Abstract: Systems and methods for using high-impact fasteners to couple components of a solar power system together to prevent these components from any movement or slippage relative to each other. A strap may be secured over a top surface of the high-impact fasteners and around the components to prevent a disengagement of the high-impact fastener from the components and a separation of the components.

Abstract: A module mounting assembly that couples a PV module to a support structure is provided. The module mounting assembly may include a mounting bracket, a mounting pin, and a clamp. The clamp may be configured to couple the mounting bracket to the support structure and the mounting pin may be configured to couple the mounting bracket to the PV module. The mounting pin may have a number of features and designs that facilitate positioning the mounting pin within the openings and retaining the mounting pin in an installed state.

Abstract: The invention relates to a method for the self-calibration of electric jacks (6a, 6b) capable of actuating a mobile member (2) of a turbojet nacelle (1) and connected to at least one position measuring member, characterized in that it comprises the steps of: moving the jack(s) into a retracted position corresponding to a first position of the mobile member, storing one or more position values fed back by the position measuring member for the jack(s) in said retracted position; moving the jack(s) into an extended position corresponding to a second position of the mobile member; storing one or mom position values fed back by the position measuring member for the jack(s) in said extended position.

Abstract: The invention relates to a turbojet nacelle (1) and to an aeroacoustic noise reduction device for said nacelle, the nacelle comprising a nozzle (10) on the downstream end thereof, said nozzle (10) comprising an inner wall inside which a first flow from the turbojet circulates and an outer wall (102) outside which a second flow corresponding to the surrounding outside air circulates. The invention also relates to an aeroacoustic noise reduction device (20) of the turbojet, comprising a plurality of chevrons (201) arranged on the circumference of the nozzle (10). The invention is characterized in that the aeroacoustic noise reduction device also comprises a slide (202) arranged on the circumference of the nozzle in such a way that it can rotate about the axis of the nozzle, each chevron (201) being connected to the slide (202) by means of a guiding element (204) that can move along the slide (202) during the rotation thereof in order to ensure the displacement of the chevron (201).

Abstract: The invention relates to a turbojet nacelle (1) and to an aeroacoustic noise reduction device for said nacelle, the nacelle comprising a nozzle (10) on the downstream end thereof, said nozzle (10) comprising an inner wall inside which a first flow from the turbojet circulates and an outer wall (102) outside which a second flow corresponding to the surrounding outside air circulates. The invention also relates to an aeroacoustic noise reduction device (20) of the turbojet, comprising a plurality of chevrons (201) arranged on the circumference of the nozzle (10). The invention is characterised in that the aeroacoustic noise reduction device also comprises a slide (202) arranged on the circumference of the nozzle in such a way that it can rotate about the axis of the nozzle, each chevron (201) being connected to the slide (202) by means of a guiding element (204) that can move along the slide (202) during the rotation thereof in order to ensure the displacement of the chevron (201).

Abstract: The invention relates to an electrical control system for the nacelle of a turboreactor, comprising a plurality of electromechanical maneuvering elements for a plurality of actuating devices embodied as auxiliary parts of the turboreactor. The invention is characterized in that the control system comprises an electronic control box comprising a plurality of control inlets to be connected to control elements, and a plurality of outlets connected to electromechanical maneuvering of the auxiliary actuating devices. The control box can translate each instruction received into an operating sequence for at least one corresponding electromechanical maneuvering element. The invention also relates to a nacelle and an aircraft provided with one such control system.

Abstract: The invention relates to a method for the self-calibration of electric jacks (6a, 6b) capable of actuating a mobile member (2) of a turbojet nacelle (1) and connected to at least one position measuring member, characterised in that it comprises the steps of: moving the jack(s) into a retracted position corresponding to a first position of the mobile member, storing one or more position values fed back by the position measuring member for the jack(s) in said retracted position; moving the jack(s) into an extended position corresponding to a second position of the mobile member; storing one or mom position values fed back by the position measuring member for the jack(s) in said extended position.

Abstract: The invention relates to a jack (1) that comprises, on the one hand, a rod (2) that can be driven in translation by a driving system (5, 6), and, on the other hand, a system for blocking the expansion of the rod that comprises at least one bolt (9) mounted so as to move between an engagement position, in which it defines an abutment means for the rod in the expansion direction thereof, and a release position, in which it is spaced away from the rod and allows the expansion thereof, wherein the bolt is associated with a barrel (14) having a first stable position in which it maintains the bolt (9) in the engagement position and a second stable position in which it maintains the bolt (9) in its release position, said barrel system (14) being designed so that it can be alternatively switched from the first stable position to the second stable position under the action of the rod (2) driven by a slight backward movement before expansion and at the end of the return stroke.

Abstract: The invention relates to an electrical control system for the nacelle of a turboreactor, comprising a plurality of electromechanical manoeuvring elements for a plurality of actuating devices embodied as auxiliary parts of the turboreactor. The invention is characterized in that the control system comprises an electronic control box comprising a plurality of control inlets to be connected to control elements, and a plurality of outlets connected to electromechanical manoeuvring of the auxiliary actuating devices. The control box can translate each instruction received into an operating sequence for at least one corresponding electromechanical manoeuvring element. The invention also relates to a nacelle and an aircraft provided with one such control system.

