!  Another fun comparison is that the max-Q Xombie or Xoie have seen in flight was around 250Pa.Most of the very low allowable dynamic pressure load for past aerobraking efforts has been driven by the fact that most aerobraking craft to-date have used large flimsy solar panels as their main drag structure.
  2. Peak Heat Flux:  The shockwave caused by slamming into gas particles at hypersonic velocities compresses and heats the gas particles to substantial temperatures.    Heat from this shock wave is convected and radiated into the aerobraking spacecraft.  The equation for heat flux is Q = 1/2 * rho * Ch * V^3.  Capital Q is the heat flux (in W/m^2), rho and V are the same as before, and Ch is the heat transfer coefficient.  The heat transfer coefficient, I think, represents what portion of that heating goes into the vehicle itself instead of being carried off by the now quite ruffled atmospheric gas molecules who didn’t see you coming.  Yes it is confusing that dynamic pressure is lower-case q, and heat flux is capital Q.Once again, to give you some scale, the worst case pass for Odyssey had an estimated heat flux of about 500 W/m^2,  which is about 40% of the heat you get in LEO from the solar radiation. For that Soyuz reentry case mentioned earlier, the total heat generated at max-q is in the 240 MW/m^2 range–several times higher than the heat flux at the throat of the SSME or RD-180.  The Venusian direct entry example according to one source would actually be in the 4000MW/m^2 range! Fortunately, I think that for atmospheric reentry the Ch term is relatively low–most of that heat gets carried away by the atmosphere.As with dynamic pressure loads, the reason why peak heating rates are kept so low for most aerobraking missions is that you’re using the large solar panels as most of the drag surface, and they can only take so much heating before their temperatures rise to levels that could permanently degrade their performance.
  3. Atmospheric Density Variations: If atmospheric density was nice, constant, and well-known, aerobraking could proceed a lot faster and in a lot fewer passes.  The problem is that at the altitudes where aerobraking takes place (100+km), the density can vary significantly over length scales as small as 20km.  This can be driven by many processes including variations in the solar wind and solar radiation due to sun cycles, weather effects like dust storms for Mars aerobraking, and other effects.  Going off of some data from the Odyssey mission, variations as big as 2-3x were seen in density from pass to pass.   A second-order effect of density variations is that both the drag coefficient and the heat transfer coefficient will vary with atmospheric conditions by noticeable amounts.  Unfortunately,  in many cases you don’t know the density along a given trajectory in advance, so you have to plan for not the average density, but the worst case pass density.   Which means that most of the time you’re getting less deceleration and heating than you could actually withstand, but some of the times you might actually find yourself pushing your limits more than you would like.   This drives you to taking more passes than you’d really like to take in an ideal situation.  These variations get more and more pronounced at higher aerobraking altitudes, where atmospheric density is measured in kilograms per cubic kilometer.Once again, this is an area where using large, sensitive solar panels as your drag devices really hurts. Because you can’t stand high dynamic pressures or heat fluxes, you have to do your passes higher up in the atmosphere. But due to variability in density at those higher altitudes, you end up getting driven even further up to deal with worst case variations. That said, even aerocapture trajectories are high enough altitude that atmospheric variations can be important challenges to deal with.
  4. Aerobraking Duration: For most previous Mars and Venus aerobraking missions, velocity changes in the 1-1.2km/s range have taken between 70-150 days, over several hundred passes.  While this is fine for unmanned missions, it’s harder to do for manned missions, where radiation concerns make you want to minimize your time spent in-transit.  The large number of cycles is also a difficulty for missions aerobraking at earth, where each pass will take you through the Van Allen belts.  Lastly, for reusable in-space transports, the total turn-time is an important economic parameter–the more missions you can fly in the same period of time, the fewer vehicles you need to support a given mass throughput.

A couple more quick observations before we jump into using MHD forces to enhance aerobraking:

  • For typical aerobraking, the parameter you can control easiest is the periapsis altitude, and thus indirectly the average density.  In other words, if you want to double the drag on a pass, you lower your periapsis to an altitude that has about double the average density.  This also means that to a first order approximation (ie ignoring the relation between density and the heat transfer coefficient) heat flux for traditional aerobraking is going to scale fairly linearly with drag.
  • Ballistic coefficient ends up being really important for aerobraking as well–this is the whole reason why the solar panels are used unstowed for aerobraking.  Higher ballistic coefficients mean that you have to dip lower into the atmosphere (and thus get a higher heat flux) to get the same amount of deceleration per pass.
  • In spite of the disadvantages of using solar panels as your drag brakes, there are some real advantages to being able to use a aerobraking scheme that doesn’t require your vehicle to be explicitly crammed into a typically reentry-vehicle shape behind a massive heat shield.  It would be nice for instance to be able to get tanker vehicles or orbital tugs back from lunar trajectories or martian trajectories without them having to carry a big aerobraking shield like you see in all the old literature.

