markv wrote:Just a few questions, which might have obvious answers but I'm ignorant in these areas:-
1. Why change the material at all? what are the pros/cons of the original material & design over the aluminium approach?
2. Given that all the material properties are different, how can you be 100% sure that it's going to handle as well as or better than the original under all possible conditions (loading, twist, shock, cracking, corrosion, etc.). I realise that you are thickening parts of the shape but does that necessarily result in all-round improvement?
I think the first one is obvious and that is rust but I am still investigating steel and hot dip galvanising or stainless steel, aluminium was an option I wanted to explore as it is resistant to corrosion if anodised.
Stainless steel has some issues that are not unlike the aluminium part but the advantage of the aluminium part is there are no welds and it is one piece of metal so no chance of any of the issues that can creep into welded parts.
When you say the material properties are different then as far as tensile strength they are not that far apart, in some other areas they are but as with all things it is a compromise.
As far as the loading is concerned the main body is more than strong enough due to its profile (shape) to cope with push, pull, bend or twist. This alloy (7075) is aircraft specification aluminium alloy and is about the strongest aluminium alloy available I will be running some calculations to check its strength but it is difficult as I have to make some assumptions on the original as I do not know what material has been used apart from the fact it is steel.
Looking at the weakest areas on the standard unit then the aluminium one is far stronger in these areas and I have where possible used a radius to spread the load.