Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.

Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.

A method for generating an optimum vertical trajectory of a flight trajectory of an aircraft in the descent/approach phase. The trajectory is defined between a current state and a target state of the aircraft on the basis of a speed profile of the aircraft as a function of a curvilinear abscissa of the aircraft along a flight plan. The profile corresponds to a transition between the current and target states and is broken down into successive segments each corresponding to a different aerodynamic configuration that the aircraft may adopt during the descent/approach phase. The method is based on defining a set of flight strategies, each strategy of the set being defined using for each segment of the speed profile flight parameters chosen randomly in ranges of values compatible with the aerodynamic configuration corresponding to that segment. Optimum vertical trajectory is generated on the basis of the strategy of the set.

A method for generating an optimum vertical trajectory of a flight trajectory of an aircraft in the descent/approach phase. The trajectory is defined between a current state and a target state of the aircraft on the basis of a speed profile of the aircraft as a function of a curvilinear abscissa of the aircraft along a flight plan. The profile corresponds to a transition between the current and target states and is broken down into successive segments each corresponding to a different aerodynamic configuration that the aircraft may adopt during the descent/approach phase. The method is based on defining a set of flight strategies, each strategy of the set being defined using for each segment of the speed profile flight parameters chosen randomly in ranges of values compatible with the aerodynamic configuration corresponding to that segment. Optimum vertical trajectory is generated on the basis of the strategy of the set.

Aircraft and associated methods, apparatus, system and storage devices for automatically positioning of lift control devices such as high lift devices including slats and flaps so an aircraft equipped with this technology will not need to count on the crew to command the lift control devices.

Aircraft and associated methods, apparatus, system and storage devices for automatically positioning of lift control devices such as high lift devices including slats and flaps so an aircraft equipped with this technology will not need to count on the crew to command the lift control devices.

An aerodynamic structure incorporated in an aircraft control surface provides a spar extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.

A galley cart includes walls defining an interior cavity extending between a front and a rear of the galley cart and the interior cavity extending between a top end and a bottom end. A supply port is provided in flow communication with the interior cavity at or near either the top end or the bottom end of the cart. A return port is provided in flow communication with the interior cavity that is adjacent the supply port at or near the top end or the bottom end of the cart. A barrier is positioned between the supply port and the return port within the interior cavity of the cart to define a supply chamber and a return chamber to control airflow through the interior cavity.

A galley cart includes walls defining an interior cavity extending between a front and a rear of the galley cart and the interior cavity extending between a top end and a bottom end. A supply port is provided in flow communication with the interior cavity at or near either the top end or the bottom end of the cart. A return port is provided in flow communication with the interior cavity that is adjacent the supply port at or near the top end or the bottom end of the cart. A barrier is positioned between the supply port and the return port within the interior cavity of the cart to define a supply chamber and a return chamber to control airflow through the interior cavity.

Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.