Abstract: Techniques for leveraging information from a first satellite network to improve communications with a second satellite network are described. According to some embodiments, an endpoint device in an LPWAN communicates with satellites in a GNSS as well as with satellites in another satellite network (e.g., an LPWAN satellite network). By communicating with the GNSS satellites, the endpoint device is able to determine one or more locations in the sky overhead that provide favorable (e.g., unobstructed) communication paths between the endpoint device and satellites in those locations. Then, using ephemeris data for both satellite constellations, the endpoint device determines a time when one or more satellites of the LPWAN satellite network will be in (or near to) one or more of those same locations. At the determined time, the endpoint device transmits data to be received by the one or more satellites of the LPWAN satellite network.

Abstract: Package delivery systems and methods may include a bistable beam coupled to an aerial vehicle, a bistable hook coupled to an end of the bistable beam, and a package carried by the bistable hook. The bistable beam may move between a reeled position and an extended position, and the bistable hook may move between a closed position and an open position. In addition, the bistable beam may include frangible connections or portions. Further, release or disconnection of frangible connections or portions of the bistable beam, as well as operations of the bistable hook, may be effected by passive or active methods.

Abstract: Systems and methods to reduce aerodynamic drag and/or affect flight characteristics of an aerial vehicle may include adjustable fairings associated with one or more components of the aerial vehicle. The adjustable fairings may be coupled to and at least partially surround a motor, propulsion mechanism, motor arm, strut, or other component of an aerial vehicle. In addition, the adjustable fairings may be passively movable between two or more positions responsive to airflow around the fairings, and/or the adjustable fairings may be actively moved between two more positions to affect flight characteristics. Further, the adjustable fairings may include actuatable elements to alter a portion of an outer surface of the fairings to thereby affect flight characteristics. In this manner, adjustable fairings associated with various components of an aerial vehicle may reduce aerodynamic drag and/or may improve control and safety of an aerial vehicle.

Abstract: Systems and methods to reduce aerodynamic drag and/or affect flight characteristics of an aerial vehicle may include adjustable fairings associated with one or more components of the aerial vehicle. The adjustable fairings may be coupled to and at least partially surround a motor, propulsion mechanism, motor arm, strut, or other component of an aerial vehicle. In addition, the adjustable fairings may be passively movable between two or more positions responsive to airflow around the fairings, and/or the adjustable fairings may be actively moved between two more positions to affect flight characteristics. Further, the adjustable fairings may include actuatable elements to alter a portion of an outer surface of the fairings to thereby affect flight characteristics. In this manner, adjustable fairings associated with various components of an aerial vehicle may reduce aerodynamic drag and/or may improve control and safety of an aerial vehicle.

Abstract: Various reconfigurations of propellers, propeller blades, and/or blade sections of propulsion mechanisms of an aerial vehicle are described. For example, responsive to a fault or failure of a propulsion mechanism, propellers, propeller blades, and/or blade sections of the remaining propulsion mechanisms may be modified to maintain control and safety of the aerial vehicle. In example embodiments, angular orientations, positions, and/or lengths of one or more propellers, propeller blades, and/or blade sections of propulsion mechanisms may be modified to maintain control and safety in either a horizontal, wingborn flight orientation, or a vertical, VTOL flight orientation.

Abstract: Various reconfigurations of propulsion mechanisms of an aerial vehicle are described. For example, responsive to a fault or failure of a propulsion mechanism, the remaining propulsion mechanisms may be modified to maintain control and safety of the aerial vehicle. In example embodiments, cant angles, toe angles, positions, and/or orientations of one or more propulsion mechanisms may be modified to maintain control and safety in either a horizontal, wingborn flight orientation, or a vertical, VTOL flight orientation.

Abstract: Systems and methods to improve stability and control of an aerial vehicle are described. For an aerial vehicle having a ring wing around a fuselage and a plurality of propulsion mechanisms, one or more sections of the ring wing may be pivotable to reduce vibrations and forces transferred to the aerial vehicle, and to prevent stall and minimize turbulence experienced by the aerial vehicle. The pivotable sections of the ring wing may be freely pivotable, may include locking elements to prevent or allow pivoting, may include bias elements or dampening elements to partially control the free pivoting, or may include actuators to effect desired pivoting.

