Abstract: Modular units having one or more bays or compartments are installed into openings of aerial vehicles that are sized and configured to accommodate the modular units. Multiple items may be loaded into the respective bays or compartments of the modular unit, which is installed into an opening of an aerial vehicle, and carried by the aerial vehicle to locations where the items are to be delivered. Hatches or coverings of the bays or compartments are selectively operated to deploy the items therefrom at the designated locations. A modular unit may be selected for use in a mission based on a number of bays or compartments therein, or any other features of the modular unit, and installed in any number of aerial vehicles having appropriately sized and configured openings.

Abstract: A package delivery apparatus of a vehicle may include a servo, a servo arm rotated by the servo, a latch that rotates responsive to rotation of the servo arm, and a rod and slider that moves responsive to rotation of the servo arm. The components of the package delivery apparatus may move between a plurality of positions, including a loading position, a locking position, a sensing position, and a release position. The rotation of the latch may control loading, locking, sensing, and release of a package within a package path of the vehicle, and the movement of the rod and slider may control movement of a door assembly of the vehicle between open and closed positions.

Abstract: An aerial vehicle may include adjustable shrouds to selectively provide protection for propellers of the aerial vehicle. The adjustable shrouds may be moved to an extended configuration around a periphery of one or more propellers during generally vertical flight or hovering operations, when delivery a payload, and/or upon detecting objects in proximity. Likewise, the adjustable shrouds may be moved to a retracted configuration that eliminates or minimizes adverse aerodynamic effects during generally horizontal flight operations, when operating at high altitude, and/or upon detecting no objects in proximity. The adjustable shrouds may include various designs, such as fan shrouds, telescoping shrouds, folding shrouds, and deployable arm shrouds.

Abstract: Various mechanisms for adjusting pitches of propeller blades are described. For example, the pitch adjustment mechanism may include a propeller hub enclosing a geared mechanism that cooperates with a compound gearbox having first and second planetary stages to adjust pitches of propeller blades. Alternatively, the pitch adjustment mechanism may include a propeller hub enclosing a pitch adjustment assembly that utilizes tension cables and torsion springs, or rack-and-pinion structures, to adjust pitches of propeller blades. Using any of the various mechanisms, the pitches of propeller blades may be rotated at least 90 degrees, and up to and exceeding 360 degrees, in order to effect thrust reversals and/or adjust thrust profiles.

Abstract: Aerial vehicles may be equipped with propellers having pivotable blades that are configured to rotate when the propellers are not rotating under power. A pivotable blade may rotate about an axis of a propeller with respect to a hub until the pivotable blade is coaligned with a fixed blade. When the propeller is rotating, a lifting force from the blade may cause the blade to rotate to a deployed position that is not coaligned with the fixed blade.

Abstract: An aerial vehicle having a single wing is configured for vertical-flight and forward-flight operations. The wing has a substantially high aspect ratio. The aerial vehicle includes tilt motor assemblies disposed at a forward end and an aft end of a fuselage. The tilt motor assemblies are configured to orient motors and rotors vertically, horizontally, or at any angle between vertical and horizontal. A pair of parallel booms are mounted beneath the wing on either side of the fuselage. Each of the booms has at least one vertically oriented motor and rotor associated therewith, and a vertical fin extending thereunder. Additionally, a forward tilt motor assembly includes a rotatable extension that is deployed when the motor assembly is configured for vertical flight, enabling the aerial vehicle to land on the vertical fins and the landing rotatable extension.

Abstract: An aerial vehicle may include adjustable configurations to selectively provide protection for propellers of the aerial vehicle. Portions of the wing and/or the tail plane of the aerial vehicle may be reconfigured to an extended configuration around a periphery of one or more propellers during generally vertical flight or hovering operations, when delivery a payload, and/or upon detecting objects in proximity. Likewise, the portions of the wing and/or the tail plane may be reconfigured to a retracted configuration that eliminates or minimizes adverse aerodynamic effects during generally horizontal flight operations, when operating at high altitude, and/or upon detecting no objects in proximity. During the reconfiguration, portions of the leading edge of the wing may be extended or retracted, and/or portions of the tail plane may be extended, retracted, and/or rotated.

Abstract: Various mechanisms for adjusting pitches of propeller blades are described. For example, the pitch adjustment mechanism may include a propeller hub enclosing a geared mechanism that cooperates with a compound gearbox having first and second planetary stages to adjust pitches of propeller blades. Alternatively, the pitch adjustment mechanism may include a propeller hub enclosing a pitch adjustment assembly that utilizes tension cables and torsion springs, or rack-and-pinion structures, to adjust pitches of propeller blades. Using any of the various mechanisms, the pitches of propeller blades may be rotated at least 90 degrees, and up to and exceeding 360 degrees, in order to effect thrust reversals and/or adjust thrust profiles.

Abstract: Aerial vehicles may be equipped with propellers having pivotable blades that are configured to rotate when the propellers are not rotating under power. A pivotable blade may rotate about an axis of a propeller with respect to a hub until the pivotable blade is coaligned with a fixed blade. When the propeller is rotating a lifting force from the blade may cause the blade to rotate to a deployed position that is not coaligned with the fixed blade.

Abstract: An aerial vehicle having a single wing is configured for vertical-flight and forward-flight operations. The wing has a substantially high aspect ratio. The aerial vehicle includes tilt motor assemblies disposed at a forward end and an aft end of a fuselage. The tilt motor assemblies are configured to orient motors and rotors vertically, horizontally, or at any angle between vertical and horizontal. A pair of parallel booms are mounted beneath the wing on either side of the fuselage. Each of the booms has at least one vertically oriented motor and rotor associated therewith, and a vertical fin extending thereunder. Additionally, a forward tilt motor assembly includes a rotatable extension that is deployed when the motor assembly is configured for vertical flight, enabling the aerial vehicle to land on the vertical fins and the landing rotatable extension.