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 linear actuator system includes a linear actuator and an integrated pump assembly connected to the linear actuator to provide fluid to operate the linear actuator. The integrated pump assembly includes a pump with two fluid drivers, each fluid driver comprising a prime mover and a fluid displacement assembly to be driven by the prime mover such that fluid is transferred from a first port of the pump to a second port of the pump. The pump assembly also includes two valve assembles to isolate the pump from the system. The linear actuator system also includes a controller that establishes the pump in a normal mode of operation in which the prime movers are independently driven and switches to a fail-safe mode of operation in which only one prime mover is operated.

There is provided a fluid circuit capable of continuously driving pressure-increasing devices with a simple configuration. A plurality of pressure-increasing devices are connected in parallel to a fluid supply device that delivers a working fluid. A stroke direction of the piston of each of the pressure-increasing device is switched by the working fluid. A phase of the piston of one pressure-increasing device is different from a phase of the piston of the other pressure-increasing device.

A work machine control system includes: a pump; a cylinder operating a working equipment element in a movable range based on hydraulic oil supplied from the pump; a first path connected to the pump; a second path branching from the first path; a control valve adjusting the flow rate of the oil supplied to the cylinder via the first path; a bleed valve adjusting the flow rate of the oil discharged to a tank via the second path; a sensor detecting a posture of the element in the range; and a control device outputting a first command for adjusting the flow rate of the oil supplied to the cylinder and a second command for adjusting the flow rate of the oil discharged to the tank when the element is determined to be present in an end section of the range based on detection data of the sensor.

The disclosure relates to a volume flow supply, in particular for closed center LS systems, comprising a pressure supply device and a pressure balance as components of a supply system for supplying fluid of a load which can be hydraulically connected to the supply system. The pressure supply device provides a volume flow when required in order to supply the hydraulic load in that the pressure balance is made of a circulation pressure balance which discharges a possible surplus volume flow out of the supply flow. The volume flow supply also comprises a controller which reduces the surplus volume flow to a minimum by actuating the pressure supply device.

A floating control system for a fixed displacement pump system is disclosed, which relates to the technical field of floating mechanisms and includes: a fixed displacement pump, floating control valves, a floating mechanism, boom function valves, an actuator and a control device, where the fixed displacement pump, the floating control valves and the floating mechanism are connected in sequence, the fixed displacement pump, the boom function valves and the actuator are connected in sequence, the floating control valves include a pressure reducing valve and a floating switching valve, and the boom function valves include a fixed differential overflow valve and a proportional directional valve; and the fixed differential overflow valve and the proportional directional valve are connected in parallel between the fixed displacement pump and an oil return tank, the floating switching valve and the fixed differential overflow valve are connected through a feedback oil path.

A work machine includes: a main circuit that supplies a working fluid from a pump to an actuator; a pilot circuit that introduces part of the working fluid from the pump, to a pilot pressure receiving section of a control valve; a bleed-off passage that connects the pump and a tank. The pilot circuit is provided with: a first pressure reducing valve that generates a pilot primary pressure; and second and third pressure reducing valves that generate a pilot secondary pressure to be applied to the control valve and a bleed-off valve. A moving area of a spool of the bleed-off valve has a first moving area where an opening area of a restrictor changes stepwise, and a second moving area where the opening area of the restrictor changes continuously. A controller controls the third pressure reducing valve such that the spool is positioned in the first moving area at the time of non-operation of the actuator, and the spool is positioned in the second moving area at the time of operation of the actuator. The restrictor of the bleed-off valve has a restricting hole that gives a resistance to the working fluid passing therethrough in a case the spool is positioned in the first moving area.

A hydraulic system (12) for an aircraft (10), wherein the hydraulic system (12) includes a hydraulic power pack (14), a hydraulic fluid reservoir (28) and a hydraulic pump (30), a hydraulic consumer (18), a high-pressure supply line (38) supplying the hydraulic consumer (18) with hydraulic fluid under higher pressure, and a low-pressure return line (40) returning hydraulic fluid under lower pressure from the hydraulic consumer (18); heating device (42) with a short-cut line (44) connecting the high-pressure supply line (38) with the low-pressure return line (40) and a heater valve (46) for opening and closing the short-cut line (44), and a control and monitoring unit (43). Temperature management includes automatically controlling a fluid temperature by monitoring the fluid temperature and controlling the heater valve (46).