Anyhow, that was a quick introduction to aerobraking by a complete non-expert.

Some Backstory on Why I’m Interested in Aerobraking
I started looking into this a few months ago as an alternative to propulsive retrobraking for Centaur-derived cislunar tanker vehicles.  While a Centaur stage actually can do a lunar round trip fully propulsively, with at least some payload delivered to the Moon, the “gearing ratio” (initial mass in LEO compared to payload delivered to LUNO or the Lunar Surface) was pretty pathetic.  Just to use some ballpark numbers, without digging up my more precise calculations, I’m getting around 8000lbs payload to LUNO if you drop it off in orbit and the Centaur only returns to earth, dropping to only 2500lb if the Centaur has to haul the payload all the way there and all the way back propulsively.  However, if you could do 3km/s worth of aerobraking (assuming about 1200m/s worth of burns between the Trans-Earth Injection burn and any periapsis raising maneuvers, including the final circularization), all of the sudden you’re talking about almost 20,000lb of payload on the dropoff mission, and about 13000lb on the round-trip maneuver.  Depending on how massive and expensive the aerobraking system weighs, it makes a massive difference in the performance of a reusable cis-lunar architecture.  For a long time though, I had sort of dismissed aerobraking, because any aeroshield big enough to allow single-pass aerobraking (or few enough passes to be interesting) also ended up looking like it would either be very heavy, or very bulky, or require lots of orbital assembly or some sort of new deployable technology.  Not that any of those other than being too heavy was a total show-stopper, but it definitely made it less attractive for a near-term commercial operation.

Another line of thought I had been wondering about recently was manned cislunar transportation, especially in light of the Augustine Committee report.  One of the big suggestions they made that rubbed a lot of HLV-advocates wrong was the idea of launching the crew on commercial LEO taxi vehicles, and flying Orion up to LEO unmanned.  A lot of people said this was just silly–if you’re launching Orion may as well launch it manned, even though this would require adding launch escape and emergency detection capabilities to the HLV.  I started thinking down the lines of what Orion could look like if it was designed from the start not to carry astronauts until they got to space.  The LAS would go away, as would all the structural requirements for taking those sorts of loads, being able to rapidly drop the service module, etc.  The whole thing could fit inside a fairing, thus simplifying aerodynamics and loads on the front end of Orion.  Heck, it could even be attached to the rest of the stack in whatever orientation made the most sense for mission ops–it wouldn’t be constrained by needing to be on the top in an orientation where the capsule could “get out of Dodge” in a hurry if something “went south” with the HLV.  The more I thought about it, the more I realized that Orion could end up looking like a drastically different vehicle if it was optimized for in-space use and reentry instead of needing to also handle manned ascent to orbit as well.  Then I made an interesting leap of logic.  What if Orion was only meant to be used in space?  I originally sort of dismissed this, since most single-pass aerobraking schemes I knew of would require the thing to be designed like a reentry capsule anyway.

Jumping back to the Centaur-based tug idea, I toyed around with the idea of doing a blog series, seeing if I could make an aerobraking simulator to figure out if a Centaur could without any sort of fancy aerobraking shield actually do a multi-pass aerobraking mission that would get it back to LEO within a reasonable amount of time (say three weeks or less).  However, I stumbled on the papers about magnetic aerobraking right about this point in my thought process, which may possibly provide a solution to both of these problems.

While I don’t have anywhere near the analytical chops to know for sure how far you can push this technology, if it could enable single-pass or at least small number of pass aerobraking without requiring a huge traditional aerobraking shield, interesting things might become possible. Magnetic aerobraking could potentially revolutionize cislunar transportation, enabling low-cost reusable manned and unmanned deliveries based on modified versions of existing LOX/LH2 upper stages, and could allow fully-reusable in-space only manned vehicles that weren’t just an overglorified 1960s-style reentry capsules.  But more on that later.

