The present invention relates to an apparatus and method for capturing energy from an unmanned aircraft propeller system and utilizing the energy to charge a battery. The invention further provides for a belt drive system connected to one or more propellers of an unmanned aircraft system commonly referred to as a drone aircraft. The belt drive system may be linked to an alternator or dynamo such that a portion of the energy generated by the rotation force provided to the drive system of the propeller is captured by the alternator or dynamo. The present invention provides for a system where the rotational energy of the propellers is captured by an energy recovery system such as an alternator, dynamo or the like. The energy recovery system provides power to charge a battery which can be used to power the drive systems for the propellers, or other electronic systems.

The present invention relates to an apparatus and method for capturing energy from an unmanned aircraft propeller system and utilizing the energy to charge a battery. The invention further provides for a belt drive system connected to one or more propellers of an unmanned aircraft system commonly referred to as a drone aircraft. The belt drive system may be linked to an alternator or dynamo such that a portion of the energy generated by the rotation force provided to the drive system of the propeller is captured by the alternator or dynamo. The present invention provides for a system where the rotational energy of the propellers is captured by an energy recovery system such as an alternator, dynamo or the like. The energy recovery system provides power to charge a battery which can be used to power the drive systems for the propellers, or other electronic systems.

Fly-by-wire vehicle systems and related remote actuation systems and operating methods are provided for actuating a remote flight control component using an individual analog command signal communicated over an individual electrical cable or wire. An exemplary method involves logic, circuitry or other hardware at a remote actuation system receiving an analog input command signal, converting the analog input command signal to a rotational speed command in a commanded rotational direction based on a relationship between a current state of the signal characteristic and a reference state for the signal characteristic, converting the rotational speed command into a power conversion command based at least in part on the rotational speed command and the current state of the motor, and operating power conversion circuitry at the remote actuation system to provide power to the motor in accordance with the power conversion command to achieve the commanded rotation in the commanded rotational direction.

Fly-by-wire vehicle systems and related remote actuation systems and operating methods are provided for actuating a remote flight control component using an individual analog command signal communicated over an individual electrical cable or wire. An exemplary method involves logic, circuitry or other hardware at a remote actuation system receiving an analog input command signal, converting the analog input command signal to a rotational speed command in a commanded rotational direction based on a relationship between a current state of the signal characteristic and a reference state for the signal characteristic, converting the rotational speed command into a power conversion command based at least in part on the rotational speed command and the current state of the motor, and operating power conversion circuitry at the remote actuation system to provide power to the motor in accordance with the power conversion command to achieve the commanded rotation in the commanded rotational direction.

According to one embodiment, a flying body includes a radar, a supporter, a plurality of rotors supported by the supporter, and a controller. The rotors include a first rotor. The radar is configured to perform a detection operation and a non-detection operation. The controller is configured to perform a first control operation in a first transition from the non-detection operation to the detection operation. The controller is configured to perform a first change in the first control operation to change a rotational speed of the first rotor from a rotational speed of the first rotor in the non-detection operation. The detection operation is performed after the first control operation.

According to one embodiment, a flying body includes a radar, a supporter, a plurality of rotors supported by the supporter, and a controller. The rotors include a first rotor. The radar is configured to perform a detection operation and a non-detection operation. The controller is configured to perform a first control operation in a first transition from the non-detection operation to the detection operation. The controller is configured to perform a first change in the first control operation to change a rotational speed of the first rotor from a rotational speed of the first rotor in the non-detection operation. The detection operation is performed after the first control operation.

Systems and methods for a hub system are disclosed. The hub system includes: a motor operably coupled to a first correlated magnet, wherein the first correlated magnet defines a first attachment surface having one or more first alignment configurations. The hub system may further include a propeller hub including one or more blades, wherein the propeller hub is operably coupled to a second correlated magnet, and wherein the second correlated magnet defines a second attachment surface having one or more second alignment configurations. In addition, the motor and the propeller hub may be removably coupled together via one or more of: a magnetic attraction force formed between the first attachment surface of the first correlated magnet and the second attachment surface of the second correlated magnet; and an engagement between the one or more first alignment configurations and the one or more second alignment configurations.

An axial flux electric motor for an aircraft includes a first motor section having a first stator and a first rotor, and a second motor section having a second stator and a second rotor. The first and second rotors are mounted on a common axle. The first rotor is secured to the common axle by a first set of connecting elements. The second rotor is secured to the common axle by a second set of connecting elements. The first set of connecting elements is arranged to break when the relative torque between the common axle and the first rotor is greater than a first particular threshold. The second set of connecting elements is arranged to break when the relative torque between the common axle and the second rotor is greater than a second particular threshold.

The present disclosure discloses a method for attitude control of a quadrotor UAV, comprising establishing an attitude dynamics model of the quadrotor UAV, establishing a motion equation and a state-space equation of a UAV control system, determining an LADRC-CFO, and establishing a differential tracker for reducing a system overshoot.

The present disclosure discloses a method for attitude control of a quadrotor UAV, comprising establishing an attitude dynamics model of the quadrotor UAV, establishing a motion equation and a state-space equation of a UAV control system, determining an LADRC-CFO, and establishing a differential tracker for reducing a system overshoot.