An exemplary aircraft includes a pylon rotatable relative to a wing, a proprotor assembly carried by the pylon, the proprotor assembly have a proprotor blade that is foldable to a stowed position extending substantially parallel to the pylon, and a fluidic clamp positioned with the pylon and configured to grip the proprotor blade when in the stowed position, the fluidic clamp including a first inflatable bladder positioned on a first side of an opening for receiving a portion of a proprotor blade and a pressurized fluid source in fluid connection with the first inflatable bladder.

Methods, apparatus, systems and articles of manufacture are disclosed for redundant actuation of control surfaces. An example apparatus includes a control surface of an aircraft, and an actuator to move the control surface. The example apparatus also includes an electric motor to move the actuator; the electric motor communicatively coupled to an electrical system of the aircraft. The example apparatus also includes a hydraulic motor to move the actuator, the hydraulic motor fluidly coupled to a hydraulic system of the aircraft. The example apparatus also includes a sensor to detect incorrect operation of the hydraulic system. The example apparatus also includes a switch operatively coupled to the sensor, the switch to enable operation of the electric motor in response to the detected incorrect operation of the hydraulic system.

Methods, apparatus, systems and articles of manufacture are disclosed for redundant actuation of control surfaces. An example apparatus includes a control surface of an aircraft, and an actuator to move the control surface. The example apparatus also includes an electric motor to move the actuator; the electric motor communicatively coupled to an electrical system of the aircraft. The example apparatus also includes a hydraulic motor to move the actuator, the hydraulic motor fluidly coupled to a hydraulic system of the aircraft. The example apparatus also includes a sensor to detect incorrect operation of the hydraulic system. The example apparatus also includes a switch operatively coupled to the sensor, the switch to enable operation of the electric motor in response to the detected incorrect operation of the hydraulic system.

Described herein is an apparatus comprising an aircraft wing and a trailing edge aerodynamic surface connected to a trailing edge of the aircraft wing via a piston assembly in which the piston assembly holds the trailing edge aerodynamic surface in a neutral position relative to the aircraft wing at a constant supply pressure. The piston assembly may be implemented using a pneumatic piston or a hydraulic piston. A first end of the piston assembly may be connected to the aircraft wing and a second end of the piston assembly may be connected to the trailing edge aerodynamic surface. The piston assembly may include a pressure relief valve which may open or close, raising or lowering the aerodynamic surface, responsive to lift load on the aircraft wing.

Described herein is an apparatus comprising an aircraft wing and a trailing edge aerodynamic surface connected to a trailing edge of the aircraft wing via a piston assembly in which the piston assembly holds the trailing edge aerodynamic surface in a neutral position relative to the aircraft wing at a constant supply pressure. The piston assembly may be implemented using a pneumatic piston or a hydraulic piston. A first end of the piston assembly may be connected to the aircraft wing and a second end of the piston assembly may be connected to the trailing edge aerodynamic surface. The piston assembly may include a pressure relief valve which may open or close, raising or lowering the aerodynamic surface, responsive to lift load on the aircraft wing.

A method of cooling hydraulic fluid for an aircraft hydraulic system is provided. The method comprises connecting an output side of an external cooling system to a return side of an electric motor driven pump (EMDP) in the hydraulic system and connecting an input side of the external cooling system to a hydraulic fluid reservoir in the hydraulic system. The EMDP pumps hydraulic fluid through the hydraulic system under conditions wherein fuel tanks in the aircraft are empty, and the external cooling system cools the hydraulic fluid as the EMDP pumps the hydraulic fluid, wherein the hydraulic fluid passes from the hydraulic fluid reservoir and through the external cooling system before entering the EMDP.

An aircraft control comprises a mobile pedal and comprises a cylinder coupled to the pedal such that a displacement of the pedal according to at least a first direction reduces the volume of a first chamber of the cylinder. A control device comprises a fluid type bus system connecting two aircraft controls. Additionally, an aircraft is equipped with such a control device.

An aircraft control comprises a mobile pedal and comprises a cylinder coupled to the pedal such that a displacement of the pedal according to at least a first direction reduces the volume of a first chamber of the cylinder. A control device comprises a fluid type bus system connecting two aircraft controls. Additionally, an aircraft is equipped with such a control device.

A power source for an aircraft including a solid oxide fuel cell and a proton exchange membrane fuel cell along with a solid oxide fuel cell multi-power source. At least one battery is electrically coupled to the solid oxide fuel cell, the proton exchange membrane fuel cell, and an aircraft distribution network to supply electricity to the aircraft and also for becoming recharged by the solid oxide fuel cell and the proton exchange membrane fuel cell.

An actuation system for controlling flight control members of a vehicle. Each flight control member is controlled by two or more linear hydraulic actuators. Synchronization members extend between the hydraulic actuators on the same flight control members to synchronize the movements of the hydraulic actuators for consistent movement across the length of the flight control members. Brakes can maintain the positions of the synchronization members and thus the flight control members. Motors can provide for moving the synchronization members to control the positioning of the hydraulic actuators and flight control members.