ORIGINAL: allanflowers
ORIGINAL: da Rock
No matter what the weight of the airplane, the load on either an aft located stab/elevator or a forward located canard will be a function of the CG location versus the center of lift of the wing. The demands on them may be greater for pitch changes, but the load isn't going to automatically be greater.
The problem is that a typical canard will have a cg that puts a big lifting load on the front surface, in order to be stabile in flight without computer control, while the typical aft stab does not have this kind of issue at all. So the the canard surface, for stability, must be running at a considerably greater wing loading than the main wing.
This doesn't allow much reserve for other functions, like roll control
It was my understanding that the design had to insure the canard would stall sooner, not that it had to carry a large percentage of the load.