To provide an aircraft that can efficiently improve speed performance and fuel efficiency, the aircraft is an aircraft capable of forward flight and hovering, and includes a lift generating part, a frame for holding the lift generating part, and a loadable object provided on the frame and to be mounted. The front projection area of the frame and the mounting part during forward flight is smaller than the front projection area of the frame and the mounting part during hovering.

To provide an aircraft that can efficiently improve speed performance and fuel efficiency, the aircraft is an aircraft capable of forward flight and hovering, and includes a lift generating part, a frame for holding the lift generating part, and a loadable object provided on the frame and to be mounted. The front projection area of the frame and the mounting part during forward flight is smaller than the front projection area of the frame and the mounting part during hovering.

A multicopter comprises: a support; rotors supported by the support; an internal combustion engine supported by the support; a generator supported by the support and driven by the internal combustion engine to generate power; electric motors supported by the support, supplied with electric power from the generators, and configured to drive the rotors; and a circuitry that control a flight of an aircraft by individually adjusting a rotational speed of each of the rotors. The multicopter also comprises a plurality of the internal combustion engines or a plurality of the generators.

A multicopter comprises: a support; rotors supported by the support; an internal combustion engine supported by the support; a generator supported by the support and driven by the internal combustion engine to generate power; electric motors supported by the support, supplied with electric power from the generators, and configured to drive the rotors; and a circuitry that control a flight of an aircraft by individually adjusting a rotational speed of each of the rotors. The multicopter also comprises a plurality of the internal combustion engines or a plurality of the generators.

A method for integrating and fitting at least one item of equipment and/or at least one line in a technical bay of an aircraft, comprising the steps comprising attaching the equipment and/or the line(s) on an integration module outside the fuselage of the aircraft, introducing the integration module into the fuselage of the aircraft via an opening of a baggage hold, and securing the integration module to a structure of the aircraft. An integration module is provided which comprises a chassis bounding a volume in which are positioned and attached at least one item of equipment and/or at least one line and having a cross section that is approximately identical to that of a baggage container and a length which is less than or equal to that of a baggage container.

A latch assembly may comprise: a housing; a pawl assembly coupled to the housing, the pawl assembly configured to transition from an un-restrained state to an restrained state; and a latch state detection system comprising a transducer and a communications module, the transducer configured to convert mechanical energy from the pawl assembly reaching the restrained state to an electrical energy configured to power the communications module.

A cargo restraint includes a housing. The cargo restraint further includes an inner pawl and an outer pawl coupled to the housing and configured to rotate between a retracted position and an erected position relative to the housing. The cargo restraint further includes a locking pawl rotatably coupled to at least one of the inner pawl or the outer pawl and configured to rotate between a locked position in which the inner pawl and the outer pawl are locked in the erected position and an unlocked position.

A restraint for use in restraining cargo includes a main body having an elongated shape with a contact end configured to contact and restrain the cargo and a second end opposite the contact end, the contact end defining a first face and a second face such that a first angle between the first face and the second face is at least one of less than or equal to 160 degrees. The restraint further includes a spring configured to allow the main body to rotate relative to a stationary object in response to contact with the cargo and to cause the main body to return to a neutral position in response to a lack of contact with the cargo.

A restraint for use in restraining cargo includes a main body having an elongated shape with a contact end configured to contact and restrain the cargo and a second end opposite the contact end, the contact end defining a first face and a second face such that a first angle between the first face and the second face is at least one of less than or equal to 160 degrees. The restraint further includes a spring configured to allow the main body to rotate relative to a stationary object in response to contact with the cargo and to cause the main body to return to a neutral position in response to a lack of contact with the cargo.

A quick-connect fitting for a convertible cargo handling assembly may comprise a fixed portion and a coupling component. The fixed portion may be secured to an aircraft frame structure. The coupling component may be coupled to a removable cargo handling component. The coupling component may be configured to rotate relative to the fixed portion.