Additive manufactured airframe structure having a plurality of additive manufactured airframe segments operable to be linked together in an assembled direction. Each of the plurality of additive manufactured airframe segments are separate from one another in an unassembled configuration. Plurality of reinforcement elements operable to be received in a receiving portion of the plurality of airframe segments and extending through the plurality of airframe segments in a normal direction. Receiving portion is located on the interior of a respective one of the plurality of airframe segments.

A method for integrating a backing-structure assembly in a structure of an aircraft or spacecraft is described. In this case, a plurality of individual elements is joined to form the backing-structure assembly. The individual elements for the backing-structure assembly and a skin portion for the structure are provided. The elements are arranged on a pre-assembly device which comprises retaining devices, which are each configured to hold one of the elements so as to be adjustable with respect to the position and/or location thereof. Some or all of the elements are connected to the skin portion. In the method, by adjusting the retaining devices for tolerance compensation, gaps between joint regions of the elements and the skin portion are eliminated or adjusted.

A method for joining skin portions of a closed fuselage, in particular for an aircraft or spacecraft, has the following method steps: providing at least a first skin portion and a second skin portion, at least one of the skin portions being fitted with components to remain in the fuselage; positioning at least the first skin portion and the second skin portion relative to one another in a first joint such that the skin portions form a circumferentially closed fuselage arrangement; guiding a first joining head along the first joint on an outer surface of the fuselage arrangement; and guiding a second joining head along the first joint on an inner surface of the fuselage arrangement, the second joining head being guided along longitudinal guide means which are arranged inside the circumferentially closed fuselage arrangement and are formed at least in part by the components to remain in the fuselage.

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, includes a closed wing that provides lift whenever the aircraft is in forward flight, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. One or more motors are disposed within or attached to the spokes. Three or more propellers are proximate to a leading edge of the one or more spokes, distributed along the one or more spokes, and operably connected to the one or more motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight.

A method and apparatus for facilitating the attachment of an internal module in an internal space of an aircraft part is disclosed. The attachment device includes at least one attachment member comprising an attachment shank, a chamber for introducing the attachment member, the chamber including a first orifice through which the attachment shank passes in the installed configuration of the internal module, and a second orifice which serves for the introduction of the attachment member into the chamber from the outside.

A VTOL aircraft system includes a first unit having a cockpit, at least one propeller, at least two landing legs and at least two locking mechanisms. A second unit has a housing with a base portion, a first unit engaging portion, and at least two lock mechanism-engaging structure, each corresponding to one of the at least two locking mechanisms of the first unit. The housing of the second unit defines at least one interior cavity with at least one cargo area, a central passage providing access between the first and second unit, and a fuel cell configured around the central passage.

A removable battery to provide motive power for an aircraft includes a battery frame and removable, interchangeable battery modules. Each of the battery modules defines module common space through which liquid heat transfer fluid flows during charging of the battery when the battery is removed from the aircraft and through which air as a heat transfer fluid flows during discharge of the battery, as during flight. The module common space also defines a combustion conduit to convey heated air and products of combustion safely outside the battery in the event of a cell fire during flight. The removable battery frame is a structural component of the aircraft.

A pressure bulkhead system comprises a pressure bulkhead adapted to be connected to a fuselage of a vehicle to separate a pressurized cabin space of the vehicle from an unpressurized cabin space of the vehicle, and a peripheral pressure frame to sealingly connect the pressure bulkhead to the vehicle fuselage. The peripheral pressure frame comprises an attachment section sealingly attached to an outer rim portion of a first surface of the pressure bulkhead. The first surface, when the pressure bulkhead system is installed in the vehicle, faces the unpressurized cabin space of the vehicle. A flange section is adapted to be sealingly attached to an inner surface of the vehicle fuselage and extends in a direction facing away from the first surface of the pressure bulkhead. A flexible section interconnects the attachment section and the flange section and is flexible to accommodate cabin pressure acting on the pressure bulkhead.

The aircraft can include: an airframe, a tilt mechanism, a payload housing, and can optionally include an impact attenuator, a set of ground support members (e.g., struts), a set of power sources, and a set of control elements. The airframe can include: a set of rotors and a set of support members. By utilizing a larger rotor blade area (and/or larger rotor disc area) and adjusting the blade pitch and RPM, the rotors can augment the lift generated by the aerodynamic profile of the aircraft in the forward flight mode in addition to providing forward thrust. Variants generating lift with the rotors can reduce or eliminate additional control surfaces (e.g., wing flaps, ailerons, ruddervators, elevators, rudder, etc.) on the aircraft since the thrust and motor torque is controllable (thereby indirectly controlling lift) at each rotor, thereby enabling pitch, yaw, and/or roll control during forward flight.

An assembly including a support tower and at least two support systems, each bearing a panel of a section of an aircraft fuselage and including four fixing points. The support tower includes a tower extending along an axis X, a seat on which the tower is mounted and which is rotationally mobile about the axis X, and, for each fixing point, a fixing base mounted on a three-dimensional adjustment system mounted on the tower and motorized to displace the fixing base in two horizontal directions and one vertical direction, where each fixing point and the associated fixing base can be locked with one another to ensure the fixing of one with the other, and that can be unlocked to allow them to be separated. Such an assembly makes it possible to keep the various elements of the section vertical during assembly and allows for a space saving on the ground and a saving on transfer utilities.