Abstract: An example embodiment includes a plurality of flight modules including a primary flight module and a secondary flight module. The embodiment includes a CAN controller, a second CAN controller, a first CAN bus configured to transmit primary control signals from the first CAN controller to the primary flight module and to the secondary flight module, and a second CAN bus configured to transmit secondary control signals from the second CAN controller to the primary flight module and the secondary flight module. The primary flight module is configured to perform functions responsive to receiving the primary control signals, and not in response to receiving the secondary control signals and the secondary flight module is configured to perform functions responsive to receiving the secondary control signals, and not in response to receiving the primary control signals.

Abstract: Systems and methods for dual-technology air traffic tracking are disclosed. An autonomous aerial vehicle (AAV) may include a low-power dual-technology transponder configured for transmitting real-time tracking data of the AAV in outbound tracking messages, using both first and second transmission technologies specified for operation within a common flight tracking system. The AAV may further include a global positioning satellite (GPS) system, one or more processors, and memory storing instructions for carrying out dual-technology tracking. Operations may include determining real-time tracking data of the AAV from the GPS system, and broadcasting outbound tracking messages alternatingly in time using the first and second technologies in ping-pong fashion, the outbound tracking messages including the determined real-time tracking data and an identifier of the AAV. The tracking data may include location of the AAV.

Abstract: An aerial vehicle includes one or more propeller units operable to provide thrust for takeoff or hover flight and one or more propulsion units operable to provide thrust for forward flight. At least one propeller unit includes a shaft coupled to a motor, and a first propeller blade and a second propeller blade that are both connected to the shaft. The second propeller blade is located substantially opposite the first propeller blade, and the second propeller blade has a surface area substantially perpendicular to an axis of rotation that is greater than a corresponding surface area of the first propeller blade. While the aerial vehicle is in forward flight in a first direction and the motor is turned off, the first propeller blade and the second propeller blade are each configured to orient in a second direction that is substantially parallel to the first direction, such that the first propeller blade is oriented substantially upwind of the second propeller blade.

Abstract: Systems and methods for dual-technology air traffic tracking are disclosed. An autonomous aerial vehicle (AAV) may include a low-power dual-technology transponder configured for transmitting real-time tracking data of the AAV in outbound tracking messages, using both first and second transmission technologies specified for operation within a common flight tracking system. The AAV may further include a global positioning satellite (GPS) system, one or more processors, and memory storing instructions for carrying out dual-technology tracking. Operations may include determining real-time tracking data of the AAV from the GPS system, and broadcasting outbound tracking messages alternatingly in time using the first and second technologies in ping-pong fashion, the outbound tracking messages including the determined real-time tracking data and an identifier of the AAV. The tracking data may include location of the AAV.

Abstract: Described herein are apparatuses that provided various features related to unmanned aerial vehicles (UAVs). An example apparatus may include, among other features, (i) a launch system for a UAV, (ii) a landing feature that is arranged on the apparatus so as to receive the UAV when the UAV returns from a flight, and (iii) a mechanical battery-replacement system that is configured to (a) remove a first battery from the UAV, and (b) after removal of the first battery, install a second battery in the UAV.

Abstract: Systems and methods for dual-technology air traffic tracking are disclosed. An autonomous aerial vehicle (AAV) may include a low-power dual-technology transponder configured for transmitting real-time tracking data of the AAV in outbound tracking messages, using both first and second transmission technologies specified for operation within a common flight tracking system. The AAV may further include a global positioning satellite (GPS) system, one or more processors, and memory storing instructions for carrying out dual-technology tracking. Operations may include determining real-time tracking data of the AAV from the GPS system, and broadcasting outbound tracking messages alternatingly in time using the first and second technologies in ping-pong fashion, the outbound tracking messages including the determined real-time tracking data and an identifier of the AAV. The tracking data may include location of the AAV.

Abstract: An example embodiment includes a plurality of flight modules including a primary flight module and a secondary flight module. The embodiment includes a CAN controller, a second CAN controller, a first CAN bus configured to transmit primary control signals from the first CAN controller to the primary flight module and to the secondary flight module, and a second CAN bus configured to transmit secondary control signals from the second CAN controller to the primary flight module and the secondary flight module. The primary flight module is configured to perform functions responsive to receiving the primary control signals, and not in response to receiving the secondary control signals and the secondary flight module is configured to perform functions responsive to receiving the secondary control signals, and not in response to receiving the primary control signals.

