[amsat-bb] Re: Since We Are Off Topic Somewhat....
Bruce Bostwick
lihan161051 at sbcglobal.net
Fri Feb 15 07:00:37 PST 2008
The initial re-entry speed is strictly a function of where the
spacecraft is coming from. For LEO spacecraft like the Shuttle, that
speed is almost always going to be a little less than 17,500 mph or
thereabouts, and for spacecraft arriving from outside Earth orbit,
such as on an earth transit from a lunar mission, the initial re-entry
speed will be much higher, close to Earth escape velocity of around
25,000 mph or so. There's no way to change those numbers without
changing laws of physics.
What *is* possible is to change the re-entry profile to spread out the
drag deceleration over a longer distance, staying in the higher
altitudes longer and doing more aerobraking in the thinner air at high
altitudes. The Shuttle does this somewhat, using the lift of its
wings to control its descent profile, partly to keep the re-entry
deceleration within comfortable limits for the crew, but partly to
reduce heat load on the heat shield components exactly as you
suggest. This isn't too hard for a LEO spacecraft, which is
guaranteed to return to the earth's surface one way or the other. For
an extra-orbital spacecraft, it's considerably more difficult because
approaching at too shallow an angle doesn't reduce the spacecraft's
velocity enough for a re-entry capture and it skips off back into
space, ending up in a highly elliptical HEO at best and escaping into
solar orbit in worst case scenarios. Even so, the Orion crew vehicle
is planned to use at least some controlled-deceleration techniques to
reduce the re-entry loading as well as to enable land recovery in
CONUS from an approach origin below the equator .. which is
considerably more sophisticated than the direct-reentry water recovery
methods used for Apollo missions ..
On Feb 15, 2008, at 5:06 AM, David Barber wrote:
> Is it not possible to engineer a craft with a much lower re-entry
> speed thus
> reducing friction?
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