The present disclosure relates to a load-sense system such as a load-sense steering system that operates in a static load-sense mode for low flows and operates in a dynamic load-sense mode for high flows.

Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

A hydraulic actuator circuit is disclosed for use with first and second shock absorbers, which each may include a piston disposed within a housing. The piston helps define upper and lower working chambers. The circuit may have a motor, a first pump, driven by the motor, and is associated with the first shock absorber and the motor. A second pump, driven by the motor, may be associated with the second shock absorber. A first accumulator communicates with both of the first and second pumps. A first switch valve may assist in controlling fluid flow into the chambers of the first shock absorber. A second switch valve may assist in controlling fluid flow into the chambers of the second shock absorber.

Provided is a pump device and a hydraulic actuator that can reduce the number of steps of performance measurement. The pump device includes: a switching valve for switching a flow of oil to a first chamber or a second chamber of a cylinder device, the inside of which is segmented into the first chamber and the second chamber by a piston; an up blow valve (first chamber-side relief valve) that relieves pressure of a first chamber-side flow path connected to the first chamber; and a down blow valve (second chamber-side relief valve) that relieves pressure of a second chamber-side flow path connected to the second chamber.

The present disclosure relates to a hydraulic control circuit for crane slewing gear having directional valves arranged in work lines and controllable separately for the inflow and outflow to the hydraulic motor for the carrying out of a rotational movement of the slewing gear, wherein an inflow valve serves the control of the oil inflow from a hydraulic pump via the work line to the hydraulic motor and an outflow valve is provided via which the hydraulic motor can be relieved to the tank, wherein the work lines are each connected via at least one check valve to a common inlet of the outflow valve to relieve the hydraulic motor independently of the direction of rotation of the slewing gear via an outflow valve into the tank.

A directional control valve for a dual action hydraulic pump is provided. The directional control valve can include a valve body comprising four ports and a rotor positioned within the valve body and comprising a plurality of passages configured to connect and disconnect the ports of the valve body. The directional control valve can also include a plurality of shear seal discs, each positioned adjacent to one of the plurality of passages, a sensor, and a motor configured to adjust a position of the rotor. The motor can be a brushless motor or a stepper motor.

A pilot device for a hydraulic directional valve includes a displacement sensor, a pilot valve, an actuating device, a coil assembly, and a circuit board. The displacement sensor has a sensor axis and the pilot valve has a valve axis. The valve axis and the sensor axis are arranged substantially parallel to one another so as to lie in a reference plane. The actuating device and the coil assembly are arranged adjacent to one another. The circuit board is arranged parallel to the reference plane. In each case, to establish an electrical contact, the coil assembly, the actuating device, and an electrical plug connection are either soldered directly to the circuit board or are in breakable electrical contact with a respectively associated, rigid contact assembly. The contact assembly is soldered directly to the circuit board.

Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

A pilot device for a hydraulic directional valve includes a displacement sensor, a pilot valve, an actuating device, a coil assembly, and a circuit board. The displacement sensor has a sensor axis and the pilot valve has a valve axis. The valve axis and the sensor axis are arranged substantially parallel to one another so as to lie in a reference plane. The actuating device and the coil assembly are arranged adjacent to one another. The circuit board is arranged parallel to the reference plane. In each case, to establish an electrical contact, the coil assembly, the actuating device, and an electrical plug connection are either soldered directly to the circuit board or are in breakable electrical contact with a respectively associated, rigid contact assembly. The contact assembly is soldered directly to the circuit board.