A tester apparatus is described. Various components contribute to the functionality of the tester apparatus, including an insertion and removal apparatus, thermal posts, independent gimbaling, the inclusion of a photo detector, a combination of thermal control methods, a detect circuitry in a socket lid, through posts with stand-offs, and a voltage retargeting.

A supporting assembly configured to fix a casing of an electronic device to a chassis and including a plate body, a cushioning component and a fastener. The plate body includes a mounting hole. The cushioning component is disposed through the mounting hole. The cushioning component includes a through hole. The fastener is disposed through the through hole of the cushioning component. A side of the fastener is configured to be fixed to the chassis, and the cushioning component is compressed by another side of the fastener and the chassis.

The invention relates to a reference potential assembly and an attachment assembly for an electrical circuit, the assembly having an electrically conductive flexible clip (30) which includes: an electrical circuit clamping conductor clamp; an electrical contact stub (42); an attachment (43) adapted to clamp the electrical contact stub (42) against an electrical contact surface.

A supporting assembly configured to fix a casing of an electronic device to a chassis and including a plate body, a cushioning component and a fastener. The plate body includes a mounting hole. The cushioning component is disposed through the mounting hole. The cushioning component includes a through hole. The fastener is disposed through the through hole of the cushioning component. A side of the fastener is configured to be fixed to the chassis, and the cushioning component is compressed by another side of the fastener and the chassis.

The present application relates to providing mechanical and environmental protection to an electronics rack including a frame configured in a vertical orientation configured to receive an electronics rack, a front cover and a back cover, wherein the front cover and the back cover are configured to enclose the electronics rack when the front cover is attached to the frame and when the back cover is attached to the frame, a first fastener for mechanically coupling a top portion of the electronics rack to a top portion of the frame, a second fastener for coupling a bottom portion of the electronics rack to a bottom portion of the frame and a horizontal base for supporting the frame, the base including a mechanical interface for a material handling device, at least one castor and at least one floor lock.

A method and assembly for locking/unlocking, formed of one of several a removable module (2) and a mount plate (3). The assembly includes a support wall (4) supporting each removable module (2). The removable module (2) being provided with two lugs (5) through which an aperture passes. The lugs (5) extending out of the removable (2) so that they can be inserted into opening (7) formed in the support wall (4). This assembly is equipped with a locking/unlocking system (100) having a lever (10) extending under the support wall (4) and provided with circular eccentric cams (11) arranged with offset axial symmetry in the form of an S about a central rotation axle (20) perpendicular to the support wall (4). The lever (10) being fixed in terms of rotation on this central axle (2) at equal distances from the two openings (7).

A tester apparatus is described. Various components contribute to the functionality of the tester apparatus, including an insertion and removal apparatus, thermal posts, independent gimbaling, the inclusion of a photo detector, a combination of thermal control methods, a detect circuitry in a socket lid, through posts with stand-offs, and a voltage retargeting.

An aircraft comprising a fuselage (1) subdivided by a floor (2) into a top volume (3) and a bottom value (4) in which girders (5) extend supporting the floor and co-operating with the fuselage and the floor to define two lateral housings (6) that are of substantially triangular cross-section and that extend parallel to a longitudinal axis of the fuselage. Calculation units (100) are arranged in the lateral housings and each comprises a box (101) defining a main compartment containing calculation modules (122) insertable into the main compartment along an insertion axis through an opening in the compartment and connectable to the connectors (115) carried by a back wall (116) of the compartment so as to extend into the main compartment opposite from the opening, the insertion axis being substantially parallel to the longitudinal axis of the fuselage.

A handle locking structure includes a handle having a pivot portion pivotally connected to a sliding box, a buckle portion for hooking on a cabinet and a handle shaft, and a positioning structure including a base connected to the handle shaft, a positioning device mounted in the base and an elastic member placed on the positioning device. When the handle is hooked on the cabinet, a peripheral limiter of a head member of the positioning device is disengaged from a position-limiting notch of the base to reset the elastic member, so that the positioning device is automatically locked to the sliding box, avoiding vibration of the handle and improving the locking stability of the handle.

An avionics mounting unit includes a housing with a first mounting interface to couple the housing to a structure of an aircraft and a second mounting interface to couple an avionics device to the housing. The second mounting interface includes slots oriented orthogonal to each other and extending to sides of the housing such that the avionics device can be installed via the slots from any of four sides of the housing. The avionics mounting unit also includes communication circuitry, power supply circuitry, one or more avionics device interface ports, and one or more aircraft interface ports. The avionics device interface port(s) are configured to provide power to the avionics device and configured to enable data communications with the avionics device. The aircraft interface port(s) are configured to receive power from the aircraft and to enable data communications between other aircraft systems and the avionics device.