Flying body including body portion and a plurality of propellers radially disposed to be laterally symmetrical from body portion is provided with: a plurality of motors respectively rotating the plurality of propellers; a plurality of power storage packs respectively supplying currents to the plurality of motors; and sub power storage pack connected to the plurality of power storage packs by power wirings, respectively. The same number of motors of the plurality of motors are installed on each of the left and right sides, and the same number of power storage packs of the plurality of power storage packs are installed on each of the left and right sides. Sub power storage pack is installed on a lateral center line of body portion.

Flying body including body portion and a plurality of propellers radially disposed to be laterally symmetrical from body portion is provided with: a plurality of motors respectively rotating the plurality of propellers; a plurality of power storage packs respectively supplying currents to the plurality of motors; and sub power storage pack connected to the plurality of power storage packs by power wirings, respectively. The same number of motors of the plurality of motors are installed on each of the left and right sides, and the same number of power storage packs of the plurality of power storage packs are installed on each of the left and right sides. Sub power storage pack is installed on a lateral center line of body portion.

The present invention provides a flying apparatus that can accurately measure a weight of a transported objected in a simple configuration. The flying apparatus 10 includes rotors 11, motors 12, a flight sensor 13, an electric power conversion unit 14, and a computation control unit 15. The flight sensor 13 measures physical quantities acting on a fuselage base portion 16. The computation control unit 15 generates instruction signals based on the physical quantities to cause the fuselage base portion 16 to be at a predetermined position in a predetermined attitude. The electric power conversion unit 14 adjusts amounts of electric power supplied to the motors 121 and the like based on the received instruction signals. Moreover, the computation control unit 15 calculates an estimated weight that is an estimation value of a weight of the transported object, based on magnitudes of the instruction signals.

A for providing control input adjustment for an aircraft, including one or more mode sensors disposed on an aircraft, a mode analysis system, the mode analysis system operable to receive mode sensor data from the one or more mode sensors, and operable to decompose the mode sensor data into decomposed mode data associated with fundamental modes of structural elements of the aircraft associated with the one or more mode sensors, and a flight control computer (FCC) disposed on the aircraft and connected to one or more actuators, the FCC operable to provide a control signal to the one or more actuators according to an association between the decomposed mode data and one or more rotorcraft parameters associated with the one or more actuators.

A for providing control input adjustment for an aircraft, including one or more mode sensors disposed on an aircraft, a mode analysis system, the mode analysis system operable to receive mode sensor data from the one or more mode sensors, and operable to decompose the mode sensor data into decomposed mode data associated with fundamental modes of structural elements of the aircraft associated with the one or more mode sensors, and a flight control computer (FCC) disposed on the aircraft and connected to one or more actuators, the FCC operable to provide a control signal to the one or more actuators according to an association between the decomposed mode data and one or more rotorcraft parameters associated with the one or more actuators.

A method for turning an aerial vehicle such as a drone-type vehicle is provided, according to one embodiment. The method provides for receiving a turning input and detecting a current momentum of the aerial vehicle. The method provides for converting the turning input into a yaw command and calculating a change in yaw associated with the turning input. The method provides for calculating a roll command based on the current momentum of the aerial vehicle and based on the change in yaw associated with the turning input. Further, the method provides for executing the yaw command and the roll command in synchrony, wherein the executing the yaw command and the roll command in synchrony causes the aerial vehicle to perform a turn.

Provided is an aerial vehicle, including: a package carrier including a plurality of vertical members being changeable in relative positions in a horizontal direction and surrounding a package in the horizontal direction to prevent falling of the package. A plurality of rotary wings are changeable in relative positions in the horizontal direction. The relative positions of the plurality of vertical members and the relative positions of the plurality of rotary wings are changeable. The package carrier is changed in shape in the horizontal direction in accordance with the relative positions of the plurality of vertical members. The change in the relative positions of the plurality of rotary wings is in conjunction with the shape of the package carrier.

Provided is an aerial vehicle, including: a package carrier including a plurality of vertical members being changeable in relative positions in a horizontal direction and surrounding a package in the horizontal direction to prevent falling of the package. A plurality of rotary wings are changeable in relative positions in the horizontal direction. The relative positions of the plurality of vertical members and the relative positions of the plurality of rotary wings are changeable. The package carrier is changed in shape in the horizontal direction in accordance with the relative positions of the plurality of vertical members. The change in the relative positions of the plurality of rotary wings is in conjunction with the shape of the package carrier.

An aircraft in the form of an electrically driven, vertical take-off and landing, preferably people-carrying and/or load-carrying multicopter (1) is provided, in which a multiplicity of rotors are arranged in a common rotor plane (R), in which a tail unit (6), protruding upward or downward with respect to the rotor plane (R), is provided above or below the rotor plane (R), preferably in a rear region of the aircraft (1) with respect to a forward flying direction.

An aircraft in the form of an electrically driven, vertical take-off and landing, preferably people-carrying and/or load-carrying multicopter (1) is provided, in which a multiplicity of rotors are arranged in a common rotor plane (R), in which a tail unit (6), protruding upward or downward with respect to the rotor plane (R), is provided above or below the rotor plane (R), preferably in a rear region of the aircraft (1) with respect to a forward flying direction.