Flight Control System - Scenario Part 6

If an engine fails, yaw control is maintained with the orientation device rudder, the second blade pair rudder or the hub rudder, depending on the configuration. If the configuration has only one blade pair, then engine vane split flap drag will be insufficient to maintain yaw control. Thence blade rotation will be induced, and lift will be achieved by blade rotation rather than conventional flight. -- The vehicle becomes a helicopter.

If both engines fail, then Controller Computer velocity demands are satisfied by the Perturbation Computer with altitude loss, trading potential energy for kinetic energy. Controller Computer directional demands are still satisfied with blade asymmetric and symmetric lift for roll and pitch control, respectively, and asymmetric engine vane split flap drag for yaw control. -- The vehicle becomes a glider.

When the conventional flight velocity can not longer sustain the required lift, the blades induce blade rotation to achieve the relative velocity necessary to achieve the lift demands, but without the engines to avoid blade stall, the Level Flight Computer causes the blades to seek maximum rotational velocity with blade camber and angle of attack. -- The vehicle becomes an auto-rotating helicopter.

Directional demands by the Controller Computer are satisfied by the Perturbation computer with asymmetric blade lift demands until the Level Flight Computer determines that the vehicle height above ground is such that blade rotational kinetic energy must be traded for potential energy to achieve the lift necessary to slow the decent to zero at ground level. -- The vehicle flares for a landing.

Given the large mass of a Blade Flyer relative to conventional helicopter blades, Blade Flyer engine-out landings will be safer.