Abstract: Various reconfigurations of wing sections of a ring wing of an aerial vehicle are described. For example, responsive to a fault or failure of a propulsion mechanism, one or more wing sections may be modified to maintain control and safety of the aerial vehicle. In example embodiments, positions, angular orientations, and/or pitches of one or more wing sections may be modified to maintain control and safety in either a horizontal, wingborn flight orientation, or a vertical, VTOL flight orientation.

Abstract: Systems and methods to reduce aerodynamic drag and/or affect flight characteristics of an aerial vehicle may include adjustable fairings associated with one or more components of the aerial vehicle. The adjustable fairings may be coupled to and at least partially surround a motor, propulsion mechanism, motor arm, strut, or other component of an aerial vehicle. In addition, the adjustable fairings may be passively movable between two or more positions responsive to airflow around the fairings, and/or the adjustable fairings may be actively moved between two more positions to affect flight characteristics. Further, the adjustable fairings may include actuatable elements to alter a portion of an outer surface of the fairings to thereby affect flight characteristics. In this manner, adjustable fairings associated with various components of an aerial vehicle may reduce aerodynamic drag and/or may improve control and safety of an aerial vehicle.

Abstract: Systems and methods related to passive variable pitch propellers are described. For example, an aerial vehicle may include one or more passive variable pitch propellers, and such propellers may include one or more passively movable propeller blades having respective hinges, flexible joints, or torsionally flexible joints. Based at least in part on current flight configurations, required thrust, and/or desired advance ratios, the passively movable propeller blades may modify their coning angles and/or pitches, such that the passive variable pitch propellers may operate with improved efficiency in two or more flight configurations. For example, in a VTOL flight configuration, the passive variable pitch propellers may have increased coning angles and decreased pitches, whereas in a horizontal flight configuration, the passive variable pitch propellers may have decreased coning angles and increased pitches.

Abstract: Various reconfigurations of wing sections of a ring wing of an aerial vehicle are described. For example, responsive to a fault or failure of a propulsion mechanism, one or more wing sections may be modified to maintain control and safety of the aerial vehicle. In example embodiments, positions, angular orientations, and/or pitches of one or more wing sections may be modified to maintain control and safety in either a horizontal, wingborn flight orientation, or a vertical, VTOL flight orientation.

Abstract: Various reconfigurations of propellers, propeller blades, and/or blade sections of propulsion mechanisms of an aerial vehicle are described. For example, responsive to a fault or failure of a propulsion mechanism, propellers, propeller blades, and/or blade sections of the remaining propulsion mechanisms may be modified to maintain control and safety of the aerial vehicle. In example embodiments, angular orientations, positions, and/or lengths of one or more propellers, propeller blades, and/or blade sections of propulsion mechanisms may be modified to maintain control and safety in either a horizontal, wingborn flight orientation, or a vertical, VTOL flight orientation.

Abstract: Various reconfigurations of propulsion mechanisms of an aerial vehicle are described. For example, responsive to a fault or failure of a propulsion mechanism, the remaining propulsion mechanisms may be modified to maintain control and safety of the aerial vehicle. In example embodiments, cant angles, toe angles, positions, and/or orientations of one or more propulsion mechanisms may be modified to maintain control and safety in either a horizontal, wingborn flight orientation, or a vertical, VTOL flight orientation.

Abstract: Systems and methods to improve stability and control of an aerial vehicle are described. For an aerial vehicle having a ring wing around a fuselage and a plurality of propulsion mechanisms, one or more sections of the ring wing may be pivotable to reduce vibrations and forces transferred to the aerial vehicle, and to prevent stall and minimize turbulence experienced by the aerial vehicle. The pivotable sections of the ring wing may be freely pivotable, may include locking elements to prevent or allow pivoting, may include bias elements or dampening elements to partially control the free pivoting, or may include actuators to effect desired pivoting.