An electric power system of a flying object may supply power to electric loads including a VTOL motor and a cruise motor. A control device includes an acquisition unit, a determination unit that determines whether a power surplus situation in which surplus power obtained by deducting the required power from the sum of the generated power and the regenerated power is larger than the maximum allowable power is brought about, and a control unit that can execute power consumption increase control for increasing power consumption by reducing the operation efficiency of the cruise motor in the power surplus situation.

An electric power system of a flying object may supply power to electric loads including a VTOL motor and a cruise motor. A control device includes an acquisition unit, a determination unit that determines whether a power surplus situation in which surplus power obtained by deducting the required power from the sum of the generated power and the regenerated power is larger than the maximum allowable power is brought about, and a control unit that can execute power consumption increase control for increasing power consumption by reducing the operation efficiency of the cruise motor in the power surplus situation.

A control device includes an acquisition unit configured to acquire information indicating a battery output limit value that is a maximum value of electric power that can be supplied from a battery to an electric load, and a control unit configured to, when electric power supplied from a first battery to a first electric load is expected to exceed a first battery output limit value, execute control of increasing electric power supplied from a battery other than the first battery and reducing electric power supplied from the first battery to the first electric load.

A control device includes an acquisition unit configured to acquire information indicating a battery output limit value that is a maximum value of electric power that can be supplied from a battery to an electric load, and a control unit configured to, when electric power supplied from a first battery to a first electric load is expected to exceed a first battery output limit value, execute control of increasing electric power supplied from a battery other than the first battery and reducing electric power supplied from the first battery to the first electric load.

A lift lever assembly for a vertical takeoff and landing (VTOL) aircraft is disclosed. The assembly includes a lever configured to control a lift propulsor of an aircraft. The assembly additionally includes at least a handle mechanically coupled to the lever, wherein the handle configured to allow transition of the lever from a thrust-engaged position to a thrust-disengaged position when the at least a handle is in an active position. The assembly also includes at least a sensor in communication with the lever, wherein the at least a sensor is configured to identify when the lever transitions from the thrust-engaged position to the thrust-disengaged position.

A lift lever assembly for a vertical takeoff and landing (VTOL) aircraft is disclosed. The assembly includes a lever configured to control a lift propulsor of an aircraft. The assembly additionally includes at least a handle mechanically coupled to the lever, wherein the handle configured to allow transition of the lever from a thrust-engaged position to a thrust-disengaged position when the at least a handle is in an active position. The assembly also includes at least a sensor in communication with the lever, wherein the at least a sensor is configured to identify when the lever transitions from the thrust-engaged position to the thrust-disengaged position.

A method for operating an eVTOL multirotor aircraft having distributed actuators activated by controllers that each determines an associated manipulated variable signal at least for a subset of actuators and provides it for the relevant actuator. The method provides that for an actuator: i) assigning a different priority ranking for each controller; ii) determining, by way of a given controller having a given priority ranking, at least one manipulated variable signal for the actuator and transmitting the signal identified by the given priority ranking to the relevant actuator and to a controller having a successive priority ranking; iii) receiving, via a given controller having a given priority ranking, manipulated variable signals from controllers having higher priority ranking and relaying these signals to the actuator and to a controller having a successive priority ranking; and iv) activating the actuator using the manipulated variable signal identified by the highest priority ranking.

A propulsion system that includes a plurality of power units, a plurality of propulsors, where respective power units of the plurality of power units are controllably coupled to the plurality of propulsors, and a controller configured to receive a desired throttle value corresponding to a desired propulsive force, determine a number of power units of the plurality of power units to be coupled to the plurality of propulsors to achieve the desired propulsive force based on a respective power value associated with each respective power unit of the plurality of power units, and cause the number of power units of the plurality of power units to be coupled to the plurality of propulsors.

The present disclosure relates to a flight system and a failure responding method therefor. A flight system includes: a plurality of fuse boxes configured to control application of a voltage to at least one propulsion device; and an interlock control apparatus configured to control interlock lines between fuse boxes connected using the interlock lines among the fuse boxes to synchronize and control opening of the fuse boxes connected using the interlock lines.

A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing.