Described herein are methods of forming uncured sealant assemblies and also methods of forming seals between various parts using such assemblies. In some examples, an uncured sealant assembly comprises two protective layers and an uncured sealant layer, disposed in between. The uncured sealant assembly is stored and provided at a cure-inhibiting temperature, selected to minimize the curing rate of the uncured sealant layer. The size and the shape of the uncured sealant layer are specifically selected to ensure the complete coverage of the faying surfaces, filling of all gaps and voids between the faying surfaces, and controlling the shape and size of uncured sealant squeeze out between the faying surfaces. In some examples, the size and shape of the uncured sealant layer maybe be specifically selected to have no uncured sealant squeeze out between parts.

Described herein are methods of forming uncured sealant assemblies and also methods of forming seals between various parts using such assemblies. In some examples, an uncured sealant assembly comprises two protective layers and an uncured sealant layer, disposed in between. The uncured sealant assembly is stored and provided at a cure-inhibiting temperature, selected to minimize the curing rate of the uncured sealant layer. The size and the shape of the uncured sealant layer are specifically selected to ensure the complete coverage of the faying surfaces, filling of all gaps and voids between the faying surfaces, and controlling the shape and size of uncured sealant squeeze out between the faying surfaces. In some examples, the size and shape of the uncured sealant layer maybe be specifically selected to have no uncured sealant squeeze out between parts.

Provided are stiffened stringer panels with integrated plank structures. An example composite panel comprises a skin member having an inner surface, and a plank on the inner surface. The plank comprises a set of layered laminate plies and extends from a first side to a second side. Each laminate ply of the set of layered laminate plies is sized to form a desired geometric profile for each of the first side and the second side. The composite panel further comprises a stringer including a cap portion that spans from the first side of the plank to the second side of the plank to form a first flange portion and a second flange portion, respectively, on the inner surface of the skin member. Base segments of the cap portion conform to the desired geometric profile of respective first and second sides of the plank.

Provided are stiffened stringer panels with integrated plank structures. An example composite panel comprises a skin member having an inner surface, and a plank on the inner surface. The plank comprises a set of layered laminate plies and extends from a first side to a second side. Each laminate ply of the set of layered laminate plies is sized to form a desired geometric profile for each of the first side and the second side. The composite panel further comprises a stringer including a cap portion that spans from the first side of the plank to the second side of the plank to form a first flange portion and a second flange portion, respectively, on the inner surface of the skin member. Base segments of the cap portion conform to the desired geometric profile of respective first and second sides of the plank.

To improve the seal between a wing and a ventral fairing of an aircraft, an assembly includes an air seal system arranged in an opening, between the ventral fairing and the wing. The seal system includes a sealing blade, a first end of which presses against the wing, and a connecting device, on the ventral fairing, for a second blade end that is opposite the first end. The connecting device includes at least one first connecting layer, of which a first connecting face is secured to a first surface of the sealing blade, and of which a second face, opposite the first face, is secured to the ventral fairing, the first connecting layer being made of a material including an elastomer.

To improve the seal between a wing and a ventral fairing of an aircraft, an assembly includes an air seal system arranged in an opening, between the ventral fairing and the wing. The seal system includes a sealing blade, a first end of which presses against the wing, and a connecting device, on the ventral fairing, for a second blade end that is opposite the first end. The connecting device includes at least one first connecting layer, of which a first connecting face is secured to a first surface of the sealing blade, and of which a second face, opposite the first face, is secured to the ventral fairing, the first connecting layer being made of a material including an elastomer.

An aircraft may have one or more electrically powered thrust-generating engines and a combustion engine forming part of a power generator system for powering the electric engine and/or recharging a battery system that powers the electric engine. An exhaust pipe leads via an interior space within the aircraft from the exhaust of the combustion engine, or other source of hot gases, to an exhaust outlet. The direction of the exhaust pipe at the outlet is transverse to the longitudinal axis of the aircraft. A fairing immediately upstream of the outlet has a trailing edge, for example with a sawtooth profile, which creates turbulence and/or chaotic airflow over and downstream of the outlet, and thus mixes the freestream air and the hot gases from inside the aircraft more efficiently.

A flight control surface comprising a main body comprising an upper and lower cover, upper and lower skins and a core member, a prolongation of their length over the length of the core member defining a stepped area. A trailing edge of the control surface comprises a U-shaped profile enclosing the prolongation, the U-shaped profile extending towards the main body in the chordwise direction up to the stepped area and comprising a section that progressively decreases. The trailing edge comprises a first and a second set of rivets located in the prolongation, the first set of rivets joining the upper and lower covers and the second set of rivets joining the U-shaped profile, the upper covers and the lower covers.

A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.