A control device, for a hydraulic consumer (22) and susceptible to vibrations, includes a valve (24) having a control spool (40) controllable by an actuating device (46). The valve (24) has a pressure supply port (P), to which a pressure compensator valve can be connected, which can be supplied with pressure fluid from a pressure supply device. The actuating device (46) has a motor (74). A load-pressure-dependent force on the control spool (40) can be generated by a control device (66). That force at the control spool (40) acts on an electronic motor controller (208) of the DC motor (74), which detects a change of the force and acts as a damping of the vibrations of the consumer (22) against this change of force.

Disclosed is a remote control smart blower. More particularly, the remote control smart blower includes a blower chamber (100) compressing external air flowing inside and discharging the compressed air; and a blower controller chamber (200) forming a predetermined-high partition with the blower chamber (100) and being able to operate and monitor in real time the power and operation status of a blower (110) disposed and fixed in the blower chamber (100), in which a manager can check the operation status of the blower (110) installed and fixed at a site and control and manage the blower (110) in real time using an exclusive terminal not only at the site, but regardless of the distance due to the blower controller chamber (200), whereby safety of operation and ease of management of the blower (110) are maximized.

Therefore, the present invention not only maximizes the usability of the blower (110) installed in a site, but also allows a manager to check the operation status and operation schedule of the blower (110) in real time regardless of the distance and to manage and control the operation condition and operation schedule according to the situation, whereby improving the ease and expertise of the blower (110).

A valve assembly includes a valve moveable between an open position where hydraulic fluid flow is permitted and a closed position where hydraulic fluid flow is blocked. A controller includes a magnetometer adapted to measure a magnetic flux through at least a portion of a solenoid linear actuator that moves the valve. A magnetic flux value measured by the magnetometer corresponds to a linear position of the regulating member relative to the port.

There is provided a spool type flow control valve including a sleeve in which a supply port, a control port, and an exhaust port are formed, and a spool accommodated to be movable in an axial direction inside the sleeve and including a valve body. The valve body controls an opening area of the control port so that a flow rate is controlled. A difference between a maximum value and a minimum value of an internal leakage amount which is a flow rate at which a gas supplied from the supply port is discharged from the exhaust port in a state where the control port is shut off is equal to or smaller than a predetermined threshold.

Passenger restraint systems are provided. The restraint systems can include: a passenger seat supported by a frame; a restraint bar pivotably attached to the frame; and at least one piston operably engaged between the restraint bar and the frame. Restraint system pistons are provided. The pistons can include: a central chamber housing a piston head and rod; a fluid reservoir in fluid communication with the central chamber; and at least one electromechanical valve operable between an open and a closed position. Methods for restraining a passenger within a seat are also provided.

The disclosure relates to a flight control system comprising at least one hydraulic servo actuator, wherein the servo actuator includes a two-stage electrohydraulic servo valve, wherein the servo valve comprises a pilot stage in which the control current is translated into a hydraulic control pressure, and a power stage in which a valve slide is moved in response to the control pressure in order to adjust the throughflow direction and throughflow cross-section of the valve. The disclosure furthermore relates to an aircraft comprising such a flight control system.

In accordance with at least one aspect of this disclosure, a system includes, a servo configured to control a position of a valve, a driver operatively connected to control movement of the servo, a control module operatively connected to control the driver, can configured to control the driver with pulse width modulated output to control a frequency of a generator through movement of the servo.

A rotary servo valve comprising a housing portion (105) defining a cylindrical cavity (107) and a first layer of ports. The rotary servo valve further comprises two opposing indented sides and two opposing sides having an increased radius relative to the indented sides, each side of increased radius extending between the two indented sides. The spool portion (103) is mounted for rotation relative to the cylindrical cavity (107), from a neutral position so as to prevent fluid flow through the valve, to an open position in which a fluid flow path is provided.

A directly-controlled hydraulic directional valve includes a housing, control piston, first and second springs, double-stroke solenoid, spring plate, adjustment device, and electronics. The piston is longitudinally displaceable in a bore in the housing, either directly or via a control sleeve. The springs are positioned in a region of an end of the piston remote from the solenoid. One end of each spring is supported on the spring plate, which is clamped between the springs and the piston. The other end of the first spring is fixed to the housing, and the other end of the second spring is fixed to the adjustment device. The first spring exerts a force on the piston in a first direction, and the second spring exerts a force on the piston in a second opposite direction, so as to bias the piston into a preferred position. The solenoid is mounted on a side of the housing, and is operable to move the piston out from the preferred position in opposite directions proportional to an electric current from the electronics, such that the piston moves to the preferred position in response to each of non-actuation of the solenoid and a fault in the electronics. The adjustment device is operable to alter a position of the other end of the second spring to adjust the preferred position of the piston.

The disclosure relates to a flight control system comprising at least one hydraulic servo actuator, wherein the servo actuator includes a two-stage electrohydraulic servo valve, wherein the servo valve comprises a pilot stage in which the control current is translated into a hydraulic control pressure, and a power stage in which a valve slide is moved in response to the control pressure in order to adjust the throughflow direction and throughflow cross-section of the valve. The disclosure furthermore relates to an aircraft comprising such a flight control system.