|
|
|
|
0 |
1,842 |
|
|
|
inefficient turbo-pumps and Isp by
Greg
I am trying to understand some of the loss mechanisms in a modern
rocket engine.
In a staged combustion cycle rocket engine, there are losses in the
turbine...
( 1 2)
|
|
10 |
1,841 |
|
|
|
|
|
0 |
1,840 |
|
|
|
an idea for your ridicule by
aSkeptic
Hi sci.space.tech
It seems that nuclear power is useless for booster applications and it
has forever been religated to upperstages. Propellant temperature...
( 1 2 3)
|
|
23 |
1,839 |
|
|
|
Chernobyl as SPS Rectenna Site by
cfrjlr
A Rectenna is a "Receiving Antenna" which converts RF radiation into electrical power.
They would be a fundamental component of Solar Power Satellite...
|
March 17th 07 03:09 PM
by cfrjlr 
|
0 |
1,839 |
|
|
|
|
|
0 |
1,836 |
|
|
|
|
|
10 |
1,835 |
|
|
|
|
|
0 |
1,833 |
|
|
|
|
|
0 |
1,830 |
|
|
|
|
|
0 |
1,829 |
|
|
|
VASMIR plasma engine's power source? by
Joseph S. Powell, III
I was just glancing at some sites mentioning VASMIR plasma engines, and was
wondering if the power source was nuclear (reactor or RTG?) or solar or some
other...
( 1 2 3)
|
|
28 |
1,828 |
|
|
|
Specific heats at high pressure by
Iain McClatchie
I just got the book "Mechanics and Thermodynamics of Propulsion",
mostly on the recommendations found in the sci.space.tech archives. I
turned to Appendix 2...
|
|
4 |
1,826 |
|
|
|
|
|
0 |
1,825 |
|
|
|
|
|
30 |
1,823 |
|
|
|
|
|
0 |
1,823 |
|
|
|
|
|
0 |
1,818 |
|
|
|
|
|
13 |
1,816 |
|
|
|
Why is a LOX/Kero SSTO not rather easy? by
Larry Gales
I am not a particular fan of SSTO, but it appears to me that SSTO has
long been within our grasp.
The best figures that I could get for the Titan II 1st...
( 1 2)
|
|
14 |
1,816 |
|
|
|
|
|
0 |
1,815 |
|
|
|
|
|
0 |
1,814 |
