Post edited 4:04 am – June 29, 2010 by rpulkrabek
I've been investigating the material to be used for the oxidizer tank and for the combustion chamber. I started with the oxidizer tank. The objectives I used were to minimize mass and to maximize the amount of pressure it can hold, tensile strength. I have access to a software that serves as a material database and groups materials together on a plot. See below for the Density Vs. Tensile strength plot.


http://cstart.org/wiki/images/…..9_2010.PNG
Each bubble represents a certain group of materials. For example, I believe the red colored bubbles were materials like different steels or other metals. Each steel bubble was of a certain type of steel. I can plot lines of certain slopes to determine the best choice. For this case, I chose a slope of 1. Here is a zoomed in look.


http://cstart.org/wiki/images/…..9_2010.PNG
With this slope, it basically removes steels from our choices. If we were to go with a slope of 1/2, meaning that we would prefer a higher tensile strength at the cost of having a heavier tank, a steel would be more appropriate.
In my opinion, choosing Al-50%, or as I have more commonly heard of it, Al 6061, is the best choice for this application. More information about this material can be found from here. One benefit of this material is that I know it is widely used, such as higher end bicycles, and is commonly available. One negative about this material is that it is a bit trickier to weld, although, quite many people are familiar with the technique.
All of this analysis is off the basis of objectives and constraints that I am aware of. I would love to hear what other people have to say. Are there any inputs from those that have experience with hybrid rockets and what material they chose?