Abstract: An aerospace hybrid powertrain system includes an engine, a power shaft, and an electric machine having the power shaft therein or passing therethrough. The aerospace hybrid powertrain system further includes a fan, impeller, or blower connected to the power shaft and configured to direct air toward components of at least one of the engine or the electric machine. The fan, impeller, or blower may further be configured to direct air toward cooling elements such as heat exchangers or finned heat sinks arranged to cool the components of at least one of the piston combustion engine or the electric machine.

Abstract: An energy source for an aircraft includes an enclosure, an engine, an electric generator, and at least one fuel tank configured to provide fuel to the engine; and electrical connectors for outputting power generated by the electric generator to at least one electrical component or electrical bus of the aircraft. The engine, the electric generator, and the at least one fuel tank are each housed within the enclosure.

Abstract: A hybrid powertrain system includes an engine, an electric machine having a power shaft therein, and a clutch configured to releasably engage an output of the engine and the power shaft of the electric machine. The electric machine further includes an electrical output. The power shaft is configured to mechanically attach to and provide mechanical power to a propulsion device. A controller is configured to control the engine, the electric machine, and the clutch to implement one or more power output modes.

Abstract: An aircraft safety system includes impact energy reduction systems including: an aircraft parachute, at least one rotor configured for autorotation, and an energy absorbing system. An automatic control system uses data from speed and altitude sensors to selectively and sequentially deploy the impact energy reduction systems depending on the portion of the aircraft speed and altitude flight envelope in which the aircraft is operating when an emergency is detected.

Abstract: An aircraft is configured with a propulsion system having a rotor with both cyclic and collective control, and an axis of rotation about which the propulsion system rotates with respect to the fuselage. A control system is configured to use torque generated through cyclic control of the rotor to reposition the propulsion system around the axis of rotation without the need for an independent actuator mechanism to rotate the propulsion system, thus reducing the weight and mechanical complexity of the aircraft. The control system may also utilize the torque provided by one or more rotors to position one or more wings with respect to the airflow over the aircraft, exerting torque on the aircraft to control the direction of the aircraft.

Abstract: A battery heating system for a hybrid aircraft powertrain includes a combustion engine, a battery pack, a combustion engine coolant circuit, and a battery pack coolant circuit. The battery heating system further includes a heat exchanger configured to exchange heat between the combustion engine coolant circuit and the battery pack coolant circuit. The battery heating system further includes at least one throttling device operatively connected to one of the combustion engine coolant circuit or the battery pack coolant circuit. The battery heating system further includes a controller configured to transmit a signal to the at least one throttling device to adjust a flow of coolant through the heat exchanger of at least one of the combustion engine coolant circuit or the battery pack coolant circuit.

Abstract: An aircraft safety system includes impact energy reduction systems including: an aircraft parachute, at least one rotor configured for autorotation, and an energy absorbing system. An automatic control system uses data from speed and altitude sensors to selectively and sequentially deploy the impact energy reduction systems depending on the portion of the aircraft speed and altitude flight envelope in which the aircraft is operating when an emergency is detected.

Abstract: An aircraft is configured with a propulsion system having a rotor with both cyclic and collective control, and an axis of rotation about which the propulsion system rotates with respect to the fuselage. A control system is configured to use torque generated through cyclic control of the rotor to reposition the propulsion system around the axis of rotation without the need for an independent actuator mechanism to rotate the propulsion system, thus reducing the weight and mechanical complexity of the aircraft. The control system may also utilize the torque provided by one or more rotors to position one or more wings with respect to the airflow over the aircraft, exerting torque on the aircraft to control the direction of the aircraft.

Abstract: A training garment for a child is provided which includes a decorative article capable of association with adult behavior in the mind of the wearer of the garment, and which thus assists in the cognitive development of a desire to employ toilet facilities.