Abstract: A projectile including at least one pair of airfoil sections, deployable from housings located inside the body and emerging toward the outside of the projectile. The projectile includes a casing surrounding the body of the projectile and outer surface of which is in profile continuity with the body. The casing can pivot around body along longitudinal axis and includes, for each section, an opening having two zones. A first zone is indented to be positioned, by pivoting of the casing, so as to face a housing in order to allow the section to pass to allow it to be deployed, and second zone located as a recess lateral to the first zone, the recess being oriented along a direction substantially perpendicular to the first zone's longitudinal direction, the second zone having a width allowing the passage of a foot of the deployed section.

Abstract: A rear engine attachment having a beam fixed to a pylon, a spreader pivotally mounted on the beam, the spreader comprising two ends situated on either side of a median plane, two rods located one on either side of the median plane, each rod having a first end fixed to one end of the spreader by a ball joint and a second end fixed to the engine, each ball joint comprising a clevis with two arms at the first end of the rod, a swivel bearing arranged on the end of the spreader, and a hinge pin passing through the two arms, the swivel bearing arranged between the two arms and fitted on the hinge pin. For each ball joint, an interface part is removably interposed between the end of the spreader and the first end of the rod and forms a contact surface between the spreader and the rod.

Abstract: A leading edge (3) of a control surface (1) for an aircraft includes a balance weight (6) attached to the forward-most region of the leading edge (3). The control surface (1) rotates with respect to the stabilizer (2) around a hinge line (5). The balance weight (6) is ahead of and adjacent to the most frontal portion (7) of the leading edge (3) of the control surface (1) are is inside the trailing edge of the stabilizer (2). This arrangement allows to have an anti-flutter balance weight without any impact in aerodynamic drag.

Abstract: A system for passive deployment of a vortex generator is disclosed, including a housing mounted at a fixed location relative to an airfoil structure and a piston contained in the housing. A vortex generator is moveably mounted adjacent an exterior surface of the airfoil structure, and is moveable between a stowed position inside the airfoil structure and a deployed position outside the airfoil structure. The piston is configured to drive the vortex generator between the stowed position and the deployed position in response to a pressure differential between a first airstream over a first surface of the airfoil structure and a second airstream over a second surface of the airfoil structure.

Abstract: A lift rotor arrangement (100) for a VTOL aircraft (200). The lift rotor arrangement (100) comprises: a fairing (6) mounted on a wing segment (10); and first and second rotor blades (17, 18) mounted on a first shaft (4) extending vertically from the fairing (6). The first shaft (4) is movable between an extended position in which the first and second rotor blades (17, 18) are vertically spaced above the wing segment (10) and are rotatable to provide vertical lift, and a retracted position in which the first and second rotor blades (17, 18) are rotationally-fixed with the first rotor blade (17) stowed within the wing segment (10). The blades (17, 18) may be rotatable around an axis substantially perpendicular to the axis of the respective first shaft (4) so as to act as ailerons/elevons in the retracted position.

Abstract: A sub-structure for an aircraft cabin monument is disclosed. The sub-structure includes a plurality of mounting attachment points for supporting a mount to engage with a corresponding mounting attachment point on a lattice structure of a load carrying partition wall. The aircraft cabin monument is supported by the load carrying partition wall through the sub-structure, supporting a substantial weight of the monument, and relieving the cabin floor from supporting the load and weight of the aircraft cabin monument.

Abstract: A windshield for an aircraft cockpit is provided which includes a glazed windshield part which has a single curvature corresponding to a portion of the envelope of a cone extending between a lower plane and an upper plane which intersect an axis of the cone. The single curvature of the glazed part of the windshield enables the glazed part to be produced more easily, for example by rolling or by hydroforming. It also makes it possible to create configurations for a cockpit for two pilots, a single pilot or even no pilot, on the basis of a single aerodynamic shape of the fuselage of the aircraft by only adapting the structure of the windshield. Also provided are a windshield frame for such a windshield, a windshield assembly including such a windshield frame and such a windshield, and an aircraft equipped with such a windshield.

Abstract: A tip gap control system for a ducted aircraft includes a flight control computer including an inner duct surface control module configured to generate an inner duct surface actuator command and a proprotor system in data communication with the flight control computer. The proprotor system includes a duct having active inner duct surfaces movable into various positions including a retracted position and an extended position. The proprotor system also includes proprotor blades surrounded by the duct and one or more actuators coupled to the active inner duct surfaces. The one or more actuators move the active inner duct surfaces between the various positions based on the inner duct surface actuator command, thereby controlling a tip gap between the proprotor blades and the duct.

Abstract: A rear engine attachment having first and second parts, wherein the first part has two first clevises fixed to a lower face of a pylon, two second clevises fixed to a structural casing, two connecting rods mounted to be articulated between first and second clevises, and two shafts realizing the connections between the connecting rods and the clevises. The second part has a shoe fixed to the lower face and having a bore, a main rod which bears a vertical peg engaging in the bore and which is fixed to the structural casing by a first pivot connection, and a secondary rod fixed to the main rod by a second pivot connection and to the structural casing by a third pivot connection. Such a rear engine attachment is more compact, taking up space in the longitudinal direction and thus minimizing the space taken up in the transverse direction.

