Abstract: A first propeller has a shorter blade length and a lower inertia than a second propeller. An electromagnetic field emitter is coupled to one of the first propeller or the second propeller and an electromagnetic field receptor is coupled to the other one that is not coupled to the electromagnetic field emitter. The electromagnetic field emitter emits an electromagnetic field. In response to the electromagnetic field: the electromagnetic field receptor and its coupled propeller rotate in a first rotational direction; and the electromagnetic field emitter and its coupled propeller rotate in a second and counter-rotational direction. In response to a second electromagnetic field associated with increasing torque: the first propeller increases and subsequently decreases its rotational speed; and the second propeller increases its rotational speed at a slower rate than the increase in the rotational speed of the first propeller.

Abstract: A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

Abstract: Boundary information for a three-dimensional (3D) flying space is obtained. An input associated with steering a vehicle is received from an input device and location information associated with the vehicle is received from a location sensor. A control signal for the vehicle is generated based at least in part on the boundary information, the input, and the location information. In the event the input would cause the vehicle to cross the boundary of the 3D flying space if obeyed, the control signal for the vehicle is generated so that the vehicle is prevented from crossing the boundary of the 3D flying space. In response to receiving an indication associated with the vehicle landing, the boundary information is modified so that the 3D flying space includes a landing pathway.

Abstract: A takeoff location and a landing location are received for an autonomous vertical takeoff and landing (VTOL) vehicle that includes a plurality of rotors. An autonomous and noise-reduced flight trajectory for the autonomous VTOL vehicle is determined based at least in part on the takeoff location, the landing location, a jerk function, and a noise function, including by minimizing the jerk function and minimizing the noise function. A set of one or more desired forces or moments is determined for the autonomous VTOL vehicle based at least in part on autonomous and noise-reduced flight trajectory. A plurality of motor control signals is determined for the plurality of rotors based at least in part on the set of one or more desired forces or moments.

Abstract: A system includes a power optimized energy source, an energy storage optimized source, and a network that combines a first current from the power optimized energy source and a second current from the energy storage optimized source in order to power a load at least during a high power demand event, including by connecting the power optimized energy source and the energy storage optimized source using a parallel connection.

Abstract: A landing zone indicator system which includes a battery that is configured to power a controller and a human vision output device, a controller that is configured to control human-visible light that is output by the human vision output device, and a human vision output device where the human-visible light output by the human vision output device generates an illuminated landing zone for a vertical takeoff and landing (VTOL) vehicle.

Abstract: Boundary information associated with a three-dimensional (3D) flying space is obtained, including a boundary of the 3D flying space. Location information associated with an aircraft is obtained, including a location of the aircraft. Information is presented based at least in part on the boundary information associated with the 3D flying space and the location information associated with the aircraft, including by presenting, in a display, the boundary of the 3D flying space and an avatar representing the aircraft at the location of the aircraft.

Abstract: A configuration instruction associated with configuring a plurality of batteries which supply power to a plurality of motors in a vehicle is received. The batteries are configuring as specified by the configuration instruction, where the batteries are able to be configured in a plurality of configurations, including: a first configuration where at least some of the batteries are electrically connected together in parallel and a second configuration where at least some of the batteries are electrically connected together in series.

Abstract: A pylon portion includes a first surface that attaches to an upper surface of a spar in a wing, where the pylon portion and a rotor portion protrude aft of the wing. A second surface attaches to a lower surface of the spar in the wing. The pylon portion also includes an intake air vent; a horizontal mounting surface; a rotor controller that is coupled to the horizontal mounting surface; and a heat sink that couples to the horizontal mounting surface and dissipates heat from at least the rotor controller. The rotor portion is moveably coupled to the pylon portion such that one or more rotor blades included in the rotor portion are able to move between: (1) a first position below the wing that is associated with a vertical flight mode and (2) a second position aft of the wing that is associated with a forward flight mode.

Abstract: A tiltrotor has a range of motion between a forward flight position and a hovering position, where a pylon and the tiltrotor are coupled via a telescoping actuator, a rigid bottom bar, and a fixed hinge that is attached between the rigid bottom bar and the tiltrotor. The tiltrotor moves from the forward flight position to the hovering position includes extending the telescoping actuator so that the tilt rotor rotates about the fixed hinge.

Abstract: A system includes an inboard tiltrotor subsystem and an outboard tiltrotor subsystem. The inboard tiltrotor subsystem includes an inboard pylon, an inboard tiltrotor, and a single and non-redundant drivetrain. The outboard tiltrotor subsystem includes an outboard pylon that is coupled to a wing and an outboard tiltrotor. The outboard tiltrotor has a range of motion and is coupled to the wing via the outboard pylon, such that the outboard tiltrotor is aft of the wing. The outboard tiltrotor subsystem further includes a redundant drivetrain (which has a plurality of motors and a plurality of motor controllers) that drives one or more blades and the one or more blades.

