Abstract: In general, one aspect disclosed features an apparatus, comprising: a battery; a resistive load; a switch comprising a first transistor and a second transistor; a resistor; an inductor; and a control circuit; wherein the switch, the resistor, and the inductor are coupled in series between the battery and the resistive load; and wherein the control circuit controls the switch based on a voltage across the resistor. In general, another aspect disclosed features an apparatus, comprising: a battery; a resistive load; a switch; a resistor; an inductor; and a control circuit; wherein the switch, the resistor, and the inductor are coupled in series between the battery and the resistive load; and wherein the control circuit controls the switch based on a voltage across the resistor.

Abstract: Systems and methods are provided for a high efficiency cold plate system. A high efficiency cold plate system may include an interior surface. A heat source may be configured adjacent to a lower portion of the interior surface. The interior surface may enclose an interior region. The interior surface may also include members extending across the interior surface. The members may be separated by an orifice. The members and interior surface may defined an inlet region and an outlet region. The inlet and outlet regions may be fluidly joined by an orifice separating the members extending across the interior surface. The members may be angled relative to a lower portion of the interior surface. Angling the members may allow the system to constrain and direct fluid flowing through the system to achieve efficient cooling.

Abstract: Systems and methods are provided for a high efficiency cold plate system. A high efficiency cold plate system may include an interior surface. A heat source may be configured adjacent to a lower portion of the interior surface. The interior surface may enclose an interior region. The interior surface may also include members extending across the interior surface. The members may be separated by an orifice. The members and interior surface may defined an inlet region and an outlet region. The inlet and outlet regions may be fluidly joined by an orifice separating the members extending across the interior surface. The members may be angled relative to a lower portion of the interior surface. Angling the members may allow the system to constrain and direct fluid flowing through the system to achieve efficient cooling.

Abstract: Systems and methods for controlling flight via a parallel hybrid aircraft having an electric propulsion system and a combustion propulsion system are disclosed. Exemplary implementations may include: a combustion propulsion system including a combustion engine; an electric propulsion system including a motor and an electric power source, wherein the motor comprises a stator, a rotor coupled to the engine shaft, and support bearings between the rotor and the stator; a mechanical link coupled to the stator and the combustion engine, wherein the mechanical link substantially prevents movement of the stator in a rotational degree of freedom; and a propeller coupled to the engine shaft, wherein the rotor is coupled to the engine shaft between the propeller and the combustion engine.

Abstract: In general, one aspect disclosed features an apparatus, comprising: a battery; a resistive load; a switch comprising a first transistor and a second transistor; a resistor; an inductor; and a control circuit; wherein the switch, the resistor, and the inductor are coupled in series between the battery and the resistive load; and wherein the control circuit controls the switch based on a voltage across the resistor. In general, another aspect disclosed features an apparatus, comprising: a battery; a resistive load; a switch; a resistor; an inductor; and a control circuit; wherein the switch, the resistor, and the inductor are coupled in series between the battery and the resistive load; and wherein the control circuit controls the switch based on a voltage across the resistor.

Abstract: A system for maintaining a fleet of aircraft batteries located at multiple airports. The system may be configured to obtain charge information and battery health information for individual batteries within the fleet of aircraft batteries from charging containers located at individuals ones of the multiple airports. The charge information may include charge statuses of the individual batteries and/or the battery health information may characterize the degradation of the individual batteries over time. The system may determine predictions of one or more batteries to be re-allocated and/or to receive maintenance based on the battery health information. The system may generate a battery management plan including the one or more predictions recommending one or more batteries to be re-allocated and/or to receive maintenance.

Abstract: Disclosed herein are a vehicle system and method for VTOL. The vehicle system includes: a carrier vehicle and a cruise vehicle. The carrier vehicle includes one or more fuselages, one or more wings, one or more attach units coupled to the one or more fuselages or to the one or more wings, and propulsion systems operable to provide, at least, substantially vertical thrust and substantially horizontal thrust. The cruise vehicle includes one or more fuselages for carrying passengers or cargo and one or more wings. The one or more attach units of the carrier vehicle are adapted to couple to the cruise vehicle to detachably engage.

