Provided is a non-motorized flying unit. The non-motorized flying unit includes a body part having a head part and a tail part having an accommodation space and a through hole, an image capturing unit installed in the through hole and configured to obtain an image information, a protective window installed in the through hole, a plurality of shock absorbing devices installed at the end portion of the tail part, a weight installed at the end portion of the tail part, and a lighting device installed at an end portion of the plurality of shock absorbing devices. A propulsion unit which is detachably coupled to the tail part storing a propellant which, upon combustion, forms pressure in the propulsion unit to provide thrust to the body part.

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 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.

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.

An aircraft system of an aircraft may, while the aircraft is flying in a first flight mode, receive data from one or more sensors of the aircraft and, based on received data from one or more sensors, identify an actuation failure of an actuator of a flight control surface. The vehicle system may, subsequent to identifying the actuation failure of the actuator of the flight control surface, control the aircraft to fly in a modified flight mode. Controlling the aircraft to fly in the modified flight mode may include: determining a directional bias caused by the actuation failure, determining a modified flight plan based on the determined directional bias, and controlling the aircraft to fly based on the modified flight plan and the directional bias.

An aircraft system of an aircraft may, while the aircraft is flying in a first flight mode, receive data from one or more sensors of the aircraft and, based on received data from one or more sensors, identify an actuation failure of an actuator of a flight control surface. The vehicle system may, subsequent to identifying the actuation failure of the actuator of the flight control surface, control the aircraft to fly in a modified flight mode. Controlling the aircraft to fly in the modified flight mode may include: determining a directional bias caused by the actuation failure, determining a modified flight plan based on the determined directional bias, and controlling the aircraft to fly based on the modified flight plan and the directional bias.

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 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 implement the method.