Abstract: A fluid recycling unit for use on board an aircraft or other passenger transportation vehicle. The fluid recycling unit captures various types of used fluids, filters or otherwise appropriately treats the fluids, and recycles the fluids for various uses onboard the vehicle.

Abstract: The present application generally relates to aircraft water management. The disclosed system provides an initial step of verifying the amount of available water on board and dynamically regulating water usage during flight based on projections and comparisons between projections and actual usage. The system implements a series of water conservation strategies modeled on historical data, using a control system to manage water usage.

Abstract: The present application generally relates to aircraft water management. The disclosed system provides an initial step of verifying the amount of available water on board and dynamically regulating water usage during flight based on projections and comparisons between projections and actual usage. The system implements a series of water conservation strategies modeled on historical data, using a control system to manage water usage.

Abstract: Embodiments of the disclosure provide systems and methods for improved removability and ease of maintenance for one or more components of the vacuum toilet system. They can be particularly useful on-board aircraft and other passenger transport vehicles. Specific embodiments relate to a rinse valve bracket and connection system, a rinse ring tie down, and various improved connection systems.

Abstract: Embodiments relate generally to flush plates having noncircular openings. In a specific example, the flush plate has a shark-fin shaped opening with an extending fin along a tail portion.

Abstract: Embodiments of the disclosure provide systems and methods for improved removability and ease of maintenance for one or more components of the vacuum toilet system. They can be particularly useful on-board aircraft and other passenger transport vehicles. Specific embodiments relate to a rinse valve bracket and connection system, a rinse ring tie down, and various improved connection systems.

Abstract: Embodiments of the disclosure provide systems and methods for improved removability and ease of maintenance for one or more components of the vacuum toilet system. They can be particularly useful on-board aircraft and other passenger transport vehicles. Specific embodiments relate to a rinse valve bracket and connection system, a rinse ring tie down, and various improved connection systems.

Abstract: Embodiments of the disclosure provide systems and methods for improved removability and ease of maintenance for one or more components of the vacuum toilet system. They can be particularly useful on-board aircraft and other passenger transport vehicles. Specific embodiments relate to a rinse valve bracket and connection system, a rinse ring tie down, and various improved connection systems.

Abstract: An aircraft including a device for influencing the directional stability of the aircraft is provided. The device includes a control-input device; a flight control device; a sensor device for acquiring the rotation rates, including the yaw rates, of the aircraft; and at least one actuator, which is coupled with ailerons, spoilers, an elevator and a rudder. The flight control device includes a control function generating adjusting commands for the actuators for controlling the aircraft according to control commands. The aircraft includes two tail-mounted flaps, each including an actuator connected with the flight control device, situated symmetrically to each other and on opposite sides of the fuselage, and movable between retracted and extended positions. The control function is designed such that the adjusting commands that are generated on the basis of the control commands depending on the acquired rotation rates include adjusting commands to the actuators of the tail-mounted flaps.

Abstract: The system includes deflection transmission means (16) to provide a deflection position of the high-lift device (8) for each setting angle position of an adjustable HTP (2). Preferably, the deflection transmission means (18,20,23) comprise essentially of a mechanical linkage connected between the high-lift device (8) and the aircraft (1).

Abstract: An aircraft including: a fuselage and two wings to which engine nacelles are attached and that are each connected laterally to the fuselage, one on each side thereof, by a central fairing. The central fairing includes, facing each wing, two opposed surfaces connected one to a suction face side and the other to a pressure face side of the wing and that extend longitudinally along the fuselage. At least one of the two surfaces includes at least one local geometric deformation configured to generate lateral aerodynamic disturbances on the central fairing toward the wing to control the flow of air over the wing.

Abstract: An aircraft including a device for influencing the directional stability of the aircraft is provided. The device includes a control-input device; a flight control device; a sensor device for acquiring the rotation rates, including the yaw rates, of the aircraft; and at least one actuator, which is coupled with ailerons, spoilers, an elevator and a rudder. The flight control device includes a control function generating adjusting commands for the actuators for controlling the aircraft according to control commands. The aircraft includes two tail-mounted flaps, each including an actuator connected with the flight control device, situated symmetrically to each other and on opposite sides of the fuselage, and movable between retracted and extended positions. The control function is designed such that the adjusting commands that are generated on the basis of the control commands depending on the acquired rotation rates include adjusting commands to the actuators of the tail-mounted flaps.

Abstract: An aircraft including: a fuselage and two wings to which engine nacelles are attached and that are each connected laterally to the fuselage, one on each side thereof, by a central fairing. The central fairing includes, facing each wing, two opposed surfaces connected one to a suction face side and the other to a pressure face side of the wing and that extend longitudinally along the fuselage. At least one of the two surfaces includes at least one local geometric deformation configured to generate lateral aerodynamic disturbances on the central fairing toward the wing to control the flow of air over the wing.