Abstract: In general, one aspect disclosed features a battery system for a vehicle, the battery system comprising: multiple battery modules, wherein each battery module comprises one or more battery cells, and wherein each battery module comprises an exhaust port; and one or more structural members mechanically coupled to the multiple battery modules; wherein the one or more structural members and the multiple battery modules define an exhaust chamber; wherein the exhaust chamber is in fluid communication with the exhaust ports of the multiple battery modules; wherein the one or more structural members comprise an outlet port in fluid communication with the exhaust chamber and an exterior of the exhaust chamber.

Abstract: Disclosed herein are a vehicle system and method for VTOL. The vehicle system includes: a carrier vehicle and a cruise vehicle. The carrier vehicle includes one or more fuselages, one or more wings, one or more attach units coupled to the one or more fuselages or to the one or more wings, and propulsion systems operable to provide, at least, substantially vertical thrust and substantially horizontal thrust. The cruise vehicle includes one or more fuselages for carrying passengers or cargo and one or more wings. The one or more attach units of the carrier vehicle are adapted to couple to the cruise vehicle to detachably engage.

Abstract: Systems and methods for controlling flight via a parallel hybrid aircraft having an electric propulsion system and a combustion propulsion system are disclosed. Exemplary implementations may include: a combustion propulsion system including a combustion engine; an electric propulsion system including a motor and an electric power source, wherein the motor comprises a stator, a rotor coupled to the engine shaft, and support bearings between the rotor and the stator; a mechanical link coupled to the stator and the combustion engine, wherein the mechanical link substantially prevents movement of the stator in a rotational degree of freedom; and a propeller coupled to the engine shaft, wherein the rotor is coupled to the engine shaft between the propeller and the combustion engine.

Abstract: In general, one aspect disclosed features a battery system for a vehicle, the battery system comprising: multiple battery modules, wherein each battery module comprises one or more battery cells, and wherein each battery module comprises an exhaust port; and one or more structural members mechanically coupled to the multiple battery modules; wherein the one or more structural members and the multiple battery modules define an exhaust chamber; wherein the exhaust chamber is in fluid communication with the exhaust ports of the multiple battery modules; wherein the one or more structural members comprise an outlet port in fluid communication with the exhaust chamber and an exterior of the exhaust chamber.

Abstract: In general, one aspect disclosed features a battery system for a vehicle, the battery system comprising: multiple battery modules, wherein each battery module comprises one or more battery cells, and wherein each battery module comprises an exhaust port; and one or more structural members mechanically coupled to the multiple battery modules; wherein the one or more structural members and the multiple battery modules define an exhaust chamber; wherein the exhaust chamber is in fluid communication with the exhaust ports of the multiple battery modules; wherein the one or more structural members comprise an outlet port in fluid communication with the exhaust chamber and an exterior of the exhaust chamber.

Abstract: A system for determining and/or controlling motor thrust and engine thrust in a parallel hybrid aircraft. One or more sensors may be configured to monitor one or more flight parameters to generate sensor information. User input including one or more pilot estimates may be received. The sensor information may be obtained. A performance thrust ratio may be calculated based on the user input, the sensor information, an aerodynamic model, a propeller model, and a battery model. The performance thrust ratio may be used to control the motor thrust and engine thrust to improve utilization of electric energy throughout a flight. A first thrust setting for the motor and/or a second thrust setting for the engine may be determined based on the performance thrust ratio.

Abstract: A propulsion system for a hybrid electric vehicle comprises a traction motor having first and second stator windings; a power source having a DC power output coupled to the first windings; a battery having a DC power output coupled to the second windings; and a controller to independently control: (i) a first power level output at the first DC power output, and (ii) a second power level of motive power output by the traction motor; wherein responsive to a signal to set the second power level less than full capacity of the traction motor, the controller provides a power difference between the first and second power levels from the second windings to the battery.

