Makes sense. Another potentially interesting factor is that the max takeoff weight of a plane can be much higher than the max landing weight. If the plane is powered by conventional jet fuel, it can take on this extra fuel, fly father, and land much lighter than it took off.
Will the relatively constant weight of a hydrogen cell become a significant range limitation? Battery-powered aircraft have this problem as well. Very curious to hear your thoughts.
It is definitely a design constraint that we have to consider but at the same time the relatively small change in weight during the flight is also good for our balance, given we won't be putting the fuel in the wings. All in all, the sources of weight are pretty different between the conventional jet-kerosene versus our hydrogen electric propulsion, which is what is driving us to a clean sheet design to take maximum advantage of HEP. We are doing a 15-seat retrofit of a Beech 1900D as our first product, and while it is a great MVP, the landing weight constraint, amongst others, make it a little less capable, with 800km range, than the conventional version.
Will the relatively constant weight of a hydrogen cell become a significant range limitation? Battery-powered aircraft have this problem as well. Very curious to hear your thoughts.