Systems and methods for controlling engine speed and/or pitch of propulsion members for aerial vehicles

An aerial vehicle comprising:

• a chassis;
• a mechanical power source coupled to the chassis and configured to supply mechanical power;
• an electric power generation device coupled to the chassis and the mechanical power source and configured to convert at least a portion of the mechanical power into electrical power;
• an electric motor coupled to the chassis and the electric power generation device and configured to convert electrical power into rotational power;
• a first propulsion member coupled to the chassis and the mechanical power source and configured to convert at least a portion of the mechanical power supplied by the mechanical power source into a first thrust force that directs a cooling air flow from the first propulsion member onto one or more components of the aerial vehicle;
• a second propulsion member coupled to the chassis and the electric motor and configured to convert the rotational power supplied by the electric motor into a second thrust force;
• and
• a powertrain control system associated with the mechanical power source, the electric power generation device, the electric motor, and the first propulsion member, and configured to at least partially control at least one of an output speed of the mechanical power source or at least partially control a pitch angle associated with the first propulsion member, the powertrain control system being configured to:
• receive an operational signal indicative of an operation associated with the aerial vehicle;
• receive a status signal indicative of a status factor associated with the aerial vehicle;
• receive a component parameter signal indicative of at least one component characteristic associated with at least one of the mechanical power source, the first propulsion member, or the electric power generation device;
• and
• generate, based at least in part on at least one of the operational signal, the status signal, or the component parameter signal, at least one of a speed control signal or a pitch control signal, the speed control signal configured to cause the mechanical power source to operate within a range of output speeds, and the pitch control signal configured to cause blade-like components of the first propulsion member to be oriented within a range of pitch angles,
• wherein the at least one of the speed control signal or the pitch control signal is configured to balance multiple component operational targets associated with the mechanical power source and the electric power generation device to improve flight range of the aerial vehicle.

A method for controlling supply of mechanical power and electrical power for operation of an aerial vehicle comprising a mechanical power source, an electrical power generation device coupled to the mechanical power source, and a propulsion member coupled to the mechanical power source, the method comprising:

• receiving an operational signal indicative of an operation associated with the aerial vehicle;
• receiving a status signal indicative of a status factor associated with the aerial vehicle;
• receiving a component parameter signal indicative of at least one component characteristic associated with at least one of the mechanical power source, the propulsion member, or the electric power generation device;
• and
• generating, based at least in part on at least one of the operational signal, the status signal, or the component parameter signal, at least one of a speed control signal or a pitch control signal, the speed control signal configured to cause the mechanical power source to operate within a range of output speeds, and the pitch control signal configured to cause blade-like components of the propulsion member to be oriented within a range of pitch angles such that the propulsion member is for being rotated to provide a thrust force that directs a cooling air flow from the propulsion member onto one or more components of the aerial;
• and
• balancing multiple component operational targets associated with the mechanical power source and the electric power generation device to improve flight range of the aerial vehicle.