Abstract: A cover for a rawinsonde balloon includes a cover main body with an inner surface forming inner space and an outer surface. The rawinsonde balloon is inserted into the inner space of the cover main body. Further, the cover includes an inlet, positioned at a preliminary free end of the cover main body, for allowing the rawinsonde balloon to be inserted into the inner space and the cover additionally includes an inlet control member for controlling a size of the inlet and fixing a controlled size of the inlet. Furthermore, the cover includes a plurality of basic cover fixing members formed or located respectively at a plurality of basic preliminary fixed ends on the outer surface.

Abstract: An aircraft cargo floor architecture comprises a plurality of aircraft keel frames. One or more longitudinal rails are attached directly to the aircraft keel frames. The one or more longitudinal rails are designed to provide structural support for an aircraft cargo floor.

Abstract: Fuselage sections having tapered wing rib interfaces are disclosed. A disclosed example apparatus includes a rib associated with a fuselage section, and a wing interface surface defined by the rib, where the wing interface surface is tapered relative to a longitudinal axis of the fuselage section from an aft end of the fuselage section to a fore end of the fuselage section.

Abstract: The invention relates to a device and to a method for the open and closed control of n actuators An, n=1, 2, . . . , N, where N?1, which drive aerodynamic control surfaces of an aircraft.

Abstract: Embodiments of the present invention are related to a Y-shaped airliner including an elongate main fuselage bifurcated into two outwardly angled fuselage extensions defined as a first fuselage extension and a second fuselage extension. The airliner includes a NACA inlet, a medial fan, a pair of forward canard wings, and a pair of side wings each including at least one engine. The medial fan is positioned between the first fuselage extension and the second fuselage extension. The NACA inlet is positioned on the main fuselage rear skin and is structured to feed airflow into the medial fan.

Abstract: Vortex reduction apparatus for use with airfoils are disclosed. An example vortex reduction apparatus includes a housing to couple to a tip of an airfoil. The housing defines a volute fluid flow passageway between an inlet and an outlet. The volute fluid flow passageway is structured to induce a rotational fluid flow in a first rotational direction opposite a second rotational direction of a shed vortex induced at the tip of the airfoil during flight.

Abstract: A seat configured to support an occupant may include a urine-based power generator and an adjustable cushion. The urine-based power generator includes a urine accumulation reservoir configured to receive urine from the occupant, and the urine-based power generator is configured to provide power to the adjustable cushion. The seat may be an ejection seat, and the urine-based power generator and the adjustable cushion may be mounted to the seat such that the urine-based power generator and the adjustable cushion are configured to be ejected with the ejection seat.

Abstract: A nacelle assembly includes a fixed inlet segment and a translating inlet segment. The translating inlet segment includes a slider beam laterally between a pair of tracks of the fixed inlet segment. The slider beam is mated with and slidable longitudinally along the pair of tracks. The translating inlet segment is configured to translate longitudinally between a retracted position and an extended position. An aft end of the translating inlet segment is abutted against a forward end of the fixed inlet segment when the translating inlet segment is in the retracted position. An airflow inlet into an inlet passage of the nacelle assembly is opened longitudinally between the aft end of the translating inlet segment and the forward end of the fixed inlet segment when the translating inlet segment is in the extended position.

Abstract: A ducted-rotor aircraft may include a fuselage and first and second ducts that are coupled to the fuselage at respective first and second locations. The first location may be on a first side of a fuselage of the aircraft and spaced from a nominal yaw axis of the aircraft. The second location may be on an opposed second side of the fuselage and spaced from the nominal yaw axis. Each duct may include a rotor that is disposed in an opening that extends through the duct. Each rotor may include a plurality of blades. Each duct may further include a control vane that is mounted aft of the plurality of blades and that is pivotable about a vane axis that is oriented toward the nominal yaw axis.

Abstract: The present invention includes a thrust control apparatus, method and kit for a tiltrotor craft comprising a thrust control handle; a first and a second bar connected to the thrust control handle and connected to a floor support; a first end of a transverse bar connected to the first bar; a linker connected to a second end of the transverse bar; and a crankbell connected to the floor support below the first and a second bars, wherein a first end of the crankbell is connected to the linker, wherein the thrust control handle has a substantially linear motion that controls engine thrust, and the crankbell transfers the substantially linear motion of the handle into a substantially perpendicular motion that engages an engine thrust control at a second end of the crankbell.

Abstract: A variable-geometry vertical takeoff and landing (VTOL) aircraft system may transport passengers from a departure point to a destination via partially or fully autonomous flight operations. The VTOL aircraft system may operate in hover-based ascent/descent modes, level-flight cruising modes, and transitional modes between the two. Thrust may be provided by ducted propeller units articulable relative to the fuselage; by articulating the airfoil struts connecting the thrust sources to the fuselage the thrust sources may be manipulated for ascent/descent, transition, and cruising. in order to control ascent, descent, and cruise. More precise thrust control may be achieved by further articulation of the annular propeller ducts relative to the airfoil struts. The airfoil struts and propeller ducts may present a wing-shaped or variably segmented cross section to maximize achievable lift.