Originally Posted by
Mechta
Imposing a requirement (autorotation) from one type of aircraft (helicopter) onto another type (multirotor) seems a negative step. What is required is the same or better level of reliability and survivability. If a multirotor can achieve this with two or more distinctly separate power and control systems, why should it be saddled with the weight, complexity and additional possible failure modes of an autorotation system?
A distinctly separate battery is a non-starter. In the event of a main power bus (single battery) failure, the aircraft becomes a brick.