An actuation system for a control surface for an aircraft includes a first, second, third and fourth actuator, a first and second bell crank, and at least one push pull rod system. Each of the first and second bell cranks comprises a first and a second crank arm, the first and second crank arms intersect with and are joined to each other at an intersection, the first and second crank arms extend from the intersection at an angle to each other, the first bell crank is pivotally connected to the sub-structure by a first pivot extending through the first bell crank's intersection, and the second bell crank is pivotally connected to the sub-structure by a second pivot extending through the second bell crank's intersection.

An actuation system for a control surface for an aircraft includes a first, second, third and fourth actuator, a first and second bell crank, and at least one push pull rod system. Each of the first and second bell cranks comprises a first and a second crank arm, the first and second crank arms intersect with and are joined to each other at an intersection, the first and second crank arms extend from the intersection at an angle to each other, the first bell crank is pivotally connected to the sub-structure by a first pivot extending through the first bell crank's intersection, and the second bell crank is pivotally connected to the sub-structure by a second pivot extending through the second bell crank's intersection.

An aircraft thermal hydraulic active-warming system includes an active thermal-warming valve interoperably coupled between a hydraulic pressure line and a hydraulic low-pressure return line and a hydraulic actuator arranged in parallel with the active thermal-warming valve between the hydraulic pressure line and the hydraulic low-pressure return line.

A system for controlling a hydraulic component. The system includes a control system configured to carry out a health check routine having steps of (A) fluidly connecting one of the hydraulic supply systems with the component until (i) a predetermined pressure is reached on the hydraulic supply side and/or the hydraulic return side, and/or (ii) a predetermined amount of time has passed; then (B) isolating the pressurised hydraulic fluid within the hydraulic supply side and the hydraulic return side so that hydraulic fluid leaks from the hydraulic supply side to the hydraulic return side via the controlled leakage; (C) monitoring the pressure of hydraulic fluid within the hydraulic supply side (50S) and/or the hydraulic return side over time; and then (D) determining if the pressure of hydraulic fluid within the hydraulic supply side and/or the hydraulic return side follows a predetermined or expected pattern.

A system for controlling a hydraulic component. The system includes a control system configured to carry out a health check routine having steps of (A) fluidly connecting one of the hydraulic supply systems with the component until (i) a predetermined pressure is reached on the hydraulic supply side and/or the hydraulic return side, and/or (ii) a predetermined amount of time has passed; then (B) isolating the pressurised hydraulic fluid within the hydraulic supply side and the hydraulic return side so that hydraulic fluid leaks from the hydraulic supply side to the hydraulic return side via the controlled leakage; (C) monitoring the pressure of hydraulic fluid within the hydraulic supply side (50S) and/or the hydraulic return side over time; and then (D) determining if the pressure of hydraulic fluid within the hydraulic supply side and/or the hydraulic return side follows a predetermined or expected pattern.

An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to move the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is moved away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

A method for controlling a control surface multirod actuator arrangement and the arrangement including: a first and a second multirod actuator configured to move or clamp around a first set of piston rods; a third multirod actuator configured to move or clamp around a second set of piston rods; a control unit configured to control motion of the first set of piston rods in a first motion mode and to control motion of the second set of piston rods in a second motion mode. Steps are moving at least one piston rod of first set of piston rods and/or clamping in parked position at least one piston rod of the second set of piston rods.

A Stability and Control Augmentation System (“SCAS”) module comprising one or more SCAS actuators, the or each SCAS actuator comprising a mechanical component that translates rotational motion to linear motion along a first axis of said SCAS; one or more electric motors for driving linear movement of the mechanical component in response to a command signal; and one or more angular transducers to detect the position of the SCAS actuator along the first axis.

A Stability and Control Augmentation System (“SCAS”) module comprising one or more SCAS actuators, the or each SCAS actuator comprising a mechanical component that translates rotational motion to linear motion along a first axis of said SCAS; one or more electric motors for driving linear movement of the mechanical component in response to a command signal; and one or more angular transducers to detect the position of the SCAS actuator along the first axis.

A stability control augmentation system and method for a flight control surface of an aircraft. The system includes s an actuator operable for actuating the flight control surface, and a control valve comprising a spool and an integrated augmentation mechanism. The spool and the actuation mechanism are both moveable to open and close a fluid flow path through the control valve to control the actuator.