Abstract: Described herein are apparatuses that provided various features related to unmanned aerial vehicles (UAVs). An example apparatus may include, among other features, (i) a launch system for a UAV, (ii) a landing feature that is arranged on the apparatus so as to receive the UAV when the UAV returns from a flight, and (iii) a mechanical battery-replacement system that is configured to (a) remove a first battery from the UAV, and (b) after removal of the first battery, install a second battery in the UAV.

Abstract: An example embodiment includes a plurality of flight modules including a primary flight module and a secondary flight module. The embodiment includes a CAN controller, a second CAN controller, a first CAN bus configured to transmit primary control signals from the first CAN controller to the primary flight module and to the secondary flight module, and a second CAN bus configured to transmit secondary control signals from the second CAN controller to the primary flight module and the secondary flight module. The primary flight module is configured to perform functions responsive to receiving the primary control signals, and not in response to receiving the secondary control signals and the secondary flight module is configured to perform functions responsive to receiving the secondary control signals, and not in response to receiving the primary control signals.

Abstract: Described herein are apparatuses that provided various features related to unmanned aerial vehicles (UAVs). An example apparatus may include, among other features, (i) a launch system for a UAV, (ii) a landing feature that is arranged on the apparatus so as to receive the UAV when the UAV returns from a flight, and (iii) a mechanical battery-replacement system that is configured to (a) remove a first battery from the UAV, and (b) after removal of the first battery, install a second battery in the UAV.

Abstract: An aerial vehicle includes one or more propeller units operable to provide thrust for takeoff or hover flight and one or more propulsion units operable to provide thrust for forward flight. At least one propeller unit includes a shaft coupled to a motor, and a first propeller blade and a second propeller blade that are both connected to the shaft. The second propeller blade is located substantially opposite the first propeller blade, and the second propeller blade has a surface area substantially perpendicular to an axis of rotation that is greater than a corresponding surface area of the first propeller blade. While the aerial vehicle is in forward flight in a first direction and the motor is turned off, the first propeller blade and the second propeller blade are each configured to orient in a second direction that is substantially parallel to the first direction, such that the first propeller blade is oriented substantially upwind of the second propeller blade.

Abstract: An example embodiment includes a plurality of flight modules including a primary flight module and a secondary flight module. The embodiment includes a CAN controller, a second CAN controller, a first CAN bus configured to transmit primary control signals from the first CAN controller to the primary flight module and to the secondary flight module, and a second CAN bus configured to transmit secondary control signals from the second CAN controller to the primary flight module and the secondary flight module. The primary flight module is configured to perform functions responsive to receiving the primary control signals, and not in response to receiving the secondary control signals and the secondary flight module is configured to perform functions responsive to receiving the secondary control signals, and not in response to receiving the primary control signals.

Abstract: An aerial vehicle includes one or more propeller units operable to provide thrust for takeoff or hover flight and one or more propulsion units operable to provide thrust for forward flight. At least one propeller unit includes a shaft coupled to a motor, and a first propeller blade and a second propeller blade that are both connected to the shaft. The second propeller blade is located substantially opposite the first propeller blade, and the second propeller blade has a surface area substantially perpendicular to an axis of rotation that is greater than a corresponding surface area of the first propeller blade. While the aerial vehicle is in forward flight in a first direction and the motor is turned off, the first propeller blade and the second propeller blade are each configured to orient in a second direction that is substantially parallel to the first direction, such that the first propeller blade is oriented substantially upwind of the second propeller blade.

Abstract: Methods, systems, and devices for determining the placement of one or more lightning rods in one or more circles of non-interference in a solar field, where the placement is based on a determined location of one or more ungrounded triangular heliostat structures and one or more circles of interference, where the one or more circles of interference are areas within a range of motion of one or more heliostats disposed on corners of the one or more triangular heliostat structures in the solar field.

Abstract: A network topology for powering and communicating with groups of heliostats in a concentrated solar power plant. Heliostats are arranged in rows and wired together with inter-drive cables that distribute power and data from a field electrical system and plant network. Data is transmitted to and from heliostat drive control boards via network switches connected to intelligent power distribution units. Power is transmitted from battery banks to said intelligent power distribution units. Communication interface modules supply a connection between intelligent power distribution units and the heliostat control boards of non-adjacent heliostat rows to create communication and data loops having improved redundancy and robustness in the event of single point component failures.