Systems, methods, lift fans, and aircraft involving active flow control of a ducted fan or fan-in-wing configuration are described.

Various examples are provided related to flight duration enhancement for rotorcraft and multicopters. In one example, a rotorcraft or multicopter includes one or more rotors, and one or more nozzles positioned in relationship to at least one corresponding rotor. The one or more nozzles can modulate, reshape, redirect, or adjust downwash produced by the corresponding rotor. The one or more nozzles can dynamically modulate, reshape, redirect, or adjust the downwash below the rotorcraft or multicopter. The one or more nozzles can be morphed or reshaped to dynamically modulate, reshape, redirect, or adjust the downwash using, e.g., a stochastic optimization framework and/or a motif-based auto-controller.

An unmanned aerial vehicle (UAV) includes lift rotors and control rotors. The lift rotors are mounted to the UAV and oriented to provide a first vertical thrust to the UAV. The control rotors are mounted to the UAV outboard of the lift rotors and oriented to provide a second vertical thrust to the UAV. The control rotors are each smaller than any of the lift rotors.

Methods and systems for controlling windmilling in an engine are described. An electric starter motor is coupled to the engine, a circuit element is coupled to the electric starter engine and to a DC signal source, and a control system coupled to the engine and to the circuit element. The control system is configured for: determining whether the engine is in a windmilling state; when the engine is in a windmilling state, commanding the circuit element to apply a DC signal to the electric starter motor; and modulating the DC signal applied to the electric starter motor to control a level of rotational motion of the engine.

Provided are a flying object control device, a flying object, and a program that can suppress occurrence of unintended turning in the flying object. A flying object control device has: a command value generation unit that generates a turning torque command value on the basis of a turning torque target value which is a target value of turning torque of a flying object; and an external disturbance countermeasure value generation unit that generates an external disturbance countermeasure value in accordance with turning torque generated by external disturbance, on the basis of the turning torque command value generated by the command value generation unit and a sensor detection value acquired by using a sensor provided to the flying object, wherein the command value generation unit generates the turning torque command value by subtracting the external disturbance countermeasure value generated by the external disturbance countermeasure value generation unit from the turning torque target value.

Provided are a flying object control device, a flying object, and a program that can suppress occurrence of unintended turning in the flying object. A flying object control device has: a command value generation unit that generates a turning torque command value on the basis of a turning torque target value which is a target value of turning torque of a flying object; and an external disturbance countermeasure value generation unit that generates an external disturbance countermeasure value in accordance with turning torque generated by external disturbance, on the basis of the turning torque command value generated by the command value generation unit and a sensor detection value acquired by using a sensor provided to the flying object, wherein the command value generation unit generates the turning torque command value by subtracting the external disturbance countermeasure value generated by the external disturbance countermeasure value generation unit from the turning torque target value.

The present disclosure provides a multi-rotor aerial vehicle. The multi-rotor aerial vehicle includes a body, the body including a first side and a second side opposite to each other; a first rotor connected to the first side of the body; and a second rotor connected to the second side of the body, a torque coefficient of the second rotor being different from a torque coefficient of the first rotor. When the multi-rotor aerial vehicle flies in a direction from the second side toward the first side or from the first side toward the second side, the first rotor rotates at a first rotational speed, the second rotor rotates at a second rotational speed, and an absolute value of a difference between the first rotational speed and the second rotational speed is less than a predetermined value.

An automated system for monitoring and treating pests in a crop field, comprising at least one trap for monitoring and identifying pests, at least one UA V containing at least one chemical or biological products; a home base for parking or storing said at least one UA V when they are not operating; at least one database server; and equipment for communicating with said at least one trap, said at least one home base, said at least one UA V and said at least one database server.

Methods and systems for controlling windmilling in an engine are described. An electric starter motor is coupled to the engine, a circuit element is coupled to the electric starter engine and to a DC signal source, and a control system coupled to the engine and to the circuit element. The control system is configured for: determining whether the engine is in a windmilling state; when the engine is in a windmilling state, commanding the circuit element to apply a DC signal to the electric starter motor; and modulating the DC signal applied to the electric starter motor to control a level of rotational motion of the engine.

In an embodiment, a rotorcraft includes a control element; a first control sensor connected to the control element, the first control sensor operable to generate position data indicating an actual position of the control element; and a flight control computer (FCC) in signal communication with the first control sensor, the FCC being operable to determine a suggested position for the control element, the FCC including an error monitor, the error monitor being operable to compare the suggested position of the control element with the actual position of the control element and determine whether the second control sensor is functional or defective, the FCC being further operable to provide a first flight management function when the second control sensor is determined to be functional, and the FCC being further operable to provide a second flight management function when the second control sensor is determined to be defective.