Abstract: A vehicle includes a tilt rotor that is aft of a wing and that is attached to the wing via a pylon. The tilt rotor has an adjustable maximum downward angle from horizontal that is less than or equal to 60° and that is set via a setting associated with a flight computer. The vehicle takes off and lands using at least some lift from the wing and from the tilt rotor. In response to a change to the adjustable maximum downward angle, via the setting associated with the flight computer, which produces a new maximum downward angle: the flight computer updates an actuator authority database associated with the flight computer to reflect the new maximum downward angle. Using the updated actuator authority database that reflects the new maximum downward angle, the flight computer generates a rotor control signal for the tilt rotor.

Abstract: In an embodiment, a system includes a frame configured to support a load, a first set of wheels provided on the frame, a second set of wheels provided on the frame, and a controller. The first set of wheels is configured to descend or ascend in response to the controller, and is oriented to move in a first direction. The second set of wheels is configured to descent or ascend in response to the controller, and is oriented to move in a different direction from the first direction. The controller configured to control the descent and ascent of the second set of wheels and the first set of wheels.

Abstract: A system is disclosed that includes an interface which receives sensor information associated with a vehicle, a severing tool, a parachute load limiting device state controller, and a reefing device. The controller determines, based at least in part on the sensor information, whether to instruct the severing tool to release a reefing device prior to parachute deployment. If it is determined to instruct the severing tool to release the reefing device prior to the parachute deployment, the severing tool is so instructed. If it is determined to not instruct the severing tool to release the reefing device prior to the parachute deployment, the reefing device is configured to be situated around a parachute canopy to constrain the parachute canopy during an initial state and slide down the parachute canopy to a position below the parachute canopy to constrain one or more parachute tethers.

Abstract: Sensor data is received from an inertial measurement unit on a vehicle. An observed attitude and an observed attitude rate of the vehicle are determined based on the sensor data. Using a model associated with a vehicle failure mode, an expected attitude and an expected attitude rate of the vehicle are determined. A malfunctioning rotor is determined based on the observed attitude, the observed attitude rate, the expected attitude, and the expected attitude rate. In response to identifying the malfunctioning rotor, a responsive action is performed, including by updating a geometry matrix so that at least one non-malfunctioning rotor in the plurality of rotors compensates for the malfunctioning rotor.

Abstract: An interference sensor dataset associated with interference between airflows from at least two rotors in a multicopter and a first isolated sensor dataset and a second isolated sensor dataset which are associated with isolated airflows from a first rotor and a second rotor in the multicopter, respectively, are received. A generalized flow model associated with a generalized rotor is received. An altitude for the multicopter is generated based at least in part on the interference sensor dataset, the first isolated sensor dataset, the second isolated sensor dataset, and the generalized flow model, including by using a non-linear filter that builds a consolidated probability function associated with altitude that reconciles the interference sensor dataset, the first isolated sensor dataset, and the second isolated sensor dataset with the generalized flow model.

Abstract: A first sensitivity level is used to interpret an input signal received from an input device in a vehicle while the vehicle is in a first region. A second sensitivity level is used to interpret the input signal received from the input device in the vehicle while the vehicle is in a second region, wherein the second sensitivity level is greater than the first sensitivity level.

Abstract: An electronic vertical takeoff and landing (eVTOL) multicopter which includes a communications interface configured to establish a communication channel between a site local server and the eVTOL multicopter and send a vehicle identifier and vehicle state information from the eVTOL multicopter to the site local server. The eVTOL multicopter also includes a processor configured to perform a management operation received from the site local server, wherein the site local server is configured to determine the management operation based at least in part on the vehicle identifier and the vehicle state information.

Abstract: A hinged propeller comprising a hub and one or more blades is disclosed. In various embodiments, a blade is connected to the hub via a hinge, wherein at least a substantial part of the blade has a longitudinal axis that is substantially parallel to a line extending radially from a center of the hub, and wherein the hinge has an axis of hinge rotation that is oriented at a non-zero acute angle to a line that is perpendicular, in a plane of rotation of the hub, to said longitudinal axis.

Abstract: An electric vertical take-off and landing (eVTOL) vehicle is positioned to be in a charging position on the ground, wherein the eVTOL vehicle is capable of performing vertical take-offs and landings. The battery is charged while in the charging position on the ground using a wind turbine that includes the rotor.