A switching valve module which is part of a switching valve control system for use with reciprocating slat-type conveyors is disclosed herein. Disclosed herein is a switching valve module that includes an inner control valve and an outer control valve. A spool is positioned within the inner control valve and a spool positioned within the outer control valve. Movement of each the spool creates both a spool-type seal and a poppet-type seal between the spool and the respective control valve.

Motion of rams in fluid cylinders to drive machine parts is equalized by equalization chambers between drive chambers for equalizing outward and inward driven motion of the rams and the attached machine parts, irrespective of portions of loads and forces on the machine parts in relation to the rams. Duplicated machine parts may be closely positioned or widely separated, while providing the same controlled equalized movement irrespective of loading. The movable elements may be tilted to new angular positions before they are translated by the rams.

Motion of rams in fluid cylinders to drive machine parts is equalized by equalization chambers between drive chambers for equalizing outward and inward driven motion of the rams and the attached machine parts, irrespective of portions of loads and forces on the machine parts in relation to the rams. Duplicated machine parts may be closely positioned or widely separated, while providing the same controlled equalized movement irrespective of loading. The movable elements may be tilted to new angular positions before they are translated by the rams.

The present disclosure is directed to a hydrostatic transmission apparatus including a pump, a first motor, and a second motor having two elementary motors. Each of the motors having first and second enclosures for feed/discharge. In work mode and in road mode, the second enclosure of the first elementary motor of the second motor and the first enclosure of the first motor are connected together in series, the second enclosure of the first motor being connected to the second port of the pump, and the second enclosure of the second elementary motor of the second motor is connected to the second port of the pump. In work mode, the first enclosure of each of the two elementary motors of the third motor is connected to the first port of the pump.

The present disclosure is directed to a hydrostatic transmission apparatus including a pump, a first motor, and a second motor having two elementary motors. Each of the motors having first and second enclosures for feed/discharge. In work mode and in road mode, the second enclosure of the first elementary motor of the second motor and the first enclosure of the first motor are connected together in series, the second enclosure of the first motor being connected to the second port of the pump, and the second enclosure of the second elementary motor of the second motor is connected to the second port of the pump. In work mode, the first enclosure of each of the two elementary motors of the third motor is connected to the first port of the pump.

The subject matter of this specification can be embodied in, among other things, an assembly that includes a piston having a piston inner surface defining a cylindrical cavity and includes a first axial portion, a piston face at a first end of the first axial portion, a second axial portion at a second end of the first axial portion, and a helical piston thread defined upon the piston inner surface, a bushing configured to contact the piston inner surface, and a lock nut configured to engage the piston and the bushing.

A system and method for deploying a flight control surface. The method includes displacing actuators engaged with the flight control surface during an initial period wherein each actuator displaces from zero speed to a deployment speed, and during a deployment period after the initial period. The method includes during the deployment period, controlling displacement of at least one of the actuators in response to actuator status information received therefrom. The method includes during the initial period, limiting an acceleration of said actuator from the zero speed to the deployment speed. The system has a control unit with a force fight controller and an acceleration limiter.

A system and method for deploying a flight control surface. The method includes displacing actuators engaged with the flight control surface during an initial period wherein each actuator displaces from zero speed to a deployment speed, and during a deployment period after the initial period. The method includes during the deployment period, controlling displacement of at least one of the actuators in response to actuator status information received therefrom. The method includes during the initial period, limiting an acceleration of said actuator from the zero speed to the deployment speed. The system has a control unit with a force fight controller and an acceleration limiter.

A hydraulic control system includes a first hydraulic cylinder, a second hydraulic cylinder, a fluid supply apparatus, a first control valve bank, a second control valve bank, a third control valve bank, and a first check valve. The first control valve bank is configured to independently control the first hydraulic cylinder; the second control valve bank is configured to independently control the second hydraulic cylinder; and the third control valve bank is configured to synchronously control the first hydraulic cylinder and the second hydraulic cylinder. Synchronous volume control is implemented through series connection of the hydraulic cylinders, and has quite high synchronization precision, which is measured to be up to two percent.

An actuator system for controlling a control surface of an aircraft, which includes a control structure which defines the control surface and the control structure has an axis of rotation about which the control structure can rotate relative to the aircraft. A first actuator assembly has a first actuator arm and a second actuator assembly has a second actuator arm. The first actuator assembly and the second actuator assembly are spaced apart from one another along the axis of rotation. The first actuator arm is connected to a first band member and the first band member is connected to the control structure on a first side of the axis of rotation and the second actuator arm is connected to a second band member and the second band member is connected to the control structure on a second opposing side of the axis of rotation.