Abstract: A cabin crew area (10) of an aircraft (14) includes an aft area (16) with multiple galley carts (30). The aft area (16) has a fore/aft depth that is approximately equal to the depth of two or more of the galley carts (30). A galley storage unit (32) resides in the aft area (16) and stores the galley carts (30). The galley storage unit (32) is configured for placement of a portion of the galley carts (30) in a lateral row in a forward section (42) of the aft area (16). A main counter (34) resides over the galley storage unit (32) and extends laterally across a galley-servicing area (12) of the aircraft (14).

Abstract: A simplified structure for a wing skin and wing box wherein the internal surface (2) of an aircraft wing skin panel (1) in the wing box includes a multiplicity of strips (3), each strip being associated with a stringer. The strips (3) have different gradients in the span-wise direction S, which is the direction in which the strips extend. The surface of each strip is, in the chord-wise direction C, parallel to the external surface (5). At a junction, at which a rib meets a stringer, the interior surface (2) has an area (4a) that is parallel to the exterior surface (5), such that the rib and stringer at that junction may be simply attached to the wing skin panel (1).

Abstract: A small, substantially spherical, free-flying utility platform for use in space can be docked, inspected and serviced in an apparatus including a container with a chamber therein mounted on the outside of a space vehicle or space station. A motorized closing mechanism drives a door to selectively open or close an opening of the container into the chamber, and another mechanism automatically latches and locks the door. The door operations can be automatically triggered as the platform breaks the beams of light beam devices arranged in the container. The proper positioning of the platform in the container can be detected by a photoelectric switch. Capture and docking of the platform is facilitated by sloping funnel-shaped interior walls of the container, and properly shaped cushions and/or a docking cradle. When docked, the platform has its batteries recharged, its fuel tank refueled, and its electronics evaluated and diagnosed.

Abstract: Methods and systems for controlling fuel tank flammability control systems are disclosed herein. In one embodiment, a system for use with an aircraft or other vehicle includes a flammability control system and a controller operably coupled to the flammability control system. The flammability control system can be configured to control the development of flammable vapors in a fuel tank of the vehicle. The controller can be configured to receive one or more signals relating to a condition of the fuel tank and control operation of the flammability control system at least partially in response to the one or more fuel tank condition signals. In another embodiment, the controller can be configured to receive one or more signals relating to an operational phase of the aircraft and control operation of the flammability control system at least partially in response to the one or more aircraft operation signals.

Abstract: A float retractable landing gear. The float retractable landing gear incorporates a wheel support, a side gear door, a bottom gear door, and one or more hinges and strut ears attached to a spine. At least one hinge is rotatably attached to a float. The float incorporates a float side cutout communicating with a float bottom cutout. A spring-loaded strut incorporating on over center toggle down lock feature is attached between the float retractable landing gear and the float. A float side wall skin is attached to an upper portion of the float side wall cutout. The side gear door is sized to cover the lower portion of the float side wall cutout, and the bottom gear door is sized to cover the float bottom cutout. The float retractable landing gear may be specified to default into the extended or retracted position depending on the strut spring constant selected.

Abstract: The present invention relates to a convertible aircraft provided with first and second tilt fans disposed on either side of the fuselage a little forward of the center of gravity of the convertible aircraft. In addition, the convertible aircraft includes, in remarkable manner, a non-tilting fan that is permanently in a vertical position and that is contained inside the fuselage.

Abstract: The invention relates to a mechanism to control the pitch and/or roll and/or center of gravity of a vehicle. The first embodiment is a track-based mass transfer system in which pathways are positioned along or radially terminate at a central horizontal plane of the vehicle to move one or more mass transfer devices to a desired location to control the pitch and/or roll and/or center of gravity of the vehicle. A second embodiment is a fluid mass distribution system in which one or more conduits selectively distribute a fluid to one or more tanks positioned near a central horizontal plane of the vehicle to control the pitch and/or roll and/or center of gravity of the vehicle.

Abstract: A method of calibrating a gyro (42) of a spacecraft (14) may include determining a yaw attitude residual of the spacecraft. Roll gyro bias residual is determined in response to the yaw attitude residual. The gyro (42) is calibrated in response to the roll gyro bias residual. A method of calibrating a gyro (42) of a spacecraft (14) may alternatively include disabling gyro calibration, gain scheduling, or resetting attitude and gyro bias covariance, for selective axes, for a yaw transient period. The gyro (42) is calibrated in a nominal fashion after completion of the yaw transient period.

Abstract: An air discharge valve for an aircraft has an inner valve flap (1) and an outer valve flap (3) which partially overlap each other to form a nozzle of the Laval type with a nozzle inlet (6) converging toward a nozzle neck (S) and with a nozzle outlet (7) diverging away from the nozzle neck (S). The inner valve flap (1) has a trailing edge (8A) hinged to the aircraft body and a first leading edge (8) facing in the flight direction and having a curved sectional configuration. The outer valve flap (3) has a second leading edge (9) hinged to the aircraft body and a trailing edge (9A). Both flaps (1, 3) have a wedge shape. An outwardly facing surface portion (11B) of the inner flap (1) forms an air flow guide for air flowing out of the nozzle outlet (7). An inwardly facing surface portion (15B) of the outer flap (3) forms an air flow guide into the nozzle inlet (6) formed by the curved sectional configuration of the first leading edge (8) and by the inwardly facing surface portion (15B).

Abstract: A parachute is formed using a non-woven composite material. The non-woven composite material is formed by fusing a plurality of mono-filament fibers between thin layers of plastic. The non-woven material may be used as reinforcing tapes or as parachute lines in connection with a parachute of typical construction.