Abstract: An aircraft cabin including at least two seats, which seat each include at least two elements which can be moved relative to each other and at least one actuator for the relative displacement of these movable elements, and at least one central power control unit in the cabin in order to allocate a total available power level to each seat, where each seat includes parts for reading at least one item of morphological information of the passenger sitting in the seat, and a part for transmitting information to the central power control unit in accordance with each item of morphological information, and the central power control unit is capable of allocating to each seat a total available power level in accordance with each item of morphological information.

Abstract: The installation (10) for controlling power in an aircraft comprises a power distribution network (22); at least two subscribers (14A, 14B, 14C) connected to the network (22); a central power control unit (20) which is capable of allocating a total available power level to each subscriber; and a device for determining the total power effectively consumed for each load of the subscribers. The central power control unit (20) acquires information which represents the total power effectively consumed by each subscriber and is capable of allocating the total available power to each subscriber in accordance with the total power levels effectively consumed by the subscribers.

Abstract: A wheel assembly for a vehicle, includes a wheel rim (16) and a tire (18) defining a closed space (30) therebetween which is filled with a pressurized gas. The inventive wheel assembly also includes a pressurized-gas reservoir (40) and elements (50) for selectively connecting the pressurized-gas reservoir (40) to the closed space (30) defined between the wheel rim (16) and the tire (18). The pressurized-gas reservoir (40) is rotationally fixed to the wheel rim (16).

Abstract: The installation (10) for controlling power in an aircraft comprises: a power distribution network (22); at least two subscribers (14A, 14B, 14C) connected to the network (22); a central power control unit (20) which is capable of allocating a total available power level to each subscriber; and means for determining the total power effectively consumed for each load of the subscribers. The central power control unit (20) comprises means (18B) for acquiring information which represents the total power effectively consumed by each subscriber and is capable of allocating the total available power to each subscriber in accordance with the total power levels effectively consumed by the subscribers.

Abstract: The aircraft cabin comprises: at least two seats (14A, 14B, 14C) which each comprise at least two elements which can be moved relative to each other and at least one actuator (24, 26) for the relative displacement of these movable elements, at least one central power control unit (20) in the cabin in order to allocate a total available power level to each seat. Each seat (14A, 14B, 14C) comprises means (30, 32, 34) for reading at least one item of morphological information of the passenger sitting in the seat, and means (18B) for transmitting information to the central power control unit (20) in accordance with the or each item of morphological information. The central power control unit (20) is capable of allocating to each seat (14A, 14B, 14C) a total available power level in accordance with the or each item of morphological information.

Abstract: A power management installation in an aircraft includes a power distribution network and at least two subscribers. Each subscriber has loads consuming electric power and local control means. The power management installation allocates, to each subscriber, a maximum total power for all the loads and evaluates, for each subscriber, the total electric power consumed. The conditions for controlling the loads of each subscriber are modified according to the controlled loads of the subscriber, the total electric power consumed by the subscriber and the maximum total power allocated to the subscriber.

Abstract: A wheel assembly for a vehicle, includes a wheel rim (16) and a tire (18) defining a closed space (30) therebetween which is filled with a pressurized gas. The inventive wheel assembly also includes a pressurized-gas reservoir (40) and elements (50) for selectively connecting the pressurized-gas reservoir (40) to the closed space (30) defined between the wheel rim (16) and the tire (18). The pressurized-gas reservoir (40) is rotationally fixed to the wheel rim (16).

Abstract: A power management installation in an aircraft includes a power distribution network and at least two subscribers, each subscriber having loads consuming electric power and local control means. The power management installation has means for allocating, to each subscriber, a maximum total power for all the loads; means of evaluating for each subscriber, the total electric power consumed; and means for modifying the conditions for controlling the loads of each subscriber, according to the control loads of the subscriber, the total electric power consumed by the subscriber and the maximum total power allocated to the subscriber.

Abstract: A device for actuating a seat element includes an actuator fitted with a transducer delivering a state information representative of the current position of the actuator and a unit for controlling the actuator which includes a device for registering and for storing several reference state informations each representative of a position of the actuator for an identified position of the element and a device for driving the actuator so as to move the seat element towards several target positions. The control unit is adapted so as, when a movement towards a predetermined target position is commanded, to activate the actuator until the current reference state information delivered by the transducer is equal to the reference state information stored for the position of the commanded element.

Abstract: The invention relates to an actuator for operating an access door on an aeroplane, comprising a body (18) fitted with a motor member (20) and with a drive member (24) that is movable relative to the body (18) under the action of the motor member (20). The motor member (20) is an electric motor, and the mechanical means (22) of movement transmission are mounted inside the body (18) between the electric motor (20) and the drive member (24) to drive the said drive member (24) from the electric motor (20). The transmission means (22) comprise means (26) of mechanical disengagement of the electric motor (20) from the drive member (24), which, after disengagement, allow the drive member (24) to be moved independently of the electric motor (20).

Abstract: The invention relates to an installation for operating seat modules (12) equipped with an assembly of actuators (30, 32, 34, 36, 38, 40, 42, 44) each intended for adjusting a seat element (22, 24, 26, 28). It comprises a control unit (16) suited to each seat module (12). This control unit (16) comprises means (62) for the acquisition of variables representing the functioning state of the seat module. A central unit (18) for the management of the seat modules (12) is connected to the control unit (16). It comprises means (96) for the transmission of information toward the control units (16). Each control unit (16) comprises means (66) for the transmission of variables representing the functioning state of the associated seat module toward the central management unit (18). Use in aircraft seats.