For now let’s get back to how we can use magneto-hydrodynamic interactions to enhance traditional aerobraking, and see if we can figure out if this idea has merit at all.

Magnetic Aerobraking
Going back to our previous two discussions, one of the key takeaways was that the enhanced braking and thermal protection provided by strong magnetic fields was strongest at high altitudes where atmospheric density was lowest. At high altitudes, the ambient atmospheric density is low, but Joule heating caused by the interactions between ions in the shock layer and the superconducting magnet keeps the electrical conductivity of the plasma in the shock layer high. Also, for aerobraking or aerocapture short of reentry, by definition you are both always at a speed and altitude high enough that you don’t have to worry about the shock layer losing sufficient conductivity for MHD effects to dominate aerodynamic drag effects. The magnetic interaction parameter (Qmhd) introduced in my first post in this series can easily be in the 250-1000+ range at high altitudes compared to down in the 5-50 range you might see during atmospheric reentry. For example, the paper I cited in my first article (Otsu et al) showed that for a vehicle coming back from a GTO-like orbit, you could cut the return time by 70% with a 0.1T magnet, which is about 5x weaker than the magnet assumed for most of the reentry magnetic TPS studies.   While magnetic effects may be helpful for reentry, they truly come into their own for aerobraking and aerocapture.

A few other thoughts:

  • While the total drag for a magnetic aerobraking concept can actually be several times the drag of a similar non-magnetic vehicle, the gas-dynamic portion of the total drag actually decreases substantially in the case of magnetic aerobraking.  This is due to a much lower velocity behind the shock layer in the magnetic case.  Figure 9 from the Fujino et al paper I used in the last post (“Numerical Analysis of Reentry Trajectory Coupled with Magnetohydrodynamics Flow Control”, JS&R Vol 45 No 5, pg 911-920) illustrates this beautifully:MHD_Aerobraking_GasdynamicPressureReduction
  • For a vehicle using magnetic braking, most of the total drag force is actually reacted electromagnetically through the magnet itself, not through the surface of the vehicle.  The dynamic pressure that the vehicle surface itself sees is greatly reduced compared to what you would expect at that altitude and entry velocity.
  • While in the above case, the dynamic pressure reduction was about 4x at ~75km, this effect is likely to be even more pronounced at the altitudes used for aerobraking (90-120km) where the electromagnetic interaction parameter is substantially higher (40-160x higher) than it is in the case shown above for atmospheric reentry.
  • The heat flux seen by the aerobraking vehicle will also be greatly reduced compared to a non-magnetic aerobraking system at a similar altitude and velocity.  This is due to the much thicker shock layer standoff distance and the lower velocity of the particles behind the shock layer.  The Fujino et al paper estimated that the heat flux would roughly be cut in half at 75km with a 0.5T magnet (due to a boundary layer between the bow shock that is twice as thick at that magnetic interaction parameter).
  • For higher parameters in the 100-1000 range that you would likely see for aerobraking, this effect should be even more pronounced.  The trend in shocklayer thickness vs. Qmhd shown in Fig 3 of Fujino et al  was linear over the Qmhd range of 0-6.  If it continued out linearly up into the Qmhd 100-1000 range, the shock layer standoff distance would be in the range of 100-125x thicker than without MHD effects, implying a drastically reduced heat flux at aerobraking altitudes.  Unfortunately without having them run the actual analysis, it would be hard to know precisely how well this would work.
  • All these factors mean that the same vehicle could use a lower periapsis with a magnetic braking system than without.  The dynamic pressure and heat flux that the vehicle sees at a given periapsis altitude is going to be at least 2-4x and possibly more than an order of magnitude less than it would be without the magnetic field.  Even in the most conservative case (ie assuming that the effect at 100km and aerobraking speeds is no better than at 75km in spite of having a Q 40-160x higher) this would allow you to go to an altitude with at least double the density while keeping the heat flux and dynamic pressure loads within tolerances.  With an effective total drag 4x higher at a given altitude combined with being able to go to a lower periapsis, you get bare minimum a 8x reduction in total aerobraking time compared to the non-magnetic case.
  • For the aggressive, “I don’t know if I’m extrapolating way too far” case, you could get even larger reductions in aerobraking time.  Going back to my linear extrapolation on shock layer standoff vs. Qmhd (and thus heat flux vs Qmhd), at Qmhd=250 this would put the shock layer standoff at about 25-30x thicker than the non-MHD case.  The example in Otsu et al gave a Qmhd of 250 using a 0.1T magnet and a 100km periapsis.  Since Qmhd is proportional to B^2 and inversely proportional to rho.  If you increased the magnetic field from 0.1 to 0.5T (similar to what was being suggested for the reentry studies done by Fujino et al and some of the others), you could maintain a Qmhd of 250 even if you increased the local density by a factor of 25.  At Qmhd of 250, the effective drag coefficient is about 3x higher than the non magnetic version.  That would give up to a 75x reduction in aerobraking time compared to the non-magnetic case.
  • One other advantage of magnetic aerobraking is that you can drastically vary your effective drag coefficient electrically.  Also, the heating and dynamic pressure are far more driven by the magnetic field strength than by the atmospheric density for the MHD aerobraking case.  These mean that you can afford to take deeper passes without having to worry as much about variability.  If the density is higher than expected, and you have some head-room on your magnet, you can increase the MHD field strength a bit to keep the shock layer back and the dynamic pressure down.  This also could cut trip times in half just by allowing you to base your planning off of the average atmospheric density instead of having to take the mean + 3 standard deviations as your predicted atmospheric density.