Abstract: A method for detecting ambient conditions conducive to ice formation. The method includes the steps of measuring at least one parameter selected from a group of parameters consisting of a static pressure, a total pressure, a total temperature, a dew point temperature, and a liquid water content, and determining whether ambient conditions are conducive to ice formation based on the measured parameter.

Abstract: An arrangement of individual seats for passengers in an aircraft, comprising a plurality of seats (1) which can be converted into beds and disposed in rows (2), comprising two lateral groups (3a) of two contiguous rows, each group being disposed along a wall (4) of the aircraft fuselage, and two central groups (3b) each comprising two continuous rows. The central groups being up against one another laterally, and the central groups being separated from each of the lateral groups by a gangway. Each of the lateral and central groups comprising, between two consecutive groups in a first row, and a gap able to allow transverse passage (6) to a gangway (7) for the passengers in the second row when the corresponding seat in the first row is in the bed position.

Abstract: A fan turbine engine arrangement is provided in which a core engine is aligned such that an input of a nacelle is aligned with the upwash of a wing to which the arrangement is secured. The engine drives a fan such that bypass flows produced by the fan are guided by a duct to present a downward component for uplift. The core engine presents its output flow through a nozzle which is aligned with the fundamental axis Y—Y of the engine. In such circumstances, the bypass flows cross the core engine flow from the nozzle unless that engine is adjustable during operation in order to maintain alignment dependent upon lift requirements.

Abstract: A rapid deployment system has an inflatable landing tube with an inflatable exit slide coupled to an aircraft. Connectors couple the landing tube to the aircraft. Flexible retarders extend inward from the inner surface of the tube for retarding gravitational descent of cargo and/or personnel from the aircraft. The tube has tubular segments, with ribs and reinforcements, forming a continuous descent tube. A spine along the tube is retractable telescopically allowing for the tube to be retracted within the aircraft. The tube is connected to exterior edges of any exit port of the aircraft. A window coaming adapter is positioned around the exterior edges and a membrane extending between sides of the adapter expands with the landing tube as the landing tube is inflated. The membrane is of multiple layers with expansion cells between adjacent layers for allowing independent expansion of the layers. The entry port has a shield behind the membrane and connected to the aircraft for protecting the membrane.

Abstract: One advantageous embodiment of the present invention is an integrated transport system (14) for moving an object (20) in an aircraft (10) between a main cabin (16) and an overhead cabin (18) via a shaft (24) in connection therebetween. This integrated transport system (14) includes a single-unit gantry-lift device (42) with an object carrier (32) for receiving the object (20). This object carrier (32) has one or more restraint members (34, 38) for securing the object (20) in the object carrier (32) and preventing the object (20) from inadvertently tipping or falling out of the object carrier (32). In this embodiment, the single-unit gantry-lift device (42) further includes a lift device (46) for moving the object carrier (32) generally along a longitudinal axis (22) of the shaft (24) and a gantry device (44) for moving the object carrier (32) generally along a first axis (26) of the overhead cabin (18) and/or a second axis (28), which is disposed generally perpendicular to the first axis (26).

Abstract: An aircraft having a vertical take-off and landing (VTOL) propulsion system. The aircraft includes a fuselage, the VTOL propulsion system, at least one forward thruster, a power source used for both the VTOL propulsion system and forward thruster, fore and aft wings and a plurality of spars attached to and spanning the space between the two wings. The VTOL propulsion system includes a plurality of VTOL cells (including a motor, motor controller, and propeller) attached in a spaced relation along each spar. The VTOL cells are used exclusively for vertical flight or hovering and are powered down as the aircraft develops forward flight velocity and corresponding wing lift. During forward flight the VTOL propellers are articulated to allow the aircraft to take on a low drag configuration. The present invention is suitable for use in manned or un-manned aircraft of any scale.

Abstract: A mounting structure for mounting a turboprop under an aircraft wing includes a rigid structure provided with an aft underwing box, and at least one forward rigid section. Each forward rigid section has two transverse frames at a spacing from each other. At least one forward rigid section of the rigid structure also includes at least one forward upper box connecting a top part of the two transverse frames of the forward rigid section.

Abstract: An arrangement of individual seats for passengers in an aircraft, comprising a plurality of seats which can be converted into beds and disposed in rows, and comprising two lateral groups (3a; 13a) of two contiguous rows, each group being disposed along a wall (4) of the aircraft fuselage, and at least one central group (3b; 13b) of two contiguous rows, the said central group being separated from each of the lateral groups by a gangway. Each lateral group comprising, between two consecutive groups in a first row, and a pitch (P1) able to allow transverse passage for the passengers in the other row. The at least one central group comprising, between two adjacent seats in the same row, and a pitch (P2) less than the pitch provided in the lateral groups.

Abstract: A ventilating and particle-filtering airflow system, and related methodology, for managing the flow of air to the brush region of an on-board aircraft (vehicle) electrical generator. Conduit structure collects intaken air during aircraft (vehicle) engine operation, filters this air to capture and prevent the passage of particles, and directs filtered airflow to that brush region. Water drainage is provided for in a region near where filtering takes place. The filtered airflow is substantially the only airflow admitted to this region.

Abstract: Interoperable aerial refueling apparatus and methods are disclosed. In one embodiment, a receptacle configured to fluidly receive a terminal portion of a refueling boom is coupled to a refueling drogue. A retainer is coupled to an aircraft that removably retains the receptacle when the aircraft is refueling another aircraft configured to directly engage the boom. The receptacle releases the receptacle when the terminal portion of the boom engages the receptacle so that an aircraft that receives the refueling drogue may be refueled. In another embodiment, a method includes providing fuel to a first receiving aircraft that receives fuel by directly coupling to an end of a refueling boom. The method further includes, while the tanker aircraft is in flight, configuring the boom to supply fuel to a second receiving aircraft having a refueling probe operable to receive fuel from a drogue.