Nasa chooses Orion heat shield

http://spacefellowship.com/News/?p=8617

As Apollo did, Orion will use an Avcoat heat-shield, which is made of
"silica fibers with an epoxy-novalic resin filled in a fiberglass-phenolic
honeycomb." Damn fools, shuttle tile is the good stuff. It shouldn't take
three years to learn that they did it right the last time. :P~

On Apr 8, 6:48*am, Bluuuue Rajah Bluuuuue@Rajah. wrote:
http://spacefellowship.com/News/?p=8617

As Apollo did, Orion will use an Avcoat heat-shield, which is made of
"silica fibers with an epoxy-novalic resin filled in a fiberglass-phenolic
honeycomb." *Damn fools, shuttle tile is the good stuff. *It shouldn't take
three years to learn that they did it right the last time. *:P~

What is the biggest tile that can be fabricated? The design of the
Orion is not one large flat surface . IIRC there were no Apollo burn-
thru problems.

http://averyhenderson.files.wordpres...0152_lores.jpg

http://blogs.nashvillescene.com/nash...e-launch3a.jpg

"Bluuuue Rajah" Bluuuuue@Rajah. wrote in message
. 17.102...

http://spacefellowship.com/News/?p=8617

As Apollo did, Orion will use an Avcoat heat-shield, which is made of
"silica fibers with an epoxy-novalic resin filled in a fiberglass-phenolic
honeycomb." Damn fools, shuttle tile is the good stuff. It shouldn't
take
three years to learn that they did it right the last time. :P~

The velocity of a vehicle reentering coming from the moon is *a lot* higher
than the velocity of a vehicle reentering coming from low earth orbit.
Given the shape and density of the Orion (similar to Apollo CM), I've got to
believe that the shuttle TPS materials simply aren't good enough.

Jeff
--
"Many things that were acceptable in 1958 are no longer acceptable today.
My own standards have changed too." -- Freeman Dyson

"Jeff Findley" wrote in message
...

The velocity of a vehicle reentering coming from the moon is *a lot*
higher than the velocity of a vehicle reentering coming from low earth
orbit. Given the shape and density of the Orion (similar to Apollo CM),
I've got to believe that the shuttle TPS materials simply aren't good
enough.

There's nothing wrong with the shuttle TPS for LEO work, but might not make
the grade for Lunar returns.

Three questions:

1 Will the Orion heat shield be in two thicknesses; one for LEO and one
for Lunar missions?

2 Is there a mass advantage to using an ablator over re-useable TPS?

3 Is there a cost advantage to ablator over re-useable TPS?

"Alan Erskine" wrote in
:

"Jeff Findley" wrote in message
...

The velocity of a vehicle reentering coming from the moon is *a lot*
higher than the velocity of a vehicle reentering coming from low
earth orbit. Given the shape and density of the Orion (similar to
Apollo CM), I've got to believe that the shuttle TPS materials simply
aren't good enough.

There's nothing wrong with the shuttle TPS for LEO work, but might not
make the grade for Lunar returns.

Three questions:

1 Will the Orion heat shield be in two thicknesses; one for LEO and
one for Lunar missions?

2 Is there a mass advantage to using an ablator over re-useable
TPS?

I think so.

3 Is there a cost advantage to ablator over re-useable TPS?

Shuttle tile must be a lot more expensive than ablator.

We've made a few advances in materials sciences in the past 30 years.

"Bluuuue Rajah" Bluuuuue@Rajah. wrote in message
. 17.102...


Damn fools, shuttle tile is the good stuff. It shouldn't take
three years to learn that they did it right the last time.

Different materials for different uses. For example: The ablation
materials I have seen would not make a good airfoil, because of their rough
surface after reentry, so they would be quite useless on the shuttle wings
and fins.

Vaughn

Bluuuue Rajah wrote:
http://spacefellowship.com/News/?p=8617

As Apollo did, Orion will use an Avcoat heat-shield, which is made of
"silica fibers with an epoxy-novalic resin filled in a fiberglass-phenolic
honeycomb." Damn fools, shuttle tile is the good stuff. It shouldn't take
three years to learn that they did it right the last time. :P~


Well, so much for the reusable heatshield concept... it's going the same
way as the landing on ground instead of a splashdown apparently.

Pat

Jeff Findley wrote:
The velocity of a vehicle reentering coming from the moon is *a lot* higher
than the velocity of a vehicle reentering coming from low earth orbit.
Given the shape and density of the Orion (similar to Apollo CM), I've got to
believe that the shuttle TPS materials simply aren't good enough.


If you did a multi-skip lifting reentry RCC might have worked.

Pat

"Bluuuue Rajah" Bluuuuue@Rajah. wrote in message
. 17.102...
"Alan Erskine" wrote in
Three questions:

1 Will the Orion heat shield be in two thicknesses; one for LEO and
one for Lunar missions?

2 Is there a mass advantage to using an ablator over re-useable
TPS?

I think so.

You _think_ so? I didn't ask for opinion.


3 Is there a cost advantage to ablator over re-useable TPS?

Shuttle tile must be a lot more expensive than ablator.

Must be?