Abstract: A system for determining and/or controlling motor thrust and engine thrust in a parallel hybrid aircraft. One or more sensors may be configured to monitor one or more flight parameters to generate sensor information. User input including one or more pilot estimates may be received. The sensor information may be obtained. A performance thrust ratio may be calculated based on the user input, the sensor information, an aerodynamic model, a propeller model, and a battery model. The performance thrust ratio may be used to control the motor thrust and engine thrust to improve utilization of electric energy throughout a flight. A first thrust setting for the motor and/or a second thrust setting for the engine may be determined based on the performance thrust ratio.

Abstract: A system for maintaining a fleet of aircraft batteries located at multiple airports. The system may be configured to obtain charge information and battery health information for individual batteries within the fleet of aircraft batteries from charging containers located at individuals ones of the multiple airports. The charge information may include charge statuses of the individual batteries and/or the battery health information may characterize the degradation of the individual batteries over time. The system may determine predictions of one or more batteries to be re-allocated and/or to receive maintenance based on the battery health information. The system may generate a battery management plan including the one or more predictions recommending one or more batteries to be re-allocated and/or to receive maintenance.

Abstract: A system for determining and/or controlling motor thrust and engine thrust in a parallel hybrid aircraft. One or more sensors may be configured to monitor one or more flight parameters to generate sensor information. User input including one or more pilot estimates may be received. The sensor information may be obtained. A performance thrust ratio may be calculated based on the user input, the sensor information, an aerodynamic model, a propeller model, and a battery model. The performance thrust ratio may be used to control the motor thrust and engine thrust to improve utilization of electric energy throughout a flight. A first thrust setting for the motor and/or a second thrust setting for the engine may be determined based on the performance thrust ratio.

Abstract: A system for maintaining a fleet of aircraft batteries located at multiple airports. The system may be configured to obtain charge information and battery health information for individual batteries within the fleet of aircraft batteries from charging containers located at individuals ones of the multiple airports. The charge information may include charge statuses of the individual batteries and/or the battery health information may characterize the degradation of the individual batteries over time. The system may determine predictions of one or more batteries to be re-allocated and/or to receive maintenance based on the battery health information. The system may generate a battery management plan including the one or more predictions recommending one or more batteries to be re-allocated and/or to receive maintenance.

Abstract: A structurally-integrated battery pack may comprise an outer skin, an inner skin, structural foam, battery cells, and/or other components. Structural foam may be disposed between the outer skin and the inner skin. The structural foam may include battery voids and/or one or more cooling channels. Battery cells may be disposed within the battery voids. The battery cells within the battery voids and the structural foam may form layers. The layers may comprise a first layer including a first structural foam layer, a second layer including a first battery disposed within a first battery void, a third layer including at least a partial structural foam layer, and/or other layers. The partial structural foam layer may at least partially form a cooling channel. The outer skin, the inner skin, the structural foam, and/or the battery cells may be incorporated into a structural or non-structural element of an aircraft and/or vehicle.

Abstract: An oblique rotor-wing aircraft may be capable of vertical take-off and landing, subsonic cruise, transonic cruise, and/or supersonic cruise. The oblique rotor-wing aircraft may comprise one or more of a fuselage, a rotor-wing, a thrust-vectored propulsion system, a locking mechanism, and/or other components. The rotor-wing may be rotatably coupled to the fuselage. The rotor-wing may rotate about an axis in a first flight mode for vertical takeoff and landing. The oblique rotor-wing aircraft may include a thrust-vectored propulsion system that drives the rotation of the rotor-wing about the axis. The thrust-vectored propulsion system may include multiple, separately operable propulsion systems coupled to the rotor-wing and/or the fuselage. The oblique rotor-wing aircraft may comprise a locking mechanism that locks the rotor-wing at an angle oblique to the fuselage responsive to initiation of a second flight mode. The rotor-wing may be fixed at an angle oblique to the fuselage during the second flight mode.