A coaxial rotor system for a rotorcraft includes a mast, a top rotor assembly and a bottom rotor assembly. The top rotor assembly is coupled to the distal end of the mast. The bottom rotor assembly includes a motor configured to provide rotational energy to the mast, thereby rotating the top rotor assembly. The bottom rotor assembly experiences a torque reaction force responsive to the motor rotating the mast such that the top and bottom rotor assemblies counter rotate.

A coaxial rotor system for a rotorcraft includes a mast, a top rotor assembly and a bottom rotor assembly. The top rotor assembly is coupled to the distal end of the mast. The bottom rotor assembly includes a motor configured to provide rotational energy to the mast, thereby rotating the top rotor assembly. The bottom rotor assembly experiences a torque reaction force responsive to the motor rotating the mast such that the top and bottom rotor assemblies counter rotate.

An aeronautical composite structure configured to monitor a physical status of a bonded portion between structural components using a multi-core optical fiber. A method and system for monitoring the physical status of a bonded portion in an aeronautical composite structure also uses a multi-core optical fiber. More particularly, the invention relates to a structure and method for monitoring the physical status of a bonded portion of an aeronautical composite structure from its manufacturing to its use in flight using a multi-core optical fiber.

An aeronautical composite structure configured to monitor a physical status of a bonded portion between structural components using a multi-core optical fiber. A method and system for monitoring the physical status of a bonded portion in an aeronautical composite structure also uses a multi-core optical fiber. More particularly, the invention relates to a structure and method for monitoring the physical status of a bonded portion of an aeronautical composite structure from its manufacturing to its use in flight using a multi-core optical fiber.

An aircraft has a vertical stabilizer with a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has front longitudinal lugs, rear longitudinal lugs, and opposing middle longitudinal lugs. Front clevises corresponding to the front longitudinal lugs are secured to frame members of the fuselage of the aircraft and each has a first, second, and third mounting arms. Rear clevises corresponding to the rear longitudinal lugs are secured to frame members and each has a first, second, and third mounting arms. Middle clevises corresponding to the middle longitudinal lugs are secured to frame members and each has only first and second mounting arms. Retaining members inserted through mounting holes in each longitudinal lug and mounting holes in each corresponding clevis secures the vertical stabilizer to the fuselage.

An aircraft has a vertical stabilizer with a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has front longitudinal lugs, rear longitudinal lugs, and opposing middle longitudinal lugs. Front clevises corresponding to the front longitudinal lugs are secured to frame members of the fuselage of the aircraft and each has a first, second, and third mounting arms. Rear clevises corresponding to the rear longitudinal lugs are secured to frame members and each has a first, second, and third mounting arms. Middle clevises corresponding to the middle longitudinal lugs are secured to frame members and each has only first and second mounting arms. Retaining members inserted through mounting holes in each longitudinal lug and mounting holes in each corresponding clevis secures the vertical stabilizer to the fuselage.

A leading edge structure for an aircraft flow control system includes a leading edge panel curvingly surrounding a plenum. The leading edge panel has a first side portion and a second side portion with an inner surface facing the plenum and an outer surface contacting an ambient flow. The leading edge panel includes a plurality of micro pores forming a fluid connection between the plenum and the ambient flow. An air outlet is arranged in the first or second side portion and is fluidly connected to the plenum for letting out air from the plenum into the ambient flow. The air outlet is formed as a fixed air outlet including an outlet panel extending in a fixed manner from the leading edge panel into the ambient flow, such that a rearward facing outlet opening is formed between the leading edge panel and a rear edge of the outlet panel.

A leading edge structure for an aircraft flow control system includes a leading edge panel curvingly surrounding a plenum. The leading edge panel has a first side portion and a second side portion with an inner surface facing the plenum and an outer surface contacting an ambient flow. The leading edge panel includes a plurality of micro pores forming a fluid connection between the plenum and the ambient flow. An air outlet is arranged in the first or second side portion and is fluidly connected to the plenum for letting out air from the plenum into the ambient flow. The air outlet is formed as a fixed air outlet including an outlet panel extending in a fixed manner from the leading edge panel into the ambient flow, such that a rearward facing outlet opening is formed between the leading edge panel and a rear edge of the outlet panel.

An aircraft has a vertical stabilizer having a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has a pair of middle longitudinal lugs between a front and rear of the base rib assembly, a pair of front lateral lugs along the front of the base rib assembly, and a pair of rear lateral lugs along the rear of the base rib assembly. There are no lateral lugs between the pairs of middle lugs. A pair of middle clevises extend through corresponding apertures in an outer skin of the fuselage and are secured to one of the plurality of frame members and a plurality of retaining members are inserted through mounting holes in each middle longitudinal lug and mounting holes in each middle clevis to secure the vertical stabilizer to the aircraft fuselage.

An aircraft has a vertical stabilizer having a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has a pair of middle longitudinal lugs between a front and rear of the base rib assembly, a pair of front lateral lugs along the front of the base rib assembly, and a pair of rear lateral lugs along the rear of the base rib assembly. There are no lateral lugs between the pairs of middle lugs. A pair of middle clevises extend through corresponding apertures in an outer skin of the fuselage and are secured to one of the plurality of frame members and a plurality of retaining members are inserted through mounting holes in each middle longitudinal lug and mounting holes in each middle clevis to secure the vertical stabilizer to the aircraft fuselage.