Abstract: An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.

Abstract: Certain exemplary embodiments can provide a system comprising a pressurized air source, a pressure regulator, an air flow control solenoid valve, a wastegate assembly, a reservoir assembly, a filter, a coolant flow control solenoid valve, a mixer assembly, and an outlet assembly. The pressure regulator is constructed to control a pressure of air from the air source. The wastegate assembly is constructed to control air pressure in the reservoir assembly. The filter is constructed to remove impurities from a coolant stream.

Abstract: An exemplary method includes controlling a rotation rate of a rotor in a vehicle, detecting that an electric motor system is electrically energized and rotating the rotor at least at a minimum rotation rate that is greater than zero in response to the electric motor system being electrically energized. The rotor may be rotated at least at the minimum rotation rate when the electric motor system is energized and the motor is turned-off.

Abstract: An exemplary electric distributed propulsion system includes two or more rotors that are individually controlled by the rotational speed of associated motors, an input control connected to the associated motors to provide rotational speed control to the two or more rotors to produce a desired net thrust, and a logic connected to the input control and the associated motors, the logic for controlling speed and direction of the two or more rotors to achieve the desired net thrust and to avoid a motor speed condition.

Abstract: Certain exemplary embodiments can provide a dolly comprising a frame, a set of guide rollers, a planetary disc, a set of rollers, and a caster. The frame comprises a plurality of cells. The set of guide rollers is coupled to the frame. The planetary disc constrained within a cell of the plurality of cells via the guide rollers. The set of rollers is coupled to the cell of the plurality of cells. Each of the plurality of rollers contacts a surface of the planetary disc. The set of rollers is constructed to distribute a load placed on the dolly over a surface of the planetary disc, thereby reducing a probability of failure of the dolly. The caster is coupled to the planetary disc.

Abstract: A yaw control system for a rotorcraft featuring a floor mounted pair of pedals configured to measure an up and down motion of a pair of pedals and utilize that up and down motion as a yaw moment control input. The pair of pedals can rock laterally, fore and aft, or vertically. The pair of pedals can be mechanically interconnected to other pairs of pedals or electrically interconnected to duplicate motion across pairs of pedals.

Abstract: Systems and methods include providing a helicopter, with a fuselage, a tail boom extending from the fuselage, a main rotor system, and a tail rotor assembly disposed on an aft end of the tail boom. The tail rotor assembly includes a tail rotor housing, at least one normal ducted fan that generate anti-torque thrust to prevent rotation of the fuselage, and at least one canted ducted fan configured to generate both anti-torque thrust to prevent of the fuselage and lift to the tail boom in order to control the pitch of the helicopter. The canted ducted fans generate sufficient lift to prevent a nose-up orientation of the helicopter when the center of gravity of the helicopter is shifted rearward behind the main rotor system, while the normal ducted fans maintain sufficient anti-torque thrust to prevent rotation of the fuselage when the main rotor is operated.

Abstract: An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.

Abstract: Systems and methods include providing an aircraft with a fuselage, a tail boom or empennage extending from the fuselage, a main rotor, a tail rotor, and at least one counter torque device. The counter torque device provides counter torque to the fuselage to prevent rotation of fuselage when the main rotor is operated, particularly in right sideward flight (RSF) for conventional helicopters with a counter-clockwise rotating (when viewed from above the helicopter) main rotor.

Abstract: In some implementations, a navigation application can integrate third party services into the navigation application in an easy to use and convenient manner. For example, the navigation application can receive user input indicating that the user is interested obtaining transportation from a ride hailing service. In response to receiving the indication, the navigation application can invoke an application extension for a third party ride hailing application. The navigation application and ride hailing application can then communicate to provide the ride hailing service through the navigation application.

Abstract: An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.

Abstract: In some implementations, a navigation application can integrate third party services into the navigation application in an easy to use and convenient manner. For example, the navigation application can receive user input indicating that the user is interested reserving a table from a table reservation service. In response to receiving the indication, the navigation application can invoke an application extension for a third party table reservation application. The navigation application and table reservation application can then communicate to provide the table reservation service through the navigation application.

Abstract: An exemplary vertical takeoff and landing includes a rotor driven by an electric motor, a generator located in a compartment and electrically connected to the electric motor, and an inlet formed through a side of the compartment to direct sideward airflow across the generator.

Abstract: A rotor system for a rotorcraft has a hub rotatable about an axis and a plurality of blades coupled to the hub for rotation therewith about the axis. Each blade is capable of rotation about a pitch axis relative to the hub, and a ring couples adjacent blades to each other.