I’m rapidly coming up to the point where I’m pretty sure I no longer know what I’m talking about.  At least from here, it looks like there’s a good chance that MHD aerobraking could allow for aerocapture (at least into a high eccentricity elliptical orbit), and very rapid aerobraking down to a circular orbit compared to the non-magnetic case. I think you can extrapolate the conclusions of these papers in these ways, but without having the people with the analysis tools actually verify these claims, I’d still take them with the appropriate sized grain of salt.   Also, my intuition on how a MHD aerobraking vehicle would compensate for density variations is not very good.  That alone could be a paper or a thesis.

So, whether this ends up being a mild curiosity that ends up only being useful in niche applications, or a game-change remains to be seen, but the potential for this being a game-change is real.

In my last post in this series, I’ll go more into some of the implications of what this could do if it works, and some thoughts on how to actually flight-demonstrate MHD aerobraking.

[Edit: It turns out I had misspelled Fujino’s name in the original post. Fixed that and added the title of the paper in case people want to get a copy–it’s free if you have a JS&R subscription, $15 if you’re an AIAA member without a JS&R subscription, and something like $30 if you’re not an AIAA member–highly recommended if you’re interested in this topic]

The following two tabs change content below.
Jonathan Goff

Jonathan Goff

President/CEO at Altius Space Machines
Jonathan Goff is a space technologist, inventor, and serial space entrepreneur who created the Selenian Boondocks blog. Jon was a co-founder of Masten Space Systems, and is the founder and CEO of Altius Space Machines, a space robotics startup in Broomfield, CO. His family includes his wife, Tiffany, and five boys: Jarom (deceased), Jonathan, James, Peter, and Andrew. Jon has a BS in Manufacturing Engineering (1999) and an MS in Mechanical Engineering (2007) from Brigham Young University, and served an LDS proselytizing mission in Olongapo, Philippines from 2000-2002.
This entry was posted in Lunar Commerce, MHD Aerobraking and TPS, Space Transportation, Technology. Bookmark the permalink.

17 Responses to MHD Aerobraking and Thermal Protection Part III: Aerobraking and Aerocapture

  1. A_M_Swallow says:

    Some of the testing could be performed in vacuum chambers acting as wind tunnels. A sounding rocket can perform a reentry sequence. If the demo machine is under a third of a ton then a Pegasus or Falcon 1 can put the test machine into an elliptical orbit.

  2. johnhare john hare says:

    This would also be a game changer for outer planets missions. To get there in a reasonable amount of time (before the prime investigator retires), the vehicle really needs to be moving considerably faster than the ones considered here, and the method seems to improve at higher velocities.

  3. A_M_Swallow says:

    When slowing down is there a way of using the heat generated to power some of the hardware? This way reduce the quantity and mass of batteries carried.

    Being a brake the field probably needs to be as wide as possible.

  4. wintermuted says:

    That’s an interesting point – is there an advantage/disadvantage to a larger weaker field vs. smaller stronger field? I’m guessing the effect of a stronger field has some kind of squared relationship, where you start to need some really heavy coils or high power to generate it? Maybe it’s more cost effective to carry something that can generate a weaker, wider field?

