oe.
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about 1965. There apparently is no prublem in shut-down or re-start of
the reactor rocket engine so long as the shut-down is programmed to control
‘the rate of cooling down of the reactor.
One problem existing in an inter-
planetary type mission would be to vent the fuel tanks during the coast |
periods due to the heating, A question was asked whether there is a difference
a in a rocket reactor fora -wingle stage type rocket from that to be used for
we oe - moving out of a stabilized orbit . Apparently they are essentially the same. .
: . . Another question was brought up as to whether some parallel approach should
| be made to nuclear rocket propulsion such as the ion propulsion,
It was
apparently felt by the AEC people that no parallel program should be made
_ but that emphasis should be placed on developing materials, higher temperature
fuel elements and more advanced types of reactors. During lunch it was brought
out that no large electrical power supplies are being developed for the massive
:
payloads to be carried in the 5 to 10 year period.
|
a
|
In the afternoon Abe Hyatt of NASA gave his presentation concerning the
mo
|
large boaster program,
In view of the fact that most of the members of the Panel
. were familiar with the Atlas and Thor combination programs, the first missile
-
he discussed was the Centaur.
This missile hae a first stage that is a modified
Atlas. The second stage is a liquid oxy gen-liquid hydrogen consisting of two
engines each having 15,000 lbs, thrust being developed by Pratt & Whitney.
It will put 8500 lbs. in a 300 n.m, orbit, 1450 lb. payload in a planetary probe,
or it will put 915 Iba, in a 24-hour communications orbit,
SERIE,
It is
a
“