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I was reading an article about the Reuseable Solid Rocket Motor ("RSRM") and it had details of propellant and rocket casing weight. Due to the fact that the RSRM is built robustly in order for it to be reused the casing weight has to be a higher ratio of total weight of the system than an ICBM for example. I could not find comparable information for SLBMs or ICBMs. Can someone provide me with a link or a rough estimate of how much lighter a one time use carbon fibre casing would be.
The information I have on the RSRM is; Total weight 1,300,000 lbs made up of propellant - 1,100,000 and casing, 200,000 lbs for a casing to system weight ratio of 15.38%
The information I have on the RSRM is; Total weight 1,300,000 lbs made up of propellant - 1,100,000 and casing, 200,000 lbs for a casing to system weight ratio of 15.38%