  5. j. campbell says:

    Tom D , in his comments about part 1, mentioned a book co-authored by Dean Ing, which reminded me that I had read a novella by Ing (in Analog?, late seventies? early eighties?) that centered around a SSTO spaceship built by a single inventor/constructor in his garage (actually his hangar at the local general aviation airport). Said SSTO not only used MHD for TPS, the chemically fueled rocket engines used magnetic containment in the thrust chambers and magnetic pinch nozzles.

  6. Chris (Robotbeat) says:

    Don’t forget that a big magnet will be torqued by the earth’s magnetic field.

    Also, the magnetic field strength in Teslas is proportional to the inverse _cubed_ distance to the magnetic dipole (a quite rough approximation, I know), which means that moving the shock layer far enough away from the magnet will make the magnetic field at that point far less. I think using magnetic field strength as a figure of merit is kind of weird, since it really depends quite strongly on how far you are away from the magnet.

    This is a rather interesting concept, though. I like the idea of using a lunar lander for cislunar travel, although a dedicated cislunar vehicle is probably better for integrating a magnetic aerobrake.

    Of course, no ferromagnetic implants for any astronauts! You have to be careful of any ferromagnetic bolts, etc, too.

  7. Jonathan Goff Jonathan Goff says:

    Chris,
    The B^2 in the Qmhd equation is the field strength at the stagnation point. Yeah, dipoles drop off pretty quickly. As I said, modeling all of this is outside my area of expertise, so I’d love to get help analyzing this from people in the field. I wish there were more Americans working on this–it’d make it a lot easier to ask them questions if ITAR wasn’t a concern.

    The magnetic torque issue is one I was wondering about though. That could be quite significant, huh? I wonder what impact it would have if you placed the magnet inside something that allowed you to rotate the vehicle with respect to it. It would be pretty easy to get big angles of attack, but I wonder what it would do to the trajectories of the particles and the resulting current loops.

    ~Jon

  8. Tom D says:

    Jon,
    From what you say it sounds like the energy dissipation associated with MHD-assisted aerobraking is taking place in a wider, broader shockwave around the vehicle. Is there any induced heating in the magnet itself? That could be a potential design challenge.

  9. Tom,
    Re: induced heating in the magnet. No, so long as the magnet stays superconducting any induced currents or magnetic forces shouldn’t generate any heat.

    ~Jon

  10. Doug Jones says:

    The only good way to counter the torque on such a large high field magnet might be… ANOTHER large high field magnet. Doubles the mass of the system, but makes the controls far simpler.

    I think Chris (robotbeat) has the right thread- rather than a small, high field magnet, you may want a big honkin’ coil, perhaps even a deployable hoop with a few spokes. Maybe some of the Magsail papers would be useful.

  11. Nels Anderson says:

    I find it easier to think in terms of magnets interacting with each other, because I’ve played with magnets. In that spirit, what’s going on here is that the currents in the magnet tend to induce in the plasma a mirror image of themselves, and that mirror image repels the magnet. The greater the plasma’s conductivity, the higher the fidelity of the mirror image. If you’ve ever seen a high-temperature superconductor floating above a magnet, you’ve seen the case in which the conductivity is effectively infinite.

    Let’s build a toy model to play with: imagine a circular loop of radius a in which a current I flows. In SI units the B-field along the loop’s axis of symmetry at a distance x from its center is 0.5*mu0*I/a * (1 + (x/a)^2)^-1.5 . This drops off as x^-3 for x >> a. Just among friends, let’s pretend the field is constant at strength B = mu0*I/L over a distance L and essentially zero beyond, L = 2*a being the size of the magnet.

    One thing this suggests is that in the quest to reduce heating rates by pushing the shock front out, it may be tough to push it much further away than L . If so, then this obviously pushes one to increase L in the trade between I and L.

    Plugging B into the equation for Qmhd, we get sigma*mu0^2*I^2 / (rho*V*L) . Taking into account that the effective area of the magnetic field goes as L^2, the MHD force scales as I^2*L . This starts to make large I look more attractive than large L.

    To generate a field of strength B, we need a current of B*L/mu0 . For B = 1 T and L = 3 m (a Centaur’s diameter), the current is about 2 MA. The magnetic moment is just the area of the loop times the current, roughly L^2 * I = 2e7 A m^2. If the strength of the earth’s own B-field is, say, 0.3 gauss = 3e-5 T, then the torque is (2e7 A m^2)*(3e-5 T) = 600 N m. That’s appreciable and something to be dealt with, but it’s not overwhelming. Maybe the drag, whether electrodynamic or aerodynamic, could be made asymmetric so as to generate an equal but opposite torque.

