A method and a device for assisting the piloting of a propeller rotorcraft having a rotary wing and at least one propeller. The piloting assistance device comprises a computer configured to display the following on a display: (i) a first scale representing a power consumed by the at least one propeller and carrying a minimum power mark and a maximum power mark, (ii) a second scale graduated in forward speed of the propeller rotorcraft, (iii) an index comprising a power section representing a current power consumed by the at least one propeller, the index comprising a speed section indicating a current forward speed on the second scale.

An abnormality diagnosis system performs an abnormality diagnosis of a plurality of motor systems that include a motor for moving a moving body. The abnormality diagnosis system identifies a comparison target system that is the motor system, among the motor systems, that is a comparison target in relation to a diagnosis target system that is the motor system to be a target of the abnormality diagnosis. The abnormality diagnosis system acquires a state-related value that is a value related to an operation state of the motor from each of the diagnosis target system and the comparison target system. The abnormality diagnosis system performs a comparison of the state-related value that is acquired from the diagnosis target system and the state-related value that is acquired from the comparison target system, and diagnoses a presence or absence of an abnormality in the diagnosis target system using a result of the comparison.

An abnormality diagnosis system performs an abnormality diagnosis of a plurality of motor systems that include a motor for moving a moving body. The abnormality diagnosis system identifies a comparison target system that is the motor system, among the motor systems, that is a comparison target in relation to a diagnosis target system that is the motor system to be a target of the abnormality diagnosis. The abnormality diagnosis system acquires a state-related value that is a value related to an operation state of the motor from each of the diagnosis target system and the comparison target system. The abnormality diagnosis system performs a comparison of the state-related value that is acquired from the diagnosis target system and the state-related value that is acquired from the comparison target system, and diagnoses a presence or absence of an abnormality in the diagnosis target system using a result of the comparison.

Disclosed herein is a VTOL tilt-wing aircraft that serves as a 4-6 passenger airliner for scheduled service between city centers and that is optimized for travel distances from 100-500 miles fully loaded with passengers and fuel. The VTOL aircraft solves technical, cost, and time problems inherent in other forms of transportation, including, but not limited to, rail, passenger airlines, and helicopters. The VTOL aircraft (1) takes off and lands like a helicopter, (2) flies fast like a jet, and (3) costs less than or comparable to a helicopter.

Embodiments include an aircraft comprising a fuselage; a wing connected to the fuselage; and first and second propulsion systems connected to the wing on opposite sides of the fuselage, wherein at least a portion of each of the first and second propulsion systems and at least a portion of the wing are tiltable between a first position in which the aircraft is in a hover mode and a second position in which the aircraft is in a cruise mode, wherein each of the propulsion systems includes pylon and a rotor assembly comprising a plurality of rotor blades.

Embodiments include an aircraft comprising a fuselage; a wing connected to the fuselage; and first and second propulsion systems connected to the wing on opposite sides of the fuselage, wherein at least a portion of each of the first and second propulsion systems and at least a portion of the wing are tiltable between a first position in which the aircraft is in a hover mode and a second position in which the aircraft is in a cruise mode, wherein each of the propulsion systems includes pylon and a rotor assembly comprising a plurality of rotor blades.

A plurality of energy storage packs (51 to 58) supply a current to a plurality of motor driver (31 to 38) that drive a plurality of motors (21 to 28) mounted on moving object (1), respectively. Sub energy storage pack (59) supplies a current to at least one of a plurality of first current paths connecting the plurality of motor driver (31 to 38) and the plurality of energy storage packs (51 to 58), or pulls a current from at least one of the plurality of first current paths. Controller (70) controls the plurality of first switches (S11 to S18) and the plurality of second switches (S21 to S28) to adjust capacities between the plurality of energy storage packs (51 to 58).

A plurality of energy storage packs (51 to 58) supply a current to a plurality of motor driver (31 to 38) that drive a plurality of motors (21 to 28) mounted on moving object (1), respectively. Sub energy storage pack (59) supplies a current to at least one of a plurality of first current paths connecting the plurality of motor driver (31 to 38) and the plurality of energy storage packs (51 to 58), or pulls a current from at least one of the plurality of first current paths. Controller (70) controls the plurality of first switches (S11 to S18) and the plurality of second switches (S21 to S28) to adjust capacities between the plurality of energy storage packs (51 to 58).

An improved aircraft design to harness advantages of vertical or short-takeoff and landings (V/STOL) and efficient horizontal flight. Configuration improves aircraft flight stability and efficiency in flight profiles: (1.) vertical flight; (2.) transition to and from horizontal flight and; (3.) horizontal flight on wings. The aircraft is capable of stable flight at any airspeed from hover to its maximum designed speed. It has the possibility of a controlled emergency landing using autorotation or, wings or, a combination of the two. Aircraft design includes: multiple thrust sources and, wings free to rotate on a spanwise axis. Wing rotation is independent—not coupled—with either the fuselage or, the thrust sources. Wing configurations include single, tandem or, multiple sets. Wings are coupled each other such that rotation induced in one wing affects rotation in all wings. Thrust sources are directed vertically during hover and some degree forward of vertical for horizontal flight. Thrust sources for vertical and horizontal flight can be the same rotors, such as in tilt-rotor configurations; or, divided between vertical flight rotors and horizontal flight rotors, such is in lift and cruise (a.k.a. lift and thrust) configurations.

An improved aircraft design to harness advantages of vertical or short-takeoff and landings (V/STOL) and efficient horizontal flight. Configuration improves aircraft flight stability and efficiency in flight profiles: (1.) vertical flight; (2.) transition to and from horizontal flight and; (3.) horizontal flight on wings. The aircraft is capable of stable flight at any airspeed from hover to its maximum designed speed. It has the possibility of a controlled emergency landing using autorotation or, wings or, a combination of the two. Aircraft design includes: multiple thrust sources and, wings free to rotate on a spanwise axis. Wing rotation is independent—not coupled—with either the fuselage or, the thrust sources. Wing configurations include single, tandem or, multiple sets. Wings are coupled each other such that rotation induced in one wing affects rotation in all wings. Thrust sources are directed vertically during hover and some degree forward of vertical for horizontal flight. Thrust sources for vertical and horizontal flight can be the same rotors, such as in tilt-rotor configurations; or, divided between vertical flight rotors and horizontal flight rotors, such is in lift and cruise (a.k.a. lift and thrust) configurations.