A method and apparatus for auto range control are described. In one embodiment, the apparatus comprises a projector configured to project a sequence of light patterns on an object; a first camera configured to capture a sequence of images of the object illuminated with the projected light patterns; a controller coupled to the projector and first camera and operable to receive the sequence of images and perform range control by controlling power of the sequence of light patterns being projected on the object and exposure time of a camera based on information obtained from the sequence of images captured by the camera.

A cylinder device includes a piston and a piston rod disposed movably, and a movable body in which another end portion of the piston rod is inserted. The piston rod includes a first pin groove that extends along an axial direction and through which a support pin is inserted. The support pin is also inserted through second pin grooves formed in the movable body and having a substantially L-shaped cross section. Further, a link pin is inserted through a pin hole on the other end portion of the piston rod. The link pin is inserted through third pin grooves in the movable body which are inclined at a predetermined angle with respect to the axis of the movable body. In addition, under a moving action of the piston, the movable body is displaced linearly, and thereafter, is rotationally displaced by the link pin moving along the third pin grooves.

A method and apparatus for auto range control are described. In one embodiment, the apparatus comprises a projector configured to project a sequence of light patterns on an object; a first camera configured to capture a sequence of images of the object illuminated with the projected light patterns; a controller coupled to the projector and first camera and operable to receive the sequence of images and perform range control by controlling power of the sequence of light patterns being projected on the object and exposure time of a camera based on information obtained from the sequence of images captured by the camera.

A hydraulic system for an aircraft. The hydraulic system can include a hydraulic actuator that is operatively coupled to a flight control member. Hydraulic fluid is moved through the hydraulic system by an engine driven pump that delivers hydraulic fluid to the actuator at a first pressure, and a boost pump that delivers hydraulic fluid to the actuator at a second pressure that is higher than the first pressure. The hydraulic system is configured such that the hydraulic fluid returning from the actuator to the engine driven pump can be delivered to the boost pump prior to reaching the engine driven pump.

A portable tool having a working head that is actuated by an electric motor and/or a hydraulic medium and has a working part. The working part is displaceable in a displacement direction and the working head is rotatable together with the working part in the circumferential direction with respect to the displacement direction. The working head is rotatable together with the working part hydraulically and by the motor. The working head has a segment mounted therein, the segment having a largest extension in the circumferential direction by a first angular amount, and that the rotation of the working head and the working part takes place in the circumferential direction by a second angular amount, wherein values of the first and the second angular amounts are different. Moreover, a method for operating a portable tool is provided using first and second hydraulic pistons.

An e.g. fluid powered linear actuator is provided with a helical orientation surface in a fixed angular position relative to a first component; and a follower in a fixed angular position relative to a second component. When the first and second components are moved towards one another as the actuator is retracted, the follower engages and moves along the helical orientation surface to rotate the first and second components to a predetermined relative angular position.

The invention relates to a clamping cylinder (100) comprising a body (110) and a movable assembly (102) contained in a receiving chamber (112) of the body, rotatable and translatable relative to the body along a predetermined movement axis (V), the cylinder comprising guide means (142; 150) in order to guide the movable assembly between a clamping position and a free position. The guide means comprise: at least one cylindrical roller (150A-150D) arranged on the body of the cylinder such that the axis of the roller is essentially perpendicular to the movement axis (V), a rod (104) of the movable assembly extending along the movement axis and being configured so as to comprise at least one movement portion (142) having a polygonal section in a plane normal to the movement axis, the section comprising at least one rectilinear edge, the movement portion (142) being configured such that said section follows an essentially helical base line around the movement axis over at least a fraction (143) of the portion, the rod (104) and the rollers (150A-150D) being positioned such that a roller is arranged across from each of the sides of the polygonal section.

The present disclosure concerns a nacelle for an aircraft turbojet engine that includes a thrust reverser having a cowl displaceable between a deployed position and a stowed position, a fixed structure, and a secondary nozzle. The nozzle includes panels movable in rotation, and hydraulic actuators for sequenced actuation of the cowl and panels. The actuators include a body mounted on the fixed structure, and a rod mounted in the body and is linked to the cowl and panels via a device for transmitting movement of the actuator to the panel. An actuation system having a hydraulic control device controls the displacement of the rod of the actuator. The actuator further includes a device for alternately displacing the rod in translation relative to the body to cause translation of the cowl, or in rotation relative to the body to cause rotation of the nozzle panel.

A rotary actuator where a thrust bearing ring is positioned at an inside of a tube assembly accommodating oil, thereby reducing abrasion and damage caused by rolling friction and improving rotary power of an axle load by increasing hydraulic pressure of a piston. The rotary actuator includes the tube assembly, a piston, an axle load assembly, and a thrust bearing ring. The tube assembly is provided with a tube spiral portion where a spiral is formed at an inner circumference surface, and is formed of a first passage where oil flows into and out and a second passage spaced apart from the first passage by a fixed distance.

The present disclosure concerns a nacelle for an aircraft turbojet engine that includes a thrust reverser having a cowl displaceable between a deployed position and a stowed position, a fixed structure, and a secondary nozzle. The nozzle includes panels movable in rotation, and hydraulic actuators for sequenced actuation of the cowl and panels. The actuators include a body mounted on the fixed structure, and a rod mounted in the body and is linked to the cowl and panels via a device for transmitting movement of the actuator to the panel. An actuation system having a hydraulic control device controls the displacement of the rod of the actuator. The actuator further includes a device for alternately displacing the rod in translation relative to the body to cause translation of the cowl, or in rotation relative to the body to cause rotation of the nozzle panel.