An airframe 1 or part thereof comprises a set of modular cells 10, including a first cell 10A comprising a set of profiles 100 including: a first structural profile 100A, having a first length L1 and enclosing a first volume V1 providing a first passageway P1; and a second profile 100B, having a second length L2 and enclosing a second volume V2, wherein the first passageway P1 is arranged to receive the second profile 100B therein.

A motor integrated type fluid machine suctions a fluid from a suction port and discharges the suctioned fluid from a discharge outlet. The machine includes: a shaft portion provided at a center of a rotation axis; a rotating portion rotating around the shaft portion; an outer peripheral portion provided on an outer periphery of the shaft portion; and an outer peripheral drive motor rotating the rotating portion. The rotating portion includes a hub rotatably supported by the shaft portion, blades provided on an outer peripheral side of the hub and provided side by side in a circumferential direction of the rotation axis, and a rotating outer peripheral portion having an annular shape along the circumferential direction. A ratio of a rigidity of the rotating outer peripheral portion against a centrifugal force to a rigidity of the rotating portion against the centrifugal force is 50% to 95%.

A composite laminate for an airframe lifting surface including: at least two sides and one ramp area defined by a decreasing staggered laminate extended along a ramp direction, wherein the composite laminate includes: first plies formed by tapes arranged parallel to the ramp direction, second plies formed by tapes arranged orthogonal to the ramp direction, third plies formed by tapes arranged in a first laying up direction, being the first laying up direction different from the ramp direction and the direction orthogonal to the ramp direction, and fourth plies formed by tapes arranged in a second laying up direction, being the second laying up direction different from the ramp direction, the direction orthogonal to the ramp direction and the first laying up direction; wherein in the ramp area, the tapes forming the third and/or fourth plies are extended from one laminate side to another laminate side.

One embodiment includes a structural panel for an aerospace vehicle, including a single sheet of material, the material having a first raised pattern on a first side, and a second raised pattern on a reverse side, wherein a repeating portion of the first raised pattern is substantially identical in size and shape to a repeating portion of the second raised pattern, and is rotated at an angle θ to the first raised pattern.

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.

An aircraft fuselage includes an element forming a skin and a load-carrying structure supporting the element forming the skin. The load-carrying structure includes a plurality of elements forming a spar disposed parallel to an axial direction defined by the fuselage and a plurality of elements forming a frame disposed spaced apart along the axial direction. Each element forming a frame being arranged substantially perpendicularly to the elements forming a spar, where the element forming the skin is fastened on an external perimeter of each element forming a frame by means of fastening elements configured to keep the element forming the skin away from the external perimeter and where the element forming the skin is made of a transparent material.

Apparatuses and systems for more efficient construction and operations of a vehicle. A structural/storage system that includes a plurality of storage elements. Each of the storage elements includes a housing having an outer surface, an inner surface, and at least one opened end. The structural/storage system further includes first attachment devices disposed at the outer surface and second attachment devices disposed at the outer surface. The second attachment devices of a first one of the plurality of storage elements are configured to be removably attachable to the first attachment devices of a second one of the plurality of storage elements.

A method of manufacturing a structural component for a vehicle, in particular an aircraft or spacecraft, includes additively manufacturing a reinforcing plate of a metal material having on a joining surface a plurality of joining arms projecting from the joining surface; and joining the reinforcing plate at the joining surface to a structural element to form the structural component by inserting the joining arms into the structural element such that the joining arms permanently hold the structural element together with the reinforcing plate.

A method for the assembly of frames in an aircraft shell, wherein the aircraft shell comprises a skin and a plurality of stringers co-cured with the skin, wherein the skin has a plurality of reference marks. Identifying the reference marks on the skin using a first robot with artificial vision, establishing a local reference for the positioning of each frame based on a reference mark, grabbing a frame using the first robot, establishing a relative position between the first robot and the frame based on the reference mark, positioning the frame on an inner side of the aircraft shell using the first robot, and with a second robot, drilling holes through the frame and skin, and attaching the frame to the skin with fasteners.

Embodiments are directed to an aircraft fuselage comprises two keel beams and two roof beams. Each keel beam is formed as a single component having no joints. Each keel beam comprises a first portion that is configured to define a floor of an aircraft and a second portion that is configured to define a tail section of an aircraft. The second portion is positioned at an angle relative to the first portion. Each roof beam is coupled to the second portion of a corresponding keel beam at a point remote from the first portion. Each roof beam and a corresponding keel beam are positioned along a single butt line relative to an aircraft fuselage centerline. Frame members are coupled to both keel beams and both roof beams.