Systems and methods for extending the interior cargo bay of fixed-wing cargo aircraft into a replaceable tailcone bay are disclosed. The system includes an aircraft and a removable tailcone configured couple to the aft end of the fuselage. The aircraft fuselage includes a cargo bay and an aft end opening into the cargo bay. The tailcone, when attached, encloses the aft end opening the cargo bay. The tailcone can include an interior volume configured to extend the fuselage cargo bay such that the interior volume defines an aft end of a cargo bay of the cargo aircraft. In some examples, the tailcone includes a plurality of segments, which can be configured to extend from the aft end of the aircraft to adjust a length of the cargo extension provided by the tailcone.

An aircraft comprising at least one bay for receiving different types of standardized modules. The bay is configured to receive at least two different types of energy modules as standardized modules, preferably two types of energy modules chosen from a conventional fuel tank, a battery, a fuel tank for a fuel cell, a tank for electrofuel, a tank for nano-electrofuel, a gas tank or a combined energy source.

An aircraft comprising at least one bay for receiving different types of standardized modules. The bay is configured to receive at least two different types of energy modules as standardized modules, preferably two types of energy modules chosen from a conventional fuel tank, a battery, a fuel tank for a fuel cell, a tank for electrofuel, a tank for nano-electrofuel, a gas tank or a combined energy source.

An embodiment is a system including an external passenger seating unit comprising at least one seat; and a translation mechanism for translating the external passenger seating unit between a first position in which the external passenger seating unit is stowed in a payload bay of an aircraft and a second position in which the external passenger seating unit is deployed external to the aircraft for accommodating at least one passenger.

A method for operating a cargo door of an aircraft. The method comprises, opening the cargo door inwardly in relation to a cargo door opening by pivoting the cargo door to an open position adjacent a ceiling of a cargo space. The cargo door is supported by a door frame during opening of the cargo door. The method further comprises, moving the cargo door in relation to the door frame to a position wherein the cargo door opening is substantially free from the cargo door. The cargo door is supported by a support frame, moveable in relation to the door frame, during this movement. The invention also concerns a device for operating a cargo door of an aircraft.

A method for operating a cargo door of an aircraft. The method comprises, opening the cargo door inwardly in relation to a cargo door opening by pivoting the cargo door to an open position adjacent a ceiling of a cargo space. The cargo door is supported by a door frame during opening of the cargo door. The method further comprises, moving the cargo door in relation to the door frame to a position wherein the cargo door opening is substantially free from the cargo door. The cargo door is supported by a support frame, moveable in relation to the door frame, during this movement. The invention also concerns a device for operating a cargo door of an aircraft.

An in-floor adapter for a cargo deck of a cargo handling system may comprise: a plate extending from a proximal end to a distal end; a pocket disposed in the plate, the pocket having a sidewall and a bottom wall; a fitting disposed in the pocket, the fitting configured to mount a leg of a seat; and a slot disposed through the plate, the slot configured to guide an attachment mechanism during installation of the in-floor adapter in the cargo deck.

An in-floor adapter for a cargo deck of a cargo handling system may comprise: a plate extending from a proximal end to a distal end; a pocket disposed in the plate, the pocket having a sidewall and a bottom wall; a fitting disposed in the pocket, the fitting configured to mount a leg of a seat; and a slot disposed through the plate, the slot configured to guide an attachment mechanism during installation of the in-floor adapter in the cargo deck.

An aircraft comprises a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system. The aircraft further comprises a fuselage having a cargo bay (502) including one or more (510A-G) of the plurality of hydrogen storage tanks, the longitudinal axes (511A-G) of the one or more hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis (501) of the fuselage and lying in one or more planes (595, 597) extending across the width dimension of the cargo bay. The hydrogen storage tanks within the cargo bay have a common aspect ratio R in the range 4.2≤R≤25.7, allowing the volume of space with the cargo bay occupied by stored hydrogen to be maximised or approximately maximised.

An aircraft comprises a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system. The aircraft further comprises a fuselage having a cargo bay (502) including one or more (510A-G) of the plurality of hydrogen storage tanks, the longitudinal axes (511A-G) of the one or more hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis (501) of the fuselage and lying in one or more planes (595, 597) extending across the width dimension of the cargo bay. The hydrogen storage tanks within the cargo bay have a common aspect ratio R in the range 4.2≤R≤25.7, allowing the volume of space with the cargo bay occupied by stored hydrogen to be maximised or approximately maximised.