As described here:
Pretty cool, but I'm wondering how NASA defines "low cost." Technically, the shuttle's tiles could be considered "low cost" since at $10K a square foot, they're cheaper than that used on the Apollo capsules which came in at $30K a square foot.

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It says "low-density", not "low-cost"!

Jon

Is this meant as a reusable or use-once-burn-up heat shield?

"low cost" indeed isn't mentioned anywhere, but every kg less in heat shield is a kg extra in payload capacity, which means that lightweight materials kind of pay for themselves. Or in case of Orion, help staying below the maximum weight.

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Ok, maybe that doesn't mean it's not reusable, but I would think that in this kind of application, they would use just enough for protection of single use. I guess it depends on what it takes to remove and reapply.

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Reusable and low cost like...... STS?
Ouch did I realy say that?

Heh.

This one's ablative though, so it isn't really reusable and should be much better for both low cost and resilience than something like the RCC panels on the shuttle.

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Yeah, I don't know. Since you didn't mention cost per square foot for the proposed system, there's not much of a comparison value. Pure, fine, carbon fiber ballute, tightly bound, might be a LOT cheaper. 10 square feet of pure carbon fiber windboard (20 square feet, counting top and bottom) goes for around $3,000, which is just $150 per square foot.

Sounds like a bargain!

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Here's an idea... How about a self-inflatable ballute such as the ones used for years to retard the parabola of free-fall bombs?

For re-entry, you could have two sections. The first section would inflate from front scoops, thereby protecting the entire re-entry vessel, while the back would inflate simply to maintain stability.

There would be a very small direct contact area up front which could easily be insulated using space-shuttle-like tiles. The remainder of the area would largely be insulated by air space between the outer inflated ballute and the inner ballute surface, which would only require minimal, and inexpensive insulation between it and the re-entry vehicle's surface.

Scoops redesigned as required for re-entry velocities, mach effects, etc., everything made of hexagonal woven carbon-fiber cloth with rounded, multilayered leading edges, etc....

Can it be done?

Yes.

Cheaply?

Certainly a lot cheaper than $10 per square foot...

When the vehicle is slowed to a thicker atmospheric, sub-mach terminal velocity, the design can be "unzipped," allowing it to stream to the stern while normal parachutes continue to slow descent and bring home the baby.

Heck, I can think of three ways to modify the ballistics throughout reentry, including using what we called "ring-slot" chutes whereby during the first phase, high-level to low level, the chute's ability to retard the fall was limited by a ring which kept the chute from full inflation. This allows for more accurate fall, but also for much greater descent velocity.

The ballutes could have a progressive "ring-slot" design which would allow for progressively greater air pressures and slow terminal velocities until the main chute's deploy for final touchdown/splashdown. If you really want to reuse the body, build it in a blended wing design (I think we've got all the six-million-dollar-man kinks worked out) and use the ballutes for re-entry before transitioning to glider mode.

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I am Mugs, of the Alien clan of Usa, Nordamerica, a Terran, of Sol.

Perception isn't reality. It's merely an abstraction thereof, and quite often not a very good one at that.

I am human. Fully human.

That article does, but I've seen others (which I can't find) that say it's less expensive than that used on the shuttle. They don't give a price, either, which is why I posted this piece. I'd be interested to see what the drop is.

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Oh, ablative indeed, that doesn't sound like reusable. And I doubt they'd put on tenfold of what they need, so it lasts the 10 times an Orion can be reused.

Oh well, nothing wrong with ablative heat shields as a concept.

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The point of a low-density heat shield of any design would, I think, mean that less mass for shield means more mass for cargo.

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