Correct me if I'm wrong, but won't the skin of the satellite crumple due to the G force difference between side that's closer to the point of rotation vs the outer side? What would be the G force difference is the satellite were say 2 feet in diameter.
You are correct. The outer side of the launch vehicle will experience different G verses the inner side.
Using the numbers in the OP's video which is 450rpm and 100 meter diameter (50 meters radius). This is for the targeted launch configuration, not the prototype which is smaller and much lower RPM.
450 round per minute = 450/60 round per second = 7.5 round per second
Each round travels the circumference 2*pi*radius
7.5 round per second so total travel in one second = 2*pi*radius*7.5
First, the outer side (at the edge of the spinning wheel):Plug the numbers in, you have:
2*3.1416*50meter*7.5/second =
2356 meters per second (this is actually
close to mach 7)
centrifugal acceleration = V
2/r
centrifugal g force = (V
2/r) /9.8
= (2356*2356/50)/9.8
= 11,328gNow the inner side of the payload vehicle which you are using 2 feet wide (0.61 meter),
the radius of rotation is thus (50-0.61) = 49.39 meterThe inner-side velocity is:
2*3.1416*49.39meter*7.5/second =
2327 meters per secondcentrifugal g force = (V
2/r) / 50) /9.8
= (2327 *2327 /49.3)/9.8
= 11,208gSo,
here is your answer to the 2 feet wide satellite payload g delta:
outer exit velocity is 2356m/s and centrifugal g is 11,328g2 feet width in,
inner exit velocity is 2327 m/s, 11,208g Note 1:
Look at the exit velocity delta, outer side is 2356m/s and inner side is 2327m/s, 29m/s less.
That is why I insisted that the payload will exit with an end-to-end rotating force. One side is moving 29 m/s faster than the other side, 48x the width of the payload (per second) if the payload is indeed 2 feet wide. The delta is progressively decreasing as you move from one side to the other but there is a delta none the less. You can trade speed for steering, but that is yet another problem non the less.
Note 2:
No doubt the spinner and even the booster rocket can be engineer to withstand the 11,000g. The payload.... that is where the problem lies. I just visited their website. I can't find anything about payload hardening. They just say their launcher (will?) withstands 20,000g. It is left for the audience to imagine how a satellite will look after it is hardened to withstand 11,000g, how much cost it will add to making that 11,000g proof satellite. etc. Seem to me "buyer beware" should apply here.