An aircraft includes a fuselage, a wing disposed above the fuselage, a pylon connecting the wing to the fuselage, and a plurality of internal combustion engines housed in the fuselage. The pylon vertically traverses the fuselage and is fixed to an upper portion and a lower portion of the fuselage. Among the plurality of internal combustion engines, a first internal combustion engine and a second internal combustion engine are disposed bilaterally symmetrically about the pylon and are fixed to the pylon.

A pressure deck system for a fuselage of an aircraft. The pressure deck system comprises a first sloping outboard pressure panel, a first longitudinal stiffener connected to the first sloping outboard pressure panel, a second sloping outboard pressure panel opposite the first sloping outboard pressure panel, a second longitudinal stiffener connected to the second sloping outboard pressure panel, pressure panels between the first sloping outboard pressure panel and the second sloping outboard pressure panel and forming the an upper barrier of a wheel well, longitudinal beams connected to the pressure panels and supporting a cabin floor of the fuselage, and a sloping pressure deck connecting a number of these components to the rear spar of the center wing box. A waterline of the pressure deck system is de-coupled from a side-of-body waterline in the fuselage.

A self-righting aeronautical vehicle comprising a hollowed frame and a lift mechanism. The exterior of the frame and center of gravity are adapted to self-right the vehicle. The frame can include sealed, hollowed sections for use in bodies of water. The frame can be spherical in shape enabling inspection of internal surface of partially or fully enclosed structures. Inspection equipment can be integrated into the vehicle and acquired data can be stored or wirelessly communicated to a server. A controlled or other mass can be pivotally assembled to a pivot axle spanning across the interior of the frame. The pivot axis can rotate about a vertical axis (an axis perpendicular to the elongated axis). The propulsion mechanisms can be adapted for use as a terrestrial vehicle when enclosed in a sealed spherical shell.

The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas. A manufacturing processes of said integrated aircraft structure is also provided.

This structure is provided with a first composite material 11, a second composite material 12 joined to the first composite material 11 by a film adhesive 21 provided between the first composite material 11 and the second composite material 12, and a corner fillet part 13 provided on a corner part 15 formed by the first composite material 11 and the second composite material 12. The shape of the corner fillet part 13 is a design shape P designed in advance, and the corner fillet part 13 is formed by curing the film adhesive 21 after arranging the film adhesive 21 on the corner part 15 so as to fit into the design shape P.

An aircraft includes a fuselage having a front, a center, and a rear section. A first mounting member is coupled to the front section. A second mounting member is coupled to the rear section. A first and a second wing are coupled to the center section. A plurality of power generator systems are included and coupled to the first or second mounting member. Each power generator system includes a power source, a first and a second propeller. The power source is configured to drive the first and second propeller. The first and second propeller have an axis of rotation, and are pivotable between a first and a second position. An amphibious landing gear system is coupled to an underside of the fuselage and has a flap and a bladder. The bladder is located under the flap, configured to inflate and deflate, and sized to provide buoyancy for the aircraft.

A harness routing electrically connects a rear fuselage section of an aircraft and a trimmable Horizontal Tail Plane (HTP) installed at this rear section. The aircraft rear section includes a first clipping point wherein the harness is attached to a fuselage frame located in front of the torsion box front spar, and a second clipping point wherein the harness is attached to a front spar of the HTP torsion box. The second clipping point is located downstream the first clipping point from the fuselage towards the torsion box interior, and the harness passes through the front spar towards the interior of the torsion box downstream the second clipping point. The harness installation and routing is optimized, in order to reduce harness length and weight, but at the same time assuring that any damage to the harness cables are prevented during the entire aircraft operative life.

An airframe component includes a skin panel, a plurality of stringers attached to the skin panel, and at least one former running substantially perpendicular to the plurality of stringers on the skin panel, the at least one former being generatively formed on the skin panel by an Additive Manufacturing (AM) method.

Example implementations provide fluid-borne vehicles comprising a body and a plurality of thrust vectoring modules, each thrust vectoring module comprising a set of thrust producing means, wherein a first thrust producing means, mounted on a first mounting bar having a first mounting bar axis, is rotatable about the mounting bar axis and the mounting bar axis is rotatable about an arm having an arm axis that is nonparallel to the mounting bar axis; and a second thrust producing means, mounted on a second mounting bar having a second mounting bar axis, is rotatable about the second mounting bar axis and the second mounting bar axis is rotatable about the arm axis that is nonparallel to the second mounting bar axis.

Disclosed herein is a system for lifting an object. The system comprises a first floor, a second floor, and an object rack supported on the second floor. The system further comprises an object advance apparatus coupled with the object rack. The object advance apparatus is configured to advance one object from the plurality of objects from an advancing position to a lifting position. The system additionally comprises a lifting cylinder that is configured to extend from a retracted position below the lifting position to an extended position above the first floor, such that the one object in the lifting position is removed from the object rack and lifted adjacent to the assembling body. The system also comprises a floor flap configured to open and close in synchronization with the extension and retraction of the lifting cylinder.