First off, these are things I've read that I'm not 100% sure ring true. I am posting this to get answers from more informed people.
Basically, apart from the S-IC
not being able to be reused, I was wondering what the advantages of each were over each other. I know that the SRBs were more a penalty in terms of dry weight, and I don't know how good their performance was past max Q...specific impulse I think was a bit higher than the S-IC
in the lower atmosphere, but I've read certain claims of the S-IC
getting a specific impulse of something like 304 in the later phases of the launch.
The last advantage, which I'm not sure of or not, appears to be that the SRBs fully fueled had a higher thrust-to-weight ratio than the S-IC
, which used almost 5,000,000 pounds of fuel and had to burn longer to get the Saturn V to the same altitude, although it could get the Saturn V up to 6,000 mph vs. the SRBs, which could only get the shuttle to about 3700 mph prior to separation.
One guy I know with some knowledge in rocket science claims that the S-IC
was much less efficent than the SRB because it was a low thrust-to-weight ratio that ended up wasting a lot of fuel, although I would think that should be taken with a grain of salt since the S-IC
-1 and LOX, which I was told costs less per pound than aluminum percholorate, although I thought SRB was better for storing purposes.
I guess my final thought was which was more suited for heavy payloads? Could the SRBs have acted as replacements for the S-IC
had the Saturn V been kept in production? I mean, they were almost as powerful.