Abstract: A system for adjusting a load on a tethered aircraft is disclosed. The aircraft is tethered to a payload. The system determines a new position for the tethered aircraft in the event that due to environmental effects, e.g., the aircraft is flying upwind or downwind, the load experienced by the tethered aircraft is not optimal.

Abstract: A system for adjusting a load on a tethered aircraft is disclosed. The aircraft is tethered to a payload. The system determines a new position for the tethered aircraft in the event that due to environmental effects, e.g., the aircraft is flying upwind or downwind, the load experienced by the tethered aircraft is not optimal.

Abstract: A system for adjusting a load on a tethered aircraft is disclosed. The aircraft is tethered to a payload. The system determines a new position for the tethered aircraft in the event that due to environmental effects, e.g., the aircraft is flying upwind or downwind, the load experienced by the tethered aircraft is not optimal.

Abstract: A geometry-based flight control system is disclosed. In various embodiments, a set of inceptor inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is computed, including by taking into consideration dynamically varying effectiveness of one or more actuators based on a current dynamic state of the aircraft. An output comprising for each actuator in the optimal mix a corresponding set of one or more control signals associated with the set of actuator parameters computed for that actuator is provided.

Abstract: A geometry-based flight control system is disclosed. In various embodiments, a set of inceptor inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is computed, including by taking into consideration dynamically varying effectiveness of one or more actuators based on a current dynamic state of the aircraft. An output comprising for each actuator in the optimal mix a corresponding set of one or more control signals associated with the set of actuator parameters computed for that actuator is provided.

Abstract: A geometry-based flight control system is disclosed. In various embodiments, a set of inceptor inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is computed, including by taking into consideration dynamically varying effectiveness of one or more actuators based on a current dynamic state of the aircraft. An output comprising for each actuator in the optimal mix a corresponding set of one or more control signals associated with the set of actuator parameters computed for that actuator is provided.

Abstract: A system to maintain a phase difference is disclosed. Two or more aircraft fly in a continuous periodic trajectory. The system maintains a phase difference between the two or more aircraft. Telemetry information for a reference aircraft moving in a first periodic trajectory is received. A phase difference between a primary aircraft and the reference aircraft with respect to the first periodic trajectory is determined. A variance in the phase difference between the primary aircraft and the reference aircraft from the target phase difference is determined. A new trajectory for the primary aircraft that decreases the variance in the phase difference with respect to the new periodic trajectory is determined, and the primary aircraft is maneuvered to follow the new trajectory.

Abstract: While an aircraft is mid-flight, a braking start point associated with a stoppable rotor is calculated where the stoppable rotor includes a first and second blade and the stoppable rotor is configured to rotate about a substantially vertical axis. A process to stop the stoppable rotor is started, while the aircraft is mid-flight, when the stoppable rotor reaches the braking start point, where the stoppable rotor is stopped with the first blade pointing forward and the second blade pointing backward.

Abstract: A system for adjusting a load on a tethered aircraft is disclosed. The aircraft is tethered to a payload. The system determines a new position for the tethered aircraft in the event that due to environmental effects, e.g., the aircraft is flying upwind or downwind, the load experienced by the tethered aircraft is not optimal.

Abstract: A system to maintain a phase difference is disclosed. Two or more aircraft fly in a continuous periodic trajectory. The system maintains a phase difference between the two or more aircraft. Telemetry information for a reference aircraft moving in a first periodic trajectory is received. A phase difference between a primary aircraft and the reference aircraft with respect to the first periodic trajectory is determined. A variance in the phase difference between the primary aircraft and the reference aircraft from the target phase difference is determined. A new trajectory for the primary aircraft that decreases the variance in the phase difference with respect to the new periodic trajectory is determined, and the primary aircraft is maneuvered to follow the new trajectory.

Abstract: A system to maintain a phase difference is disclosed. Two or more aircraft fly in a continuous periodic trajectory. The system maintains a phase difference between the two or more aircraft. Telemetry information for a reference aircraft moving in a first periodic trajectory is received. A phase difference between a primary aircraft and the reference aircraft with respect to the first periodic trajectory is determined. A variance in the phase difference between the primary aircraft and the reference aircraft from the target phase difference is determined. A new trajectory for the primary aircraft that decreases the variance in the phase difference with respect to the new periodic trajectory is determined, and the primary aircraft is maneuvered to follow the new trajectory.

Abstract: A system for adjusting a load on a tethered aircraft is disclosed. The aircraft is tethered to a payload. The system determines a new position for the tethered aircraft in the event that due to environmental effects, e.g., the aircraft is flying upwind or downwind, the load experienced by the tethered aircraft is not optimal.

Abstract: An aircraft landing system is disclosed. In various embodiments, an aircraft landing system as disclosed herein includes a processor that determines to start a final stage of descent for the aircraft. The processor determines a set of commands for actuators of the aircraft, based on the determination to start the final stage of descent, to flare the aircraft while wings of the aircraft are substantially in a forward flight position followed by transitioning to a vertical tilt position and completing the landing in substantially vertical flight. The commands are provided to the actuators of the aircraft.

Abstract: While an aircraft is mid-flight, a braking start point associated with a stoppable rotor is calculated where the stoppable rotor includes a first and second blade and the stoppable rotor is configured to rotate about a substantially vertical axis. A process to stop the stoppable rotor is started, while the aircraft is mid-flight, when the stoppable rotor reaches the braking start point, where the stoppable rotor is stopped with the first blade pointing forward and the second blade pointing backward.

Abstract: While an aircraft is mid-flight, a braking start point associated with a stoppable rotor is calculated where the stoppable rotor includes a first and second blade and the stoppable rotor is configured to rotate about a substantially vertical axis. A process to stop the stoppable rotor is started, while the aircraft is mid-flight, when the stoppable rotor reaches the braking start point, where the stoppable rotor is stopped with the first blade pointing forward and the second blade pointing backward.

Abstract: A system to maintain a phase difference is disclosed. Two or more aircraft fly in a continuous periodic trajectory. The system maintains a phase difference between the two or more aircraft. Telemetry information for a reference aircraft moving in a first periodic trajectory is received. A phase difference between a primary aircraft and the reference aircraft with respect to the first periodic trajectory is determined. A variance in the phase difference between the primary aircraft and the reference aircraft from the target phase difference is determined. A new trajectory for the primary aircraft that decreases the variance in the phase difference with respect to the new periodic trajectory is determined, and the primary aircraft is maneuvered to follow the new trajectory.

Abstract: A system to maintain a phase difference is disclosed. Two or more aircraft fly in a continuous periodic trajectory. The system maintains a phase difference between the two or more aircraft. Telemetry information for a reference aircraft moving in a first periodic trajectory is received. A phase difference between a primary aircraft and the reference aircraft with respect to the first periodic trajectory is determined. A variance in the phase difference between the primary aircraft and the reference aircraft from the target phase difference is determined. A new trajectory for the primary aircraft that decreases the variance in the phase difference with respect to the new periodic trajectory is determined, and the primary aircraft is maneuvered to follow the new trajectory.

Abstract: An aircraft landing system is disclosed. In various embodiments, an aircraft landing system as disclosed herein includes a processor that determines to start a final stage of descent for the aircraft. The processor determines a set of commands for actuators of the aircraft, based on the determination to start the final stage of descent, to flare the aircraft while wings of the aircraft are substantially in a forward flight position followed by transitioning to a vertical tilt position and completing the landing in substantially vertical flight. The commands are provided to the actuators of the aircraft.