A method, preferably including: sampling inputs, determining aircraft conditions, and/or acting based on the aircraft conditions. A method, preferably including: sampling inputs, determining input reliability, determining guidance, and/or controlling aircraft operation. A method, preferably including: operating the vehicle, planning for contingencies, detecting undesired flight conditions, and/or reacting to undesired flight conditions. A system, preferably an aircraft such as a rotorcraft, configured to implement the method.

A method, preferably including: sampling inputs, determining aircraft conditions, and/or acting based on the aircraft conditions. A method, preferably including: sampling inputs, determining input reliability, determining guidance, and/or controlling aircraft operation. A method, preferably including: operating the vehicle, planning for contingencies, detecting undesired flight conditions, and/or reacting to undesired flight conditions. A system, preferably an aircraft such as a rotorcraft, configured to implement the method.

A method, preferably including: sampling inputs, determining aircraft conditions, and/or acting based on the aircraft conditions. A method, preferably including: sampling inputs, determining input reliability, determining guidance, and/or controlling aircraft operation. A method, preferably including: operating the vehicle, planning for contingencies, detecting undesired flight conditions, and/or reacting to undesired flight conditions. A system, preferably an aircraft such as a rotorcraft, configured to implement the method.

Disclosed is a deceleration apparatus comprising a main center shaft; a plurality of disks; and, a means for moving each disk along the longitudinal axis of the main center shaft; wherein each disk comprises an outer annular ring, a plurality of vanes, and an inner annular ring; wherein each vane having an outer end and an inner end; wherein each vane extends between the outer annular ring and the inner annular ring; wherein the outer end is coupled to the outer annular ring; wherein the inner end is coupled to the inner annular ring; and, wherein the inner annular ring of each disk is movably attached to the main center shaft. The deceleration may further comprise a connector and a cargo container. The means for moving each disk along the longitudinal axis of the main center shaft may include a motorized winch.

Disclosed is a deceleration apparatus comprising a main center shaft; a plurality of disks; and, a means for moving each disk along the longitudinal axis of the main center shaft; wherein each disk comprises an outer annular ring, a plurality of vanes, and an inner annular ring; wherein each vane having an outer end and an inner end; wherein each vane extends between the outer annular ring and the inner annular ring; wherein the outer end is coupled to the outer annular ring; wherein the inner end is coupled to the inner annular ring; and, wherein the inner annular ring of each disk is movably attached to the main center shaft. The deceleration may further comprise a connector and a cargo container. The means for moving each disk along the longitudinal axis of the main center shaft may include a motorized winch.

An electronic device includes an input/output interface capable of being electrically connected to a 3-dimensional movable accessory and a processor electrically connected to the input/output interface. The processor is configured to sense an event generated in the electronic device and to transmit a command to operate the accessory to the accessory through the input/output interface in response to the event.

A non-motorized flying unit for observation according to an exemplary embodiment of the present disclosure includes: a body part which is mounted on a launcher, launched in a direction toward a preset target when the launcher operates, and falls, by its own weight, toward the ground from a position of a top dead point (TDP); a propeller unit which is coupled to the body part, and automatically generates rotational force by means of drag force applied to the body part when the body part falls so as to decrease a falling velocity of the body part; and an image capturing unit which is installed on the body part, and obtains image information in respect to the ground when the body part falls.

Disclosed herein is are systems, devices, and methods for an autorotating aerial device which includes a housing member having disposed thereon an actuator and a controller configured to control the actuator. The device also includes a wing member coupled to the actuator, the wing member including a main wing portion and a flap portion adjustable with respect to the main wing portion. The controller is configured to control the actuator to switch the autorotating aerial device between a diving mode of operation and an autorotating mode of operation based on adjusting an angle of attack of the flap portion, the angle of attack being with respect to a lateral axis along the main wing portion.

Disclosed herein is are systems, devices, and methods for an autorotating aerial device which includes a housing member having disposed thereon an actuator and a controller configured to control the actuator. The device also includes a wing member coupled to the actuator, the wing member including a main wing portion and a flap portion adjustable with respect to the main wing portion. The controller is configured to control the actuator to switch the autorotating aerial device between a diving mode of operation and an autorotating mode of operation based on adjusting an angle of attack of the flap portion, the angle of attack being with respect to a lateral axis along the main wing portion.

A payload delivery device configured to deliver an aircraft deployed payload along a flight path to a predetermined landing destination includes a support member configured to be removably attached to the payload, a flight control and navigation system module configured to control orientation of the plurality of control surfaces while the payload is travelling along the flight path to the predetermined landing destination, a control surface assembly module including a plurality of control surfaces, a rotor assembly including a plurality of rotor blades having a central axis of rotation, and a collective control assembly module including at least one collective servomotor configured to control a plurality of control linkages connected to the plurality of rotor blades.