  12. Nels Anderson says:

    Jon, do Otsu et al. or the others give indications as to how large the conductivities? That’s the biggest single thing missing from the toy model above; some parts it’s implicitly assumed that the conductivity is small enough that the B-field penetrates the plasma to a depth of L or so.

    Another question we can ask is, how much energy does it take to pump up the B-field in the first place. I don’t know how flux pumps work (@Ruediger Klaehn?), but it’s easy to estimate the total energy that must be put into the magnetic field. The energy density of the field is B^2/mu0. If it’s scale size is L, then the total energy, U, is on the order of B^2*L^3/mu0. For B = 1 T and L = 3 m, U ~ 2e7 J ~ 6 kW h, before losses.

    That doesn’t sound like a lot to me, but I don’t know how much power a Centaur would likely need for other purposes anyway. Since B ~ mu0*I/L, it follows that U ~ mu0*I^2/L, which pushes us toward larger L if power is a constraint.

  13. Chris (Robotbeat) says:

    I’m working on a model in Scilab (a good MATLAB clone) for a magnetic radiation shield. I’m in the quite early stages (and am going to use the magnetostatic approximation for now, which should work for orbital velocities…), but it should allow one to model drag occurring from deflecting ions at altitudes of about 100km (where the mean-free path is bigger than the size of the magnet). If anyone wants the code, I can email it to them… just private message me on NASASpaceflight.com (or, if you’re a selenianboondocks blogger, I think you can directly email me).

    BTW, if you want to get a feel for the magnetic fields produced by different electromagnet configurations, check out this site (really one of the best basic physics sites on the internet) :
    http://www.falstad.com/mathphysics.html
    And for 3d magnetostatics:
    http://www.falstad.com/vector3dm/

  14. Randy Campbell says:

    Jon:

    Quik question: I recall a bit of talk on both an aerobraking thread somewhere and a beamed propulsion thread that just came together in my head and I’m wondering if you can “check” me to see if I’m talking out of my keester here :o)

    The crossover point was where someone pointed out that the method used to “clear” the air for ground based telescopes with a laser deals with ionizing an air tunnel for the scope. (Which in the suggested case could be used to reduce laser propulsion losses for orbital manuevering) Then it was mentioned in the aerobraking thread that using a set of lasers in a similar manner could allow a way to ‘even’ out the atmosphere in the path of an aerobraking vehicle.

    Crossover thought: In addition to seeding for better ionization of the plasma could a set of laser pulses increase the ionization in the path of an aerobraking vehicle?

    RAndy

  15. Jonathan Goff Jonathan Goff says:

    Randy,
    That sounds like it might be plausible, though the devil is probably in the details. The problem is that at the point where the MHD effects start weakening, you’re still going ~3.5km/s. If it’s a ground-based laser, I don’t know how long you could provide that ionization before the rocket has passed too far beyond you. I guess it also depends on the deceleration rate and such. It’s not totally implausible, and depending on the energy requirements might not even be that unreasonable. But I’m not sure if it actually would end up making financial sense even if it could be made to work technically.

    ~Jon

  16. One “back of the envelope” way to estimate field strengths required is in comparing the dynamic pressure to the magnetic field energy density B^2/2mu. Remember, pressure is an energy density so the magnetic field pressure has to be strong enough to push the shock wave further away from the spacecraft.

    The AMS-02 is finally on the ISS and sending some data. This was going to be the first superconducting magnet in orbit. The system was planned to use liquid helium cooled niobium wire magnet coils. That didn’t make it to flight though. They had to use permanent magnets which means decreased field strength and longer data collection times.

    http://www.ams02.org/what-is-ams/tecnology/magnet/scmagnet/

    For an aerobraking magnet it would be lighter weight to use the newer BSCCO or YBCO which can superconduct at liquid nitrogen temperatures and then actively cool them with something like the free piston sterling cycle cryocoolers from Sunpower. But then you need power not just to run current in the coils, but also to power the cryocoolers.

  17. Pingback: Leviathan. | Photography by Bill Nash

Leave a Reply

Your email address will not